Bibliographies thématiques / Gas Turbine Cooling System

Littérature scientifique sur le sujet « Gas Turbine Cooling System »

Auteur : Grafiati
Publié le 10 mars 2023

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Articles de revues sur le sujet "Gas Turbine Cooling System"

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Valenti, Michael. « Keeping it Cool ». Mechanical Engineering 123, no 08 (1 août 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., et G. A. Romakhova. « Thermodynamic Analysis of Air-Cooled Gas Turbine Plants ». Journal of Engineering for Gas Turbines and Power 123, no 2 (1 août 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, no 5 (3 mars 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, no 1 (1 avril 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 et Chul Ho Han. