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1
Valenti, Michael. "Keeping it Cool". Mechanical Engineering 123, n.º 08 (1 de agosto de 2001): 48–52. http://dx.doi.org/10.1115/1.2001-aug-2.
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This article provides details of various aspects of air cooling technologies that can give gas turbines a boost. Air inlet cooling raises gas turbine efficiency, which is proportional to the mass flow of air fed into the turbine. The higher the mass flow, the greater the amount of electricity produced from the gas burned. Researchers at Mee Industries conduct laser scattering studies of their company’s fogging nozzles to determine if the nozzles project properly sized droplets for cooling. The goal for turbine air cooling systems is to reduce the temperature of inlet air from the dry bulb temperature, the ambient temperature, to the wet bulb temperature. The Turbidek evaporative cooling system designed by Munters Corp. of Fort Myers, Florida, is often retrofit to turbines, typically installed in front of pre-filters that remove particulates from inlet air. Turbine Air Systems designs standard chillers to improve the performance of the General Electric LM6000 and F-class gas turbines during the hottest weather.
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Khodak, E. A. y G. A. Romakhova. "Thermodynamic Analysis of Air-Cooled Gas Turbine Plants". Journal of Engineering for Gas Turbines and Power 123, n.º 2 (1 de agosto de 2000): 265–70. http://dx.doi.org/10.1115/1.1341204.
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At present high temperature, internally cooled gas turbines form the basis for the development of highly efficient plants for utility and industrial markets. Minimizing irreversibility of processes in all components of a gas turbine plant leads to greater plant efficiency. Turbine cooling, like all real processes, is an irreversible process and results in lost opportunity for producing work. Traditional tools based on the first and second laws of thermodynamics enable performance parameters of a plant to be evaluated, but they give no way of separating the losses due to cooling from the overall losses. This limitation arises from the fact that the two processes, expansion and cooling, go on simultaneously in the turbine. Part of the cooling losses are conventionally attributed to the turbine losses. This study was intended for the direct determination of lost work due to cooling. To this end, a cooled gas turbine plant has been treated as a work-producing thermodynamic system consisting of two systems that exchange heat with one another. The concepts of availability and exergy have been used in the analysis of such a system. The proposed approach is applicable to gas turbines with various types of cooling: open-air, closed-steam, and open-steam cooling. The open-air cooling technology has found the most wide application in current gas turbines. Using this type of cooling as an example, the potential of the developed method is shown. Losses and destructions of exergy in the conversion of the fuel exergy into work are illustrated by the exergy flow diagram.
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Zeitoun, Obida. "Two-Stage Evaporative Inlet Air Gas Turbine Cooling". Energies 14, n.º 5 (3 de marzo de 2021): 1382. http://dx.doi.org/10.3390/en14051382.
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Gas turbine inlet air-cooling (TIAC) is an established technology for augmenting gas turbine output and efficiency, especially in hot regions. TIAC using evaporative cooling is suitable for hot, dry regions; however, the cooling is limited by the ambient wet-bulb temperature. This study investigates two-stage evaporative TIAC under the harsh weather of Riyadh city. The two-stage evaporative TIAC system consists of indirect and direct evaporative stages. In the indirect stage, air is precooled using water cooled in a cooling tower. In the direct stage, adiabatic saturation cools the air. This investigation was conducted for the GE 7001EA gas turbine model. Thermoflex software was used to simulate the GE 7001EA gas turbine using different TIAC systems including evaporative, two-stage evaporative, hybrid absorption refrigeration evaporative and hybrid vapor-compression refrigeration evaporative cooling systems. Comparisons of different performance parameters of gas turbines were conducted. The added annual profit and payback period were estimated for different TIAC systems.
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Ibrahim, Thamir K. "The Life Cycle Assessments of Gas Turbine using Inlet Air Cooling System". Tikrit Journal of Engineering Sciences 22, n.º 1 (1 de abril de 2015): 69–75. http://dx.doi.org/10.25130/tjes.22.1.07.
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The achievement of life cycle assessments of energy systems with both maximum power output and economical profits is considered as the main objective of operations management. This paper aimed to evaluate both of the performance of a gas turbine using an inlet air cooling system as well as its life cycle cost. Accordingly, a thermodynamic model and an economic model are developed respectively to derive an analytical formula for calculating the cooling loads and life cycle cost. The major results show that, the output power of gas turbines power plant with a cooling system is (120MWh) which is higher than that of gas turbines power plant without the cooling system (96.6 MWh) at peak condition; while the life cycle cost is lower in the case of gas turbines power plant with cooling system. Thus, the proposed methods show a potential cost reduction and achievable through changing the structure of the system.
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Kim, Kyoung Hoon, Kyoung Jin Kim y Chul Ho Han. "Comparative Thermodynamic Analysis of Gas Turbine Systems with Turbine Blade Film Cooling". Advanced Materials Research 505 (abril de 2012): 539–43. http://dx.doi.org/10.4028/www.scientific.net/amr.505.539.
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Since the gas turbine systems require active cooling to maintain high operating temperature while avoiding a reduction in the system operating life, turbine blade cooling is very important and essential but it may cause the performance losses in gas turbine. This paper deals with the comparative thermodynamic analysis of gas turbine system with and without regeneration by using the recently developed blade-cooling model when the turbine blades are cooled by the method of film cooling. Special attention is paid to investigating the effects of system parameters such as pressure ratio and turbine inlet temperature on the thermodynamic performance of the systems. In both systems the thermal efficiency increases with turbine inlet temperature, but its effect is less sensitive in simpler system
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Wang, Jian, Jiang Zhou Shu, Guo Hui Huang y Ai Peng Jiang. "Measurement and Control of the Gas Turbine Inlet Air Cooling System". Applied Mechanics and Materials 220-223 (noviembre de 2012): 439–42. http://dx.doi.org/10.4028/www.scientific.net/amm.220-223.439.
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As a constant-column power generating machine, the combustion turbine has a direct proportion of its output to the quantity of input air. Therefore, when the ambient air temperature rises higher in summer, the effect of combustion turbine is decreasing. In order to enhance the efficiency of combustion turbine in summer, two sets of inlet air cooling system (IACS) were installed in PG6551(B) combustion turbines in Jinhua, Zhejiang, China. Two low-pressure evaporators were installed in the caudal flue of the waste heat boiler, therefore, the produced saturation steam drives a single-effect lithium bromide absorption chiller to cool the input air of combustion turbines to raise the output power of combustion turbine in summer; or supplies the low-pressure heater to heat the condensated water from the deaerator of the steam turbine in winter. A measurement and control system (MCS) of the new-added inlet air cooling equipments was developed. Based on the framework of DCS (Distributed Computer System), the M&C system has the IACS work correctly and easily. The structure and functions of the M&C is described in detail.
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Kim, Kyoung Hoon, Kyoung Jin Kim y Hyung Jong Ko. "Effects of Wet Compression on Performance of Regenerative Gas Turbine Cycle with Turbine Blade Cooling". Applied Mechanics and Materials 224 (noviembre de 2012): 256–59. http://dx.doi.org/10.4028/www.scientific.net/amm.224.256.
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When water is injected at an inlet of compressor, wet compression occurs due to evaporation of water droplets. In this work, the effects of wet compression on the performance of regenerative gas turbine cycle with turbine blade cooling are analytically investigated. For various pressure ratios and water injection ratios, the important system variables such as ratio of coolant flow for turbine blade cooling, fuel consumption, specific power and thermal efficiency are estimated. Parametric studies show that wet compression leads to significant enhancement in both specific power and thermal efficiency in gas turbine systems with turbine blade cooling.
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Mohd Yunus, Salmi, Savisha Mahalingam, Abreeza Manap, Nurfanizan Mohd Afandi y Meenaloshini Satgunam. "Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review". Coatings 11, n.º 5 (10 de mayo de 2021): 560. http://dx.doi.org/10.3390/coatings11050560.
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Thermal barrier coating (TBC) and cooling air systems are among the technologies that have been introduced and applied in pursuing the extensive development of advanced gas turbine. TBC is used to protect the gas turbine components from the higher operating temperature of advanced gas turbine, whereas cooling air systems are applied to assist TBC in lowering the temperature exposure of protected surfaces. Generally, a gas turbine operates in three main operational modes, which are base load, peak load, and part peak load. TBC performance under these three operational modes has become essential to be studied, as it will provide the gas turbine owners not only with the behaviors and damage mechanism of TBC but also a TBC life prediction in a particular operating condition. For TBC under base load or so called steady-state condition, a number of studies have been reviewed and discussed. However, it has been found that most of the studies have been conducted without the assistance of a cooling air system, which does not simulate the TBC in advanced gas turbine completely. From this review, the studies on TBC-assisted cooling air system to simulate the advanced gas turbine operating conditions have also been summarized, which are limited to test rig simulations under thermal cyclic mode where thermal cyclic represents peak and part peak load conditions. The equipment used to simulate the gas turbine operating condition, test temperatures, and durations are parameters that have been taken into consideration under this review. Finally, a test rig that is capable of simulating both TBC and cooling air effects at a high operating temperature of advanced gas turbines for prolonged exposure under steady-state condition has been proposed to be developed.
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Kakaras, E., A. Doukelis, A. Prelipceanu y S. Karellas. "Inlet Air Cooling Methods for Gas Turbine Based Power Plants". Journal of Engineering for Gas Turbines and Power 128, n.º 2 (23 de septiembre de 2005): 312–17. http://dx.doi.org/10.1115/1.2131888.
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Background: Power generation from gas turbines is penalized by a substantial power output loss with increased ambient temperature. By cooling down the gas turbine intake air, the power output penalty can be mitigated. Method of Approach: The purpose of this paper is to review the state of the art in applications for reducing the gas turbine intake air temperature and examine the merits from integration of the different air-cooling methods in gas-turbine-based power plants. Three different intake air-cooling, methods (evaporative cooling, refrigeration cooling, and evaporative cooling of precompressed air) have been applied in two combined cycle power plants and two gas turbine plants. The calculations were performed on a yearly basis of operation, taking into account the time-varying climatic conditions. The economics from integration of the different cooling systems were calculated and compared. Results: The results have demonstrated that the highest incremental electricity generation is realized by absorption intake air-cooling. In terms of the economic performance of the investment, the evaporative cooler has the lowest total cost of incremental electricity generation and the lowest payback period (PB). Concerning the cooling method of pre-compressed air, the results show a significant gain in capacity, but the total cost of incremental electricity generation in this case is the highest. Conclusions: Because of the much higher capacity gain by an absorption chiller system, the evaporative cooler and the absorption chiller system may both be selected for boosting the performance of gas-turbine-based power plants, depending on the prevailing requirements of the plant operator.
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Zhang, Han, Hua Chen, Chao Ma y Feng Guo. "INVESTIGATION OF CONJUGATED HEAT TRANSFER FOR A RADIAL TURBINE WITH IMPINGEMENT COOLING". Journal of Physics: Conference Series 2087, n.º 1 (1 de noviembre de 2021): 012037. http://dx.doi.org/10.1088/1742-6596/2087/1/012037.
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Abstract Radial turbine is widely used in micro-turbines, turbochargers, small jet engines and expanders, and the pursue of high system efficiency has resulted in elevated turbine inlet temperatures for some of its applications, threatening its reliability. There are, however, few cooling studies on radial turbines. This paper studies the jet impingement cooling of a turbocharger radial turbine. A small amount of air (coolant), which could come from compressor discharge cooled by an intercooler, is injected through a few jet holes on the heat shield of the turbine onto the upper part of turbine backdisc, to cool the rotor blades and the backdisc. Parameters that may affect the cooling were studied by a Conjugated Heat Transfer (CHT) numerical simulation using steady flow calculations. The influences to the cooling effects by different coolant-to-turbine mass flow ratios, Coolant-to-turbine inlet temperature ratio, number of the jets etc. were analysed by a steady flow simulation. The simulation results show that, when four jet holes are placed at blade leading edge radius, using 1.0% ~ 3.0% of the main gas mass flow of coolant, the average temperature on leading edge, inducer hub and backdisc surface is reduced by 2K ~ 17K,27K ~ 65K and 51K ~ 70K respectively. Turbine efficiency is mostly reduced little over 1% point.
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Che Sidik, Nor Azwadi y Shahin Salimi. "The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator". Applied Mechanics and Materials 695 (noviembre de 2014): 371–75. http://dx.doi.org/10.4028/www.scientific.net/amm.695.371.
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Gas turbine cooling can be classified into two different schemes; internal and external cooling. In internal cooling method, the coolant provided by compressor is forced into the cooling flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected coolant is directly perfused from coolant manifold to save downstream components against hot gases. Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream to a component. There are several ways in external cooling. Film cooling is one of the best cooling systems for the application on gas turbine blades. This study concentrates on the comparison of experimental, computational and numerical investigations of advanced film cooling performance for cylindrical holes at different angles and different blowing ratios in modern turbine gas.
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Costa, Raphael Camargo da, Cesar Augusto Arezo e. Silva Jr., Júlio Cesar Costa Campos, Washington Orlando Irrazabal Bohorquez, Rogerio Fernandes Brito y Antônio M. Siqueira. "A technical-economic analysis of turbine inlet air cooling for a heavy duty gas turbine operating with blast-furnace gas". Research, Society and Development 10, n.º 9 (29 de julio de 2021): e59810915006. http://dx.doi.org/10.33448/rsd-v10i9.15006.
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The study was developed inside an integrated steel mill, located in Rio de Janeiro city, aiming to analyse the technical-economic feasibility of installing a new inlet air refrigeration system for the gas turbines. The technologies applied for such purpose are named Turbine Inlet Air Cooling (TIAC) technologies. The power plant utilizes High Fogging and Evaporative Cooling methods for reducing the compressor’s inlet air temperature, however, the ambient climate condition hampers the turbine’s power output when considering its design operation values. Hence, this study was proposed to analyse the installation of an additional cooling system. The abovementioned power plant has two heavy-duty gas turbines and one steam turbine, connected in a combined cycle configuration. The cycle nominal power generation capacity is 450 MW with each of the gas turbines responsible for 90 MW. The gas turbines operate with steelwork gases, mainly blast furnace gas (BFG), and natural gas. The plant has its own weather station, which provided significant and precise data regarding the local climate conditions over the year of 2017. An in-house computer model was created to simulate the gas turbine power generation and fuel consumption considering both cases: with the proposed TIAC system and without it, allowing the evaluation of the power output increase due to the new refrigeration system. The results point out for improvements of 4.22% on the power output, corresponding to the electricity demand of approximately 32960 Brazilian homes per month or yearly earnings of 3.92 million USD.
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Bunker, Ronald S. "Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges". Journal of Turbomachinery 129, n.º 2 (16 de julio de 2006): 193–201. http://dx.doi.org/10.1115/1.2464142.
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The advancement of turbine cooling has allowed engine design to exceed normal material temperature limits, but it has introduced complexities that have accentuated the thermal issues greatly. Cooled component design has consistently trended in the direction of higher heat loads, higher through-wall thermal gradients, and higher in-plane thermal gradients. The present discussion seeks to identify ten major thermal issues, or opportunities, that remain for the turbine hot gas path (HGP) today. These thermal challenges are commonly known in their broadest forms, but some tend to be little discussed in a direct manner relevant to gas turbines. These include uniformity of internal cooling, ultimate film cooling, microcooling, reduced incident heat flux, secondary flows as prime cooling, contoured gas paths, thermal stress reduction, controlled cooling, low emission combustor-turbine systems, and regenerative cooling. Evolutionary or revolutionary advancements concerning these issues will ultimately be required in realizable engineering forms for gas turbines to breakthrough to new levels of performance. Herein lies the challenge to researchers and designers. It is the intention of this summary to provide a concise review of these issues, and some of the recent solution directions, as an initial guide and stimulation to further research.
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Budi, Setya y Bambang Arip Dwiyantoro. "Experimental of the Influence of Blade Pitch Angle Cooler Fan on the Performance of Closed Cooling Water System Gas Turbine". Applied Mechanics and Materials 913 (3 de marzo de 2023): 53–58. http://dx.doi.org/10.4028/p-wtn1wy.
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A closed cooling water system is one of the systems contained in gas turbines. The main function of this system is to cool the lubricating oil and winding generator. Decreased performance of closed cooling water system can cause the gas turbine protection system to be active and cause the gas turbine trip. The study began with data collection, both design data for the heat exchanger cooler fan and operating data from the closed cooling water system on the gas turbine. An experiment was carried out by varying the blade pitch angle cooler fan to measure the work parameters in the field and analyzing the results of these measurements against the performance of the heat exchanger cooler fan. Variations of blade pitch angle cooler fan were done by limiting the working parameters of the cooling fan motor. The result of this study was an increase in the blade pitch angle cooler fan results in an increase in the flow rate of the cooler fan, this also affected the heat transfer rate of the heat exchanger cooler fan which grew when the blade pitch angle cooler fan was raised. The increase of blade pitch angle cooler fan also resulted in a decrease in the temperature of closed cooling water on the heat exchanger cooler fan outlet.
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Kien, L. C. y N. Harada. "Power generation system using two models for an inertial confinement fusion reactor". Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, n.º 5 (1 de agosto de 2005): 353–60. http://dx.doi.org/10.1243/095765005x31144.
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In this study, the series cooling model and the parallel cooling model of inertial confinement fusion reactor were used as a heat source for driving the MHD/Gas Turbine combined power generation system. This reactor is designed with the first wall and the blanket, which are used to collect the products of fusion reactions (including X-ray, charged particles, and neutrons) and to convert the fusion energy into thermal energy. In the series cooling model, the coolant after being heated in the blanket is re-heated again in the first wall, therefore, > 2000 K working gas can be obtained. In the parallel cooling model, 1300-1700 K working gas was extracted from the blanket for driving the Gas Turbine cycle and high temperature 2000-2400 K working gas can be extracted from the first wall for driving the MHD cycle. The system using the series cooling model reached a highest plant efficiency of 58.34 per cent whereas the system using the parallel cooling model reached a highest plant efficiency of 57.49 per cent. It was found that the enthalpy extraction and the first wall output temperature both affected the fusion output power, therefore, the plant efficiency was greatly affected by these factors. With the increase of reactor output temperature, the plant efficiency increased, however, because of the temperature limitation of the Gas Turbine and blanket, an output temperature > 2400 K from reactor cannot be used.
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Roy Yap, Mun y Ting Wang. "Simulation of Producer Gas Fired Power Plants with Inlet Fog Cooling and Steam Injection". Journal of Engineering for Gas Turbines and Power 129, n.º 3 (9 de diciembre de 2006): 637–47. http://dx.doi.org/10.1115/1.2718571.
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Biomass can be converted to energy via direct combustion or thermochemical conversion to liquid or gas fuels. This study focuses on burning producer gases derived from gasifying biomass wastes to produce power. Since the producer gases are usually of low calorific values (LCV), power plant performance under various operating conditions has not yet been proven. In this study, system performance calculations are conducted for 5MWe power plants. The power plants considered include simple gas turbine systems, steam turbine systems, combined cycle systems, and steam injection gas turbine systems using the producer gas with low calorific values at approximately 30% and 15% of the natural gas heating value (on a mass basis). The LCV fuels are shown to impose high compressor back pressure and produce increased power output due to increased fuel flow. Turbine nozzle throat area is adjusted to accommodate additional fuel flows to allow the compressor to operate within safety margin. The best performance occurs when the designed pressure ratio is maintained by widening nozzle openings, even though the turbine inlet pressure is reduced under this adjustment. Power augmentations under four different ambient conditions are calculated by employing gas turbine inlet fog cooling. Comparison between inlet fog cooling and steam injection using the same amount of water mass flow indicates that steam injection is less effective than inlet fog cooling in augmenting power output. Maximizing steam injection, at the expense of supplying the steam to the steam turbine, significantly reduces both the efficiency and the output power of the combined cycle. This study indicates that the performance of gas turbine and combined cycle systems fueled by the LCV fuels could be very different from the familiar behavior of natural gas fired systems. Care must be taken if on-shelf gas turbines are modified to burn LCV fuels.
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Caturwati, Ni Ketut, Yusvardi Yusuf y Muhammad Ilham Al Faiz. "(Performance of Gas Turbine Cooling System (Radiator) at PLTGU XYZ against Environmental Air Temperature)". R.E.M. (Rekayasa Energi Manufaktur) Jurnal 5, n.º 1 (12 de enero de 2021): 15–21. http://dx.doi.org/10.21070/r.e.m.v5i1.889.
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The heat exchanger is an important component in the gas and steam power plant (PLTGU) industry. One of the most important heat exchangers in gas turbine cooling systems is the gas turbine radiator. The gas turbine radiator functions to cool the cooling water, which circulated to various components of the gas turbine by using environmental air as the cooling medium. The purpose of this study was to determine the effect of environmental temperature on the performance of gas turbine radiators and to compare operational data in 2017 with operational data when the study conducted in 2019. Data collected for 3 days with 2-3 hour intervals. Data processing and analysis shows that the higher the ambient temperature, the higher the radiator effectiveness value. Data in 2017 shows the highest average value of effectiveness obtained at an ambient air temperature of 35 ˚C of 71,274%. Meanwhile, data in 2019 shows the highest average value of effectiveness at an ambient air temperature of 35 ˚C of 58,859%. Thus, the average effectiveness value of gas turbine radiators has decreased by 12,415% from 2017 to 2019
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Kail, C. "Evaluation of Advanced Combined Cycle Power Plants". Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 212, n.º 1 (febrero de 1998): 1–12. http://dx.doi.org/10.1177/095765099821200101.
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This report will analyse and evaluate the most recent and significant trends in combined cycle gas turbine (CCGT) power plant configurations. The various enhancements will be compared with the ‘simple’ gas turbine. The first trend, a gas turbine with reheat, cannot convert its better efficiency and higher output into a lower cost of electrical power. The additional investments required as well as increased maintenance costs will neutralize all the thermodynamic performance advantages. The second concept of cooling the turbine blades with steam puts very stringent requirements on the blade materials, the steam quality and the steam cooling system design. Closed-loop steam cooling of turbine blades offers cost advantages only if all its technical problems can be solved and the potential risks associated with the process can be eliminated through long demonstration programmes in the field. The third configuration, a gas turbine with a closed-loop combustion chamber cooling system, appears to be less problematic than the previous, steam-cooled turbine blades. In comparison with an open combustion chamber cooling system, this solution is more attractive due to better thermal performance and lower emissions. Either air or steam can be used as the cooling fluid.
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Ibrahim, Thamir K., Mohammed K. Mohammed, Omar I. Awad, Rizalman Mamat y M. Kh Abdolbaqi. "Thermal and Economic Analysis of Gas Turbine Using Inlet Air Cooling System". MATEC Web of Conferences 225 (2018): 01020. http://dx.doi.org/10.1051/matecconf/201822501020.
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A basic goal of operation management is to successfully complete the life cycle of power systems, with optimum output against minimal input. This document intends calculating both, the performance and the life cycle cost of a gas turbine fitted with an inlet air cooling mechanism. Correspondingly, both a thermodynamic and an economic model are drawn up, to present options towards computing the cooling loads and the life cycle costs. The primary observations indicate that around 120MWh of power is derived from gas turbine power plants incorporating the cooling mechanism, compared to 96.6 MWh for units without the mechanism, while the life cycle cost is lower for units incorporating the cooling process. This indicates benefits in having the mechanism incorporated in the architecture of a gas turbine.
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Ito, Shoko, Hiroshi Saeki, Asako Inomata, Fumio Ootomo, Katsuya Yamashita, Yoshitaka Fukuyama, Elichi Koda et al. "Conceptual Design and Cooling Blade Development of 1700°C Class High-Temperature Gas Turbine". Journal of Engineering for Gas Turbines and Power 127, n.º 2 (1 de abril de 2005): 358–68. http://dx.doi.org/10.1115/1.1806456.
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In this paper we describe the conceptual design and cooling blade development of a 1700°C-class high-temperature gas turbine in the ACRO-GT-2000 (Advanced Carbon Dioxide Recovery System of Closed-Cycle Gas Turbine Aiming 2000 K) project. In the ACRO-GT closed cycle power plant system, the thermal efficiency aimed at is more than 60% of the higher heating value of fuel (HHV). Because of the high thermal efficiency requirement, the 1700°C-class high-temperature gas turbine must be designed with the minimum amount of cooling and seal steam consumption. The hybrid cooling scheme, which is a combination of closed loop internal cooling and film ejection cooling, was chosen from among several cooling schemes. The elemental experiments and numerical studies, such as those on blade surface heat transfer, internal cooling channel heat transfer, and pressure loss and rotor coolant passage distribution flow phenomena, were conducted and the results were applied to the conceptual design advancement. As a result, the cooling steam consumption in the first stage nozzle and blade was reduced by about 40% compared with the previous design that was performed in the WE-NET (World Energy Network) Phase-I.
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Kharlina, Ekaterina. "LOW-EMISSION COMBUSTION CHAMBERS AND COOLING SYSTEMS". Perm National Research Polytechnic University Aerospace Engineering Bulletin, n.º 70 (2022): 29–40. http://dx.doi.org/10.15593/2224-9982/2022.70.03.
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A modern gas turbine engine must meet a large list of requirements that are included in the parameters, resource and per-formance indicators. To increase the service life of a gas turbine engine at elevated temperatures of the gas flow, it is expendable to use thermal barrier protection on explosive structural materials. Cyclic tests of materials and thermal barrier coatings of gas tur-bine engines at temperatures above 1500 ºС are proposed to be carried out on a stand in which a hot gas flow is generated by an air-methane burner. In order to reduce the emission standards for nitrogen and carbon oxides, it is necessary to develop and use in stationary gas turbine engines fundamentally new technologies for organizing combustion and, as a result, designs of combustion chambers. From a detailed analysis of the current requirements, it follows that the newly designed low-emission combustion chamber for advanced gas turbine engines and installations should be accompanied by an increase in gas temperature by 200–300 K, an increase in the durability of the flame tube by 3–4 times, with a twofold decrease in the proportion of air for cooling the walls, a twofold or more reduction in the emission of harmful substances. In this article, heat-resistant coatings of structural elements of gas turbines are considered. The concepts of low-emission fuel combustion are described by organizing the working process according to the "DLE" - Dry Low Emission scheme. As an alter-native method for organizing low-emission combustion, stoichiometric combustion is proposed, which also makes it possible to provide the required temperature of the gas jet. A review of low-emission combustion chambers has been carried out. The existing methods of cooling the combustion chambers of gas turbine and liquid rocket engines are described. The analysis of the collected information made it possible to determine the concept of designing a high-temperature air-methane burner.
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Ebenhoch, G. y T. M. Speer. "Simulation of Cooling Systems in Gas Turbines". Journal of Turbomachinery 118, n.º 2 (1 de abril de 1996): 301–6. http://dx.doi.org/10.1115/1.2836640.
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The design of cooling systems for gas turbine engine blades and vanes calls for efficient simulation programs. The main purpose of the described program is to determine the complete boundary condition at the coolant side to support a temperature calculation for the solid. For the simulation of convection and heat pick up of the coolant flow, pressure loss, and further effects to be found in a rotating frame, the cooling systems are represented by networks of nodes and flow elements. Within each flow element the fluid flow is modeled by a system of ordinary differential equations based on the one-dimensional conservation of mass, momentum, and energy. In this respect, the computer program differs from many other network computation programs. Concerning cooling configurations in rotating systems, the solution for a single flow element or the entire flow system is not guaranteed to be unique. This is due to rotational forces in combination with heat transfer and causes considerable computational difficulties, which can be overcome by a special path following method in which the angular velocity is selected as the parameter of homotopy. Results of the program are compared with measurements for three applications.
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El-Masri, M. A. "GASCAN—An Interactive Code for Thermal Analysis of Gas Turbine Systems". Journal of Engineering for Gas Turbines and Power 110, n.º 2 (1 de abril de 1988): 201–9. http://dx.doi.org/10.1115/1.3240104.
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A general, dimensionless formulation of the thermodynamic, heat transfer, and fluid-dynamic processes in a cooled gas turbine is used to construct a compact, flexible, interactive system-analysis program. A variety of multishaft systems using surface or evaporative intercoolers, surface recuperators, or rotary regenerators, and incorporating gas turbine reheat combustors, can be analyzed. Different types of turbine cooling methods at various levels of technology parameters, including thermal barrier coatings, may be represented. The system configuration is flexible, allowing the number of turbine stages, shaft/spool arrangement, number and selection of coolant bleed points, and coolant routing scheme to be varied at will. Interactive iterations between system thermodynamic performance and simplified quasi-three-dimensional models of the turbine stages allow exploration of realistic turbine-design opportunities within the system/thermodynamic parameter space. The code performs exergy-balance analysis to break down and trace system inefficiencies to their source components and source processes within the components, thereby providing insight into the interactions between the components and the system optimization tradeoffs.
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Radchenko, Andrii, Eugeniy Trushliakov, Krzysztof Kosowski, Dariusz Mikielewicz y Mykola Radchenko. "Innovative Turbine Intake Air Cooling Systems and Their Rational Designing". Energies 13, n.º 23 (25 de noviembre de 2020): 6201. http://dx.doi.org/10.3390/en13236201.
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The efficiency of cooling ambient air at the inlet of gas turbines in temperate climatic conditions was analyzed and reserves for its enhancing through deep cooling were revealed. A method of logical analysis of the actual operation efficiency of turbine intake air cooling systems in real varying environment, supplemented by the simplest numerical simulation was used to synthesize new solutions. As a result, a novel trend in engine intake air cooling to 7 or 10 °C in temperate climatic conditions by two-stage cooling in chillers of combined type, providing an annual fuel saving of practically 50%, surpasses its value gained due to traditional air cooling to about 15 °C in absorption lithium-bromide chiller of a simple cycle, and is proposed. On analyzing the actual efficiency of turbine intake air cooling system, the current changes in thermal loads on the system in response to varying ambient air parameters were taken into account and annual fuel reduction was considered to be a primary criterion, as an example. The improved methodology of the engine intake air cooling system designing based on the annual effect due to cooling was developed. It involves determining the optimal value of cooling capacity, providing the minimum system sizes at maximum rate of annual effect increment, and its rational value, providing a close to maximum annual effect without system oversizing at the second maximum rate of annual effect increment within the range beyond the first maximum rate. The rational value of design cooling capacity provides practically the maximum annual fuel saving but with the sizes of cooling systems reduced by 15 to 20% due to the correspondingly reduced design cooling capacity of the systems as compared with their values defined by traditional designing focused to cover current peaked short-term thermal loads. The optimal value of cooling capacity providing the minimum sizes of cooling system is very reasonable for applying the energy saving technologies, for instance, based on the thermal storage with accumulating excessive (not consumed) cooling capacities at lowered current thermal loads to cover the peak loads. The application of developed methodology enables revealing the thermal potential for enhancing the efficiency of any combustion engine (gas turbines and engines, internal combustion engines, etc.).
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KUDINOV, Anatoly A. y Yulia E. DEMINA. "CALCULATION OF THE DRAINAGE SYSTEM OF LEAVING FLUE GASES FROM THE TURBINE THROUGH THE COOLING TOWER". Urban construction and architecture 8, n.º 1 (15 de marzo de 2018): 135–38. http://dx.doi.org/10.17673/vestnik.2018.01.23.
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The article presents result of a research a system of the venting of exhaust gases of the recovery boiler the gas turbine plant through the natural draft cooling tower in the environment. The use of this scheme allows the fl ue gases to lower the temperature of the circulating water at the outlet of the cooling tower to provide a deeper vacuum in the condenser steam turbine combined cycle power plant with simultaneous reduction of capital to build chimneys. As a result of the application of this scheme, an increase in the absolute electric effi ciency of turbines is achieved. As stated in Article method of calculating the removal of exhaust fl ue gas systems with a perforated distributor ring allows to determine the level of engineering design and volume requirements of these systems.
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De Lucia, M., R. Bronconi y E. Carnevale. "Performance and Economic Enhancement of Cogeneration Gas Turbines Through Compressor Inlet Air Cooling". Journal of Engineering for Gas Turbines and Power 116, n.º 2 (1 de abril de 1994): 360–65. http://dx.doi.org/10.1115/1.2906828.
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Gas turbine air cooling systems serve to raise performance to peak power levels during the hot months when high atmospheric temperatures cause reductions in net power output. This work describes the technical and economic advantages of providing a compressor inlet air cooling system to increase the gas turbine’s power rating and reduce its heat rate. The pros and cons of state-of-the-art cooling technologies, i.e., absorption and compression refrigeration, with and without thermal energy storage, were examined in order to select the most suitable cooling solution. Heavy-duty gas turbine cogeneration systems with and without absorption units were modeled, as well as various industrial sectors, i.e., paper and pulp, pharmaceuticals, food processing, textiles, tanning, and building materials. The ambient temperature variations were modeled so the effects of climate could be accounted for in the simulation. The results validated the advantages of gas turbine cogeneration with absorption air cooling as compared to other systems without air cooling.
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El-Masri, M. A. "On Thermodynamics of Gas-Turbine Cycles: Part 3—Thermodynamic Potential and Limitations of Cooled Reheat-Gas-Turbine Combined Cycles". Journal of Engineering for Gas Turbines and Power 108, n.º 1 (1 de enero de 1986): 160–68. http://dx.doi.org/10.1115/1.3239864.
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Reheat gas turbines have fundamental thermodynamic advantages in combined cycles. However, a larger proportion of the turbine expansion path is exposed to elevated temperatures, leading to increased cooling losses. Identifying cooling technologies which minimize those losses is crucial to realizing the full potential of reheat cycles. The strong role played by cooling losses in reheat cycles necessitates their inclusion in cycle optimization. To this end, the models for the thermodynamics of combined cycles and cooled turbines presented in Parts 1 and 2 of this paper have been extended where needed and applied to the analysis of a wide variety of cycles. The cooling methods considered range from established air-cooling technology to methods under current research and development such as air-transpiration, open-loop, and closed-loop water cooling. Two schemes thought worthy of longer-term consideration are also assessed. These are two-phase transpiration cooling and the regenerative thermosyphon. A variety of configurations are examined, ranging from Brayton-cycles to one or two-turbine reheats, with or without compressor intercooling. Both surface intercoolers and evaporative water-spray types are considered. The most attractive cycle configurations as well as the optimum pressure ratio and peak temperature are found to vary significantly with types of cooling technology. Based upon the results of the model, it appears that internal closed-loop liquid cooling offers the greatest potential for midterm development. Hybrid systems with internally liquid-cooled nozzles and traditional air-cooled rotors seem most attractive for the near term. These could be further improved by using steam rather than air for cooling the rotor.
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Портной, Богдан Сергійович, Андрій Миколайович Радченко, Роман Миколайович Радченко y Сергій Анатолійович Кантор. "ВИКОРИСТАННЯ РЕЗЕРВУ ХОЛОДОПРОДУКТИВНОСТІ АБСОРБЦІЙНОЇ ХОЛОДИЛЬНОЇ МАШИНИ ПРИ ОХОЛОДЖЕННІ ПОВІТРЯ НА ВХОДІ ГТУ". Aerospace technic and technology, n.º 3 (27 de junio de 2018): 39–44. http://dx.doi.org/10.32620/aktt.2018.3.05.
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The processes of air cooling at the gas turbine unit inlet by absorption lithium-bromide chiller have been analyzed. The computer programs of firms-producers of heat exchangers were used for the gas turbine unit inlet air cooling processes simulation. The absorption lithium-bromide chiller refrigeration capacity reserve (the design heat load excess over the current heat loads) generated at the reduced current heat loads on the air coolers at the gas turbine unit inlet in accordance with the lowered ambient air parameters has been considered. The absorption lithium-bromide chiller refrigeration capacity reserve is expedient to use at increased heat load on the air cooler. To solve this problem the refrigeration capacity required for cooling air at the gas turbine unit inlet has been compared with the excessive absorption lithium-bromide chiller refrigeration capacity exceeding current heat loads during July 2017.The scheme of gas turbine unit inlet air cooling system with using the absorption lithium-bromide chiller refrigeration capacity reserve has been proposed. The proposed air cooling system provides gas turbine unit inlet air precooling in the air cooler booster stage by using the absorption lithium-bromide chiller excessive refrigeration capacity. The absorption chiller excessive refrigeration capacity generated during decreased heat loads on the gas turbine unit inlet air cooler is accumulated in the thermal storage. The results of simulation show the expediency of the gas turbine unit inlet air cooling by using the absorption lithium-bromide chiller refrigeration capacity reserve, which is generated at reduced thermal loads, for the air precooling in the air cooler booster stage. This solution provides the absorption lithium-bromide chiller installed (designed) refrigeration capacity and cost reduction by almost 30%. The solution to increase the efficiency of gas turbine unit inlet air cooling through using the absorption chiller excessive refrigeration potential accumulated in the thermal storage has been proposed.
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Радченко, Андрій Миколайович, Роман Миколайович Радченко, Сергій Анатолійович Кантор, Богдан Сергійович Портной y Веніамін Сергійович Ткаченко. "ОХОЛОДЖЕННЯ ПОВІТРЯ НА ВХОДІ ГТУ З ВИКОРИСТАННЯМ РЕЗЕРВУ ХОЛОДОПРОДУКТИВНОСТІ АБСОРБЦІЙНОЇ ХОЛОДИЛЬНОЇ МАШИНИ В БУСТЕРНОМУ ПОВІТРООХОЛОДЖУВАЧІ". Aerospace technic and technology, n.º 1 (25 de febrero de 2018): 64–69. http://dx.doi.org/10.32620/aktt.2018.1.07.
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The processes of gas turbine unit inlet air cooling by absorption lithium-bromide chiller utilizing the turbine exhaust gas waste heat as athermotransformer has been analyzed for hour-by-hour changing ambient air temperatures and changeable heat loads on the air cooler as consequence. The computer programs of the firms-producers of heat exchangers were used for gas turbine unit inlet air cooling processes simulation. It is shown that at decreased heat loads on the air cooler an excessive refrigeration capacity of the absorption lithium-bromidechiller exceeding current heat loads is generated which can be used for covering increased heat loads on the air cooler and to reduce the refrigeration capacity of the absorption lithium-bromidechiller applied. To solve this task the refrigeration capacity required for gas turbine unit inlet air cooling is compared with an excessive refrigeration capacity of the absorption lithium-bromidechiller exceeding current heat loads summarized during 10 days of July 2015. The system of gas turbine unit inlet air cooling with a buster stage of precooling air and a base stage of cooling air to the temperature of about 15 °C by absorption lithium-bromide chiller has been proposed. An excessive refrigeration capacity of the absorption chiller generated during decreased heat loads on the gas turbine unit inlet air cooler that is collected in the thermal accumulator is used for gas turbine unit inlet air precooling in a buster stage of air cooler during increased heat loads on the air cooler. The results of gas turbine unit inlet air cooling processes simulation proved the reduction of refrigeration capacity of the absorption lithium-bromide chiller applied by 30-40 % due to the use of a buster stage of precooling air at the expanse of an excessive absorptionchiller refrigeration capacity served in the thermal accumulator. So the conclusion has been made about the efficient use of a buster stage of gas turbine unit inlet air cooler for precooling air by using an excessive refrigeration potential of absorption lithium-bromidechiller coolant saved in the thermal accumulator
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Bin Abas, Mohd Firdaus, Abdullah Aslam, Hamidon bin Salleh y Nor Adrian Bin Nor Salim. "Recent Trends of Impingement Cooling System Enhancement for Gas Turbine". Applied Mechanics and Materials 465-466 (diciembre de 2013): 496–99. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.496.
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Efforts have been given to improve the turbine blades ability to withstand high temperature for a long period of time by implementing effective cooling system. There are many aspects that should be considered when implementing impingement cooling. This paper will only cover two trending aspects in impingement cooling implementation; the jet-to-target plate distance and the application of ribs in promoting better impingement cooling performance. For target plate distance to impingement jet diameter value, H/d > 1, the area-averaged Nusselt number also decreases as the H/d value increases. This may have been due to a reduction of the amount of momentum exerted by the impinging jets onto the target plate. For H/d < 1, the results have been proven otherwise. Heat transfer in impingement/effusion cooling system in crossflow with rib turbulators showed higher heat transfer rate than that of a surface without ribs because the ribs prevent the wall jets from being swept away by the crossflow and increase local turbulence of the flow near the surface. It could be concluded that both H/d ratio and ribs installation play an important role in enhancing impingement cooling systems heat transfer effectiveness.
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Kim, Kwang Su y Youn Jea Kim. "Experimental Study on the Film Cooling Performance at the Leading Edge of Turbine Blade Using Infrared Thermography". Key Engineering Materials 326-328 (diciembre de 2006): 1161–64. http://dx.doi.org/10.4028/www.scientific.net/kem.326-328.1161.
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In order to protect turbine blades from high temperature, film cooling can be applied to gas turbine engine system since it can prevent corrosion and facture of material. To enhance the film cooling performance in the vicinity of the turbine blade leading edge, flow characteristics of the film-cooled turbine blade have been investigated using a cylindrical body model. Mainstream Reynolds number based on the cylinder diameter was 1.01×105 and the mainstream turbulence intensities were about 0.2%. CO2 was used as coolant to simulate the effect of coolant-tomainstream density ratio. The effect of coolant flow rates was studied for various blowing ratios of 0.5, 0.8, 1.1 and 1.4, respectively. Results show that the blowing ratio has a strong effect on film cooling effectiveness and the coolant trajectory is sensitive to the blowing ratio.
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Kim, Kyoung Hoon, Dong Joo Kim, Kyoung Jin Kim y Seong Wook Hong. "Transient Analysis of Inlet Fogging Process for Gas Turbine Systems". Applied Mechanics and Materials 234 (noviembre de 2012): 17–22. http://dx.doi.org/10.4028/www.scientific.net/amm.234.17.
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Gas turbine inlet fogging is a method of cooling intake air by injecting demineralized water in the duct through the special atomizing nozzles. Gas turbine cycles with inlet fogging could offer enhanced efficiency with low complexity, so the inlet air-cooling is considered the most cost-effective way to increase the power output as well as thermal efficiency of gas turbines. In this work the inlet fogging process is modeled based on the evaporation of droplets. Transient behaviors of the process are investigated with analytic expressions obtained by considering heat and mass transfer and thermodynamic relations. Effects of water injection ratio on the transient behaviors of temperature of mixed air, mass of liquid droplets, mass flux and heat transfer from the droplets are thoroughly investigated. Results show also the dependencies of system parameters on the critical injection ratio and evaporation time.
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Zhu, Hong Mei, Heng Sun y Tian Quan Pan. "Theoretical Study of the Operation Performance of a Natural Gas CCHP System under Variable Loads". Applied Mechanics and Materials 71-78 (julio de 2011): 1765–68. http://dx.doi.org/10.4028/www.scientific.net/amm.71-78.1765.
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A theoretical study of the performance of a CCHP system using natural gas as fuel which consists of gas turbine-steam turbine combined cycle, absorption refrigeration unit and exhaust heat boiler under variable loads was carried out. Two methods to adjust the electric and cooling loads are employed here. One method is to increase the outlet pressure of the steam turbine in the Rankine cycle. Another way is to change the air coefficient of the gas turbine. The calculation results show that the first method can obtain higher energy efficient and is the preferred method. The second way can be employed in case that further more cooling is required.
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Torbidoni, Leonardo y Aristide F. Massardo. "Analytical Blade Row Cooling Model for Innovative Gas Turbine Cycle Evaluations Supported by Semi-Empirical Air-Cooled Blade Data". Journal of Engineering for Gas Turbines and Power 126, n.º 3 (1 de julio de 2004): 498–506. http://dx.doi.org/10.1115/1.1707030.
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With the objective of performing reliable innovative gas turbine cycle calculations, a new procedure aimed at evaluating blade cooling performance is presented. This complete analytical (convective and film) blade cooling modeling provides the coolant mass flow and pressure loss estimation, and is a useful tool in the field of innovative gas turbine cycle analysis, mainly when alternative fluids are considered. In this case, in fact, the conventional semi-empirical data based on the use of air as traditional coolant and working media are no longer suitable. So the analytical approach represents a way of properly investigating alternative cooling methods and fluids. In the presented analysis the effects of internal blade geometry on cooling performance are summarized by the Z parameter, which also highly affects the coolant flow pressure losses. Since existing technology represents a natural starting point for the assessment of Z, the model is able to automatically estimate a proper value relying only on available semi-empirical data which were established for air-cooled gas turbine blades. When alternative fluids are considered, the same estimated value of Z is still maintained for the calculation, with the result of investigating the performance of existing blade technology for novel operational conditions. This represents an example of how the analytical approach, supported by conventional air-cooled blade semi-empirical data, appears as an innovative tool in the analysis of novel gas turbine cycles. In fact, the simulation results for the cooled blade were easily employed on the whole system level (gas turbine).
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Радченко, Андрій Миколайович, Богдан Сергійович Портной, Сергій Анатолійович Кантор y Ігор Петрович Єсін. "ОЦІНКА ЕФЕКТИВНОСТІ ГЛИБОКОГО ОХОЛОДЖЕННЯ ПОВІТРЯ НА ВХОДІ ГТУ ТЕПЛОВИКОРИСТОВУЮЧИМИ ХОЛОДИЛЬНИМИ МАШИНАМИ". Aerospace technic and technology, n.º 6 (24 de diciembre de 2019): 10–14. http://dx.doi.org/10.32620/aktt.2019.6.02.
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Significant fluctuations in the current temperature and relative humidity of the ambient air lead to significant changes in the heat load on the air cooling system at the inlet of the gas turbine unit, which urgently poses the problem of choosing their design heat load, as well as evaluating the efficiency of the air cooling system for a certain period of time. The efficiency of deep air cooling at the inlet of gas turbine units was studied with a change during July 2015–2018 for climatic conditions of operation at the compressor station Krasnopolie, Dnepropetrovsk region (Ukraine). For air cooling, the use of a waste heat recovery chiller, which transforms the heat of exhaust gases of gas turbine units into the cold, has been proposed. The efficiency of air cooling at the inlet of gas turbine units for different temperatures has been analyzed: down to 15 °C – an absorption lithium-bromide chiller, which is used as the first high-temperature stage for pre-cooling of ambient air, and down to 10 °C – a combined absorption-ejector chiller (with using a refrigerant low-temperature air cooler as the second stage of air cooling). The effect of air-cooling was assessed by comparing the increase in the production of mechanical energy as a result of an increase in the power of a gas turbine unit and fuel saved during the month of July for 2015-2018 in accumulating. Deeper air cooling at the inlet of the gas turbine unit to a temperature of 10 °C in a combined absorption-ejector chiller compared to its traditional cooling to 15 °C in an absorption bromine-lithium chiller provides a greater increase in net power and fuel saved. It is shown that due to a slight discrepancy between the results obtained for 2015-2018, a preliminary assessment of the efficiency of air cooling at the inlet of gas turbine plants can be carried out for one year.
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YAMASHITA, Seiji. "Profitability of Inlet Cooling Gas Turbine Co-Generation System". Proceedings of the National Symposium on Power and Energy Systems 2004.9 (2004): 461–64. http://dx.doi.org/10.1299/jsmepes.2004.9.461.
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Bartela, Łukasz y Janusz Kotowicz. "Analysis of operation of the gas turbine in a poligeneration combined cycle". Archives of Thermodynamics 34, n.º 4 (1 de diciembre de 2013): 137–59. http://dx.doi.org/10.2478/aoter-2013-0034.
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Abstract In the paper the results of analysis of an integrated gasification combined cycle IGCC polygeneration system, of which the task is to produce both electricity and synthesis gas, are shown. Assuming the structure of the system and the power rating of a combined cycle, the consumption of the synthesis gas for chemical production makes it necessary to supplement the lack of synthesis gas used for electricity production with the natural gas. As a result a change of the composition of the fuel gas supplied to the gas turbine occurs. In the paper the influence of the change of gas composition on the gas turbine characteristics is shown. In the calculations of the gas turbine the own computational algorithm was used. During the study the influence of the change of composition of gaseous fuel on the characteristic quantities was examined. The calculations were realized for different cases of cooling of the gas turbine expander’s blades (constant cooling air mass flow, constant cooling air index, constant temperature of blade material). Subsequently, the influence of the degree of integration of the gas turbine with the air separation unit on the main characteristics was analyzed.
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Gregory, Brent A. y Oleg Moroz. "Gas Turbine Cooling Flows and Their Influence in Output". Mechanical Engineering 137, n.º 03 (1 de marzo de 2015): 48–54. http://dx.doi.org/10.1115/1.2015-mar-4.
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This article presents the importance of understanding cooling flow monitoring especially when applied to land-based gas turbines. Cooling flows are necessary for the engine to function; however, too much cooling has a negative impact on the performance and output. Strategically placed instrumentation in the cooling flow delivery system can monitor the health and hence the output of the gas turbine generator utilized in a simple or combined cycle operation. In order to monitor cooling flows, a good approach is to look at disc cavity temperatures as well as bypass valve positions. It is best to trend both bypass valve position and disc cavity temperatures over a range of temperatures and engine load operation to get a better idea if the orifice plates in the main lines are sized properly. A quick way to determine whether there are cooling issues in an engine or not is to trend disc cavity temperature and bypass valve positions {AQ: Edits have been made in this sentence “A quick…valve positions.” for better readability. Please check and correct if necessary.}
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Радченко, Андрій Миколайович, Микола Іванович Радченко, Богдан Сергійович Портной, Сергій Анатолійович Кантор y Олександр Ігорович Прядко. "ВИКОРИСТАННЯ НАДЛИШКУ ХОЛОДОПРОДУКТИВНОСТІ ХОЛОДИЛЬНИХ МАШИН ПРИ ОХОЛОДЖЕННІ ПОВІТРЯ НА ВХОДІ ГТУ". Aerospace technic and technology, n.º 5 (29 de agosto de 2020): 47–52. http://dx.doi.org/10.32620/aktt.2020.5.06.
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The processes of the gas turbine inlet air cooling by exhaust heat conversion chillers, which utilizing the gas turbine exhaust gas heat, converting it into cold were analyzed. The use of two-stage air cooling has been investigated: to a temperature of 15°C – in an absorption lithium-bromide chiller and below to a temperature of 10°C – in an ejector chiller as stages of a two-stage absorption-ejector chiller. To simulate air cooling processes, the program "Guentner Product Calculator", one of the leading manufacturers of heat exchangers "Guentner", was used. The possibility of using the accumulated excess refrigeration capacity of a combined absorption-ejector chiller, which is formed at reduced current heat loads on air coolers at the gas turbine inlet, to cover the refrigeration capacity deficit arising at increased heat loads due to high ambient air temperatures has been investigated. The refrigeration capacity required to the gas turbine inlet air cooling was compared to an excess refrigeration capacity which excess of the current heat load. The considered air cooling system provides pre-cooling of air at the gas turbine inlet by using the excess refrigeration capacity of the absorption-ejector chiller, accumulated in the cold accumulator, to provide the required refrigeration capacity of the air pre-cooling booster stage. The simulation results proved the expediency of the gas turbine inlet air cooling using the accumulated excess refrigeration capacity of the combined absorption-ejector chiller. The proposed solution reduces by about 50% the design refrigeration capacity and, accordingly, the cost of the installed absorption lithium-bromide chiller, which acts as a high-temperature stage for cooling the ambient air at the gas turbine inlet.
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Takeishi, Kenichiro. "Evolution of Turbine Cooled Vanes and Blades Applied for Large Industrial Gas Turbines and Its Trend toward Carbon Neutrality". Energies 15, n.º 23 (25 de noviembre de 2022): 8935. http://dx.doi.org/10.3390/en15238935.
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Photovoltaics and wind power are expected to account for a large share of power generation in the carbon-neutral era. A gas turbine combined cycle (GTCC) with an industrial gas turbine as the main engine has the ability to rapidly start up and can follow up to load fluctuations to smooth out fluctuations in power generation from renewable energy sources. Simultaneously, the system must be more efficient than today’s state-of-the-art GTCCs because it will use either Carbon dioxide Capture and Storage (CCS) when burning natural gas or hydrogen/ammonia as fuel, which is more expensive than natural gas. This paper describes the trend of cooled turbine rotor blades used in large industrial gas turbines that are carbon neutral. First, the evolution of cooled turbine stationary vanes and rotor blades is traced. Then, the current status of heat transfer technology, blade material technology, and thermal barrier coating technology that will lead to the realization of future ultra-high-temperature industrial gas turbines is surveyed. Based on these technologies, this paper introduces turbine vane and blade cooling technologies applicable to ultra-high-temperature industrial gas turbines for GTCC in the carbon-neutral era.
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Sun, Dan Dan, Cheng Yang y Fei Zeng. "Study on Gas Turbine-Based CCHP System with Multi-Objective Evaluation Index". Advanced Materials Research 860-863 (diciembre de 2013): 1366–69. http://dx.doi.org/10.4028/www.scientific.net/amr.860-863.1366.
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Currently, there are many evaluation indexes for gas turbine-based combined cooling, heating and power （CCHP）. In this paper, a multi-objective evaluation index (MEI) model was suggested and weight coefficients were considered in the model. The CCHP system evaluated in this study was composed of gas turbine + heat recovery steam generator (HRSG ) + LiBr absorption chiller. The gas turbine-based CCHP system was evaluated and the component capacity was optimized with the proposed MEI. The study provides a reference for the allocation and operation of gas turbine-based CCHP.
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Fukuda, Masafumi, Hiroshi Harada, Tadaharu Yokokawa y Tomonori Kitashima. "Virtual Jet Engine System". Materials Science Forum 638-642 (enero de 2010): 2239–44. http://dx.doi.org/10.4028/www.scientific.net/msf.638-642.2239.
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In 1999, we proposed the concept of a virtual gas turbine system which is a combination of turbine design and material design programs. Using this system, it has become possible to design a gas turbine engine and a combined cycle automatically, by inputting some basic information such as power output, turbine inlet temperature and material specifications. The derived outputs are turbine gas path dimensions, gas and cooling air flow rates, thermal efficiency, CO2 emissions, etc. We use the system to evaluate the potential improvement if a newly developed material is to be used in building the engine. Based on the virtual gas turbine system we have begun developing the virtual jet engine system, which can simulate the operation of a jet engine or a gas turbine engine to predict the degradation of materials used in the high temperature parts of the engine. The system consists of a thermal and aerodynamic analysis of the engine, a thermal and stress analysis of hot parts, and a material degradation analysis. Actual engine dimensions, operation data and material specifications are used to perform the analyses. In this paper, we will show some of the results of the use of the virtual gas turbine system, and then describe the development plan and the preliminary output of the virtual jet engine system.
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Takematsu, Toshi'ichi. "Coal Gasification for Integrated Gasification Combined Cycle Power Generation". Energy Exploration & Exploitation 6, n.º 6 (diciembre de 1988): 437–46. http://dx.doi.org/10.1177/014459878800600604.
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A number of coal gasifiers applicable to IGCC are under development or at the demonstration stage. These include moving bed, fluidised bed, entrained flow and molten bath types. The efficiency of an IGCC system increases as the temperature of the gas entering the turbine increases. Practical temperatures are currently limited by turbine blade materials and by the system used to clean the gas prior to entering the turbine. Work on hot gas cleaning systems, turbine blade materials and blade cooling techniques are under way. The main requirements of the gasification system are to provide a high temperature, high pressure gas with a minimum of impurities.
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Basati Panah, Mehdi, Viktor A. Rassokhin, Viktor V. Barskov, Egor I. Okunev, Mikhail A. Laptev, Nikolai N. Kortikov, Van Chung Chu y Bowen Gong. "Influence of cooling of high temperature vane systems on efficiency gas turbine units regarding working substance specific heat capacity dependence on temperature". Izvestiya MGTU MAMI 16, n.º 2 (18 de enero de 2023): 115–24. http://dx.doi.org/10.17816/2074-0530-106231.
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BACKGROUND: Gas turbine units (GTU) are widely used in power plants, shipbuilding, aerospace and other industry sectors. Main performance indicators of units are effective cycle efficiency and useful internal power. It is known that gas turbine power grows on 1525% for each 100C of turbine inlet temperature increases in range of 10001400 K, which makes it possible to save fuel significantly. Further growth of turbine inlet temperature demands more drastic increase of cooling air flow rate for the sake of cooling of the GTU flow channel, that leads to decrease of effective efficiency of a GTU. Consequently, the research of cooling and heat capacity properties influence needs to be done in order to improve gas turbine unit performance in the turbine inlet temperature range of 10001400 K.
AIMS: Issues of influence of cooling of high temperature GTUs as well as issues of influence of working substance specific heat capacity dependence on temperature are studied in the article.
METHODS: The study contains comparative analysis of four gas turbine units (GTU) such as: the 3,13 MW Teeda GTU (Iran), the 4,13 MW UEC Perm Engines GTU-4P (Russia), the 5,1 MW Siemens SGT-100 (Germany) and the 5,67 MW Solar Turbines TAURUS 60 (USA).
RESULTS: As a result, dependencies of efficiency, specific effective work and GTU useful work coefficient on cooling were obtained. Working substance specific heat capacity dependence on temperature was considered in order to increase accuracy of calculations.
CONCLUSIONS: The completed calculation study allows judging on perfection of the heat layout of GTU, the flow channel of GTU and making a comparison of them for the sake of further optimization of operational processes.
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Радченко, Андрій Миколайович, Богдан Сергійович Портной, Сергій Анатолійович Кантор, Олександр Ігорович Прядко y Іван Володимирович Калініченко. "ПІДВИЩЕННЯ ЕФЕКТИВНОСТІ ОХОЛОДЖЕННЯ ПОВІТРЯ НА ВХОДІ ГТД ХОЛОДИЛЬНИМИ МАШИНАМИ ШЛЯХОМ АКУМУЛЯЦІЇ ХОЛОДУ". Aerospace technic and technology, n.º 4 (28 de agosto de 2020): 22–27. http://dx.doi.org/10.32620/aktt.2020.4.03.
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The efficiency of air cooling at the inlet of gas turbine engines by exhaust heat conversion chiller, which transforms the GTE exhaust gases heat into cold, under variable climatic operating conditions, has been investigated. Considered is the use of a combined absorption-ejector exhaust heat conversion chiller with a step-by-step principle of air cooling at the gas turbine engines inlet: preliminary down to 15°C – by an absorption lithium-bromide chiller (ACh), which is used as a high-temperature air cooling stage, and further cooling down to 10°C – by a refrigerant ejector chiller (ECh) as a low-temperature cooling stage. Reserves have been identified for reducing the design (installed) refrigeration capacity of chillers by accumulating excess cold at reduced current heat loads with its use at increased heat loads. In this case, the design (installed) refrigeration capacity of chillers was determined by two methods: the first – based on the close to the maximum reduction in annual fuel consumption, the second – according to the maximum rate of increase in the reduction in annual fuel consumption. A scheme of the air cooling system at the gas turbine engines inlet using the refrigeration capacity reserve of the ACh, which provides preliminary cooling of the ambient air at the gas turbine engines inlet, in the booster stage, using the ACh accumulated excess refrigeration capacity has been proposed. The ACh excess refrigerating capacity, which is formed at decreased heat loads on the air coolers at the gas turbine engines inlet, is accumulated in the cold accumulator and is used at increased heat loads. The simulation results show the advisability of using the air cooling system at the gas turbine engine inlet with using the ACh accumulated excess refrigeration capacity, which allows reducing the ACh design (installed) refrigeration capacity by approximately 40%.
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Радченко, Роман Миколайович, Богдан Сергійович Портной, Сергій Анатолійович Кантор, Веніамін Сергійович Ткаченко y Анатолій Анатолійович Зубарєв. "ОТРИМАННЯ І ВИКОРИСТАННЯ КОНДЕНСАТУ ПРИ ОХОЛОДЖЕННІ ПОВІТРЯ НА ВХОДІ ЕНЕРГОУСТАНОВКИ ТА ПРОБЛЕМА СЕПАРАЦІЇ КРАПЕЛЬНОЇ ВОЛОГИ З АЕРОЗОЛЬНОЇ СУМІШІ В ГРАДИРНЯХ". Aerospace technic and technology, n.º 5 (8 de noviembre de 2018): 23–27. http://dx.doi.org/10.32620/aktt.2018.5.04.
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The processes of heat-humidity treatment (cooling with dehumidification) of air in a two-stage air cooling system at the inlet of a gas turbine unit applying a combined type heat-energized refrigeration mechanism, which consists of an absorption lithium-bromide high-temperature refrigeration mechanism to approximately 15 °C and a refrigerant ejector low-temperature refrigeration mechanism to 10 °С and below, which transform the heat of exhaust gases from gas turbine unit to the cold with the production of condensate in air cooling system as a by-product of air cooling has been analyzed. The analysis was carried out for the climatic conditions of the south of Ukraine. The heat removal from the condensers and the absorber of the heat-energized refrigeration mechanism are carried out with open wet cooling towers. Based on the distribution of the heat load on the steps of the two-stage air cooling system and the heat coefficients of the heat-energized refrigeration mechanisms, the project load on the cooling towers was determined and their number was selected. Based on the results of modeling of the operation of the air cooling system at the inlet of the gas turbine unit, were obtained data from the current and total amount of condensate that falls in the air cooling system during the condensation of water vapor, which is always contained in moist air, as well as the amount of water needed to feed an open cooling tower. In this case, only water losses due to mechanical removal (without taking into account its evaporation in cooling towers) were considered, which poses the problem of separation of droplet moisture from the aerosol mixture. As a result of comparing the amount of water needed to feed the cooling towers, on the one hand, and the amount of condensate obtained in the process of air cooling at the inlet of the gas turbine unit, on the other hand, was demonstrated that it is possible to partially satisfy the necessary water needs for cooling towers. A scheme of two-stage air cooling system at the inlet of a gas turbine unit with absorption lithium-bromide and refrigerant ejector refrigeration mechanism and wet cooling towers is proposed, to discharge heat from heat-energized refrigeration mechanisms, to produce condensate as a by-product of air cooling, and apply it to feed cooling towers
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Li, Tianyi, Yanmei Liu y Zhen Chen. "Application of Sine Cosine Egret Swarm Optimization Algorithm in Gas Turbine Cooling System". Systems 10, n.º 6 (30 de octubre de 2022): 201. http://dx.doi.org/10.3390/systems10060201.
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Gas turbine cooling system is a typical multivariable, strongly coupled, nonlinear, and uncertain MIMO system. In order to solve the control problem of pressure, flow, and temperature of the system, an intelligent approach is necessary and more appropriate. The current system control mainly depends on the experience of the staff, which exists problems such as high labor intensity, low work efficiency and low control accuracy. Lack of accurate models make parameters tune difficultly, and ordinary control methods are difficult to control complex gas turbine cooling system. In this paper, the system transfer function model is built based on the field data obtained under different working conditions and system identification method. The diagonal matrix decoupling method is used to weaken the correlation between variables and achieve independent control among variables. When optimizing the parameters of the controller, Sine Cosine Egret Swarm Optimization Algorithm is proposed. Egret Swarm Optimization Algorithm is composed of Sit-And-Wait strategy, random walk, and encirclement strategy. The sit-and-wait strategy is prone to premature convergence, which makes the optimized parameters unsuitable for gas turbine cooling system. Sine Cosine Algorithm is introduced to randomly use the sine-cosine function for the pseudo-gradient of the weights of the observation equation, thus expanding the search range of the population. Friedman tests prove that the deviation of SE-ESOA is within the allowable range. The results show that the result of Sine Cosine Egret Swarm Optimization Algorithm is more stable and accurate, and it is more suitable for gas turbine cooling system, which solve the pressure, flow, and temperature control problems of complex systems.
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Kizuka, N., K. Sagae, S. Anzai, S. Marushima, T. Ikeguchi y K. Kawaike. "Conceptual Design of the Cooling System for 1700°C-Class, Hydrogen-Fueled Combustion Gas Turbines". Journal of Engineering for Gas Turbines and Power 121, n.º 1 (1 de enero de 1999): 108–15. http://dx.doi.org/10.1115/1.2816296.
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The effects of three types of cooling systems on the calculated operating performances of a hydrogen-fueled thermal power plant with a 1,700°C-class gas turbine were studied with the goal of attaining a thermal efficiency of greater than 60 percent. The combination of a closed-circuit water cooling system for the nozzle blades and a steam cooling system for the rotor blades was found to be the most efficient, since it eliminated the penalties of a conventional open-circuit cooling system which ejects coolant into the main hot gas stream. Based on the results, the water cooled, first-stage nozzle blade and the steam cooled first-stage rotor blade were designed. The former features array of circular cooling holes close to the surface and uses a copper alloy taking advantage of recent coating technologies such as thermal barrier coatings (TBCs) and metal coatings to decrease the temperature and protect the blade core material. The later has cooling by serpentine cooling passages with V-shaped staggered turbulence promoter ribs which intensify the internal cooling.
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Gritsch, Michael, Achmed Schulz y Sigmar Wittig. "Effect of Internal Coolant Crossflow on the Effectiveness of Shaped Film-Cooling Holes". Journal of Turbomachinery 125, n.º 3 (1 de julio de 2003): 547–54. http://dx.doi.org/10.1115/1.1580523.
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Film-cooling was the subject of numerous studies during the past decades. However, the effect of flow conditions on the entry side of the film-cooling hole on film-cooling performance has surprisingly not received much attention. A stagnant plenum which is widely used in experimental and numerical studies to feed the holes is not necessarily a right means to re-present real engine conditions. For this reason, the present paper reports on an experimental study investigating the effect of a coolant crossflow feeding the holes that is oriented perpendicular to the hot gas flow direction to model a flow situation that is, for instance, of common use in modern turbine blades’ cooling schemes. A comprehensive set of experiments was performed to evaluate the effect of perpendicular coolant supply direction on film-cooling effectiveness over a wide range of blowing ratios (M=0.5…2.0) and coolant crossflow Mach numbers Mac=0…0.6. The coolant-to-hot gas density ratio, however, was kept constant at 1.85 which can be assumed to be representative for typical gas turbine applications. Three different hole geometries, including a cylindrical hole as well as two holes with expanded exits, were considered. Particularly, two-dimensional distributions of local film-cooling effectiveness acquired by means of an infrared camera system were used to give detailed insight into the governing flow phenomena. The results of the present investigation show that there is a profound effect of how the coolant is supplied to the hole on the film-cooling performance in the near hole region. Therefore, crossflow at the hole entry side has be taken into account when modeling film-cooling schemes of turbine bladings.
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Радченко, Андрій Миколайович, Євген Іванович Трушляков, Сергій Анатолійович Кантор y Богдан Сергійович Портной. "ВИЗНАЧЕННЯ РАЦІОНАЛЬНОГО ТЕПЛОВОГО НАВАНТАЖЕННЯ ГРАДИРЕНЬ ВІДВЕДЕННЯ ТЕПЛОТИ У ПРОЦЕСАХ КОНДИЦІЮВАННЯ ПОВІТРЯ НА ВХОДІ ЕНЕРГОУСТАНОВОК". Aerospace technic and technology, n.º 5 (8 de noviembre de 2018): 19–22. http://dx.doi.org/10.32620/aktt.2018.5.03.
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The air conditioning processes (heat-humidity treatment) at the inlet of energy units by heat-energized refrigeration mechanisms with heat removal cooling towers of the cooling system are studied on the example of a gas turbine unit. Two-stage air cooling is considered applying a two-stage combined type heat-energized refrigeration mechanism, which applies the exhaust gas heat of a gas turbine unit and which includes absorption lithium-bromide and refrigerant ejector refrigeration mechanism as steps to convert waste heat into cold. Based on the results of modeling the operation of the cooling complex of a gas turbine unit, data was obtained on current heat loads on heat-energized refrigeration mechanisms and cooling towers in accordance with the climatic conditions of operation with different distribution of project heat loads on the air cooling stages and, accordingly, on the transformation of waste heat into cold. Due to the fact that the heat load on the cooling towers depends on the efficiency of transformation of waste heat into cold (heat coefficients) by absorption lithium-bromide and refrigerant ejector refrigeration mechanisms, a rational distribution of the project heat loads to the absorption and ejector stages of a combined type heat-energized refrigeration mechanisms that provides reduce heat load on cooling towers. It is demonstrated that due to this approach to determining the rational heat load on the cooling towers of the cooling system, which consists of calculation the redistribution of heat load between the absorption lithium-bromide and refrigerant ejector cooling stages with different efficiency and transformation of waste heat (different heat coefficients) in accordance with current climate conditions, is possible to minimize the number of cooling with a corresponding reduction in capital expenditures on the air conditioning system at the inlet of gas turbine unit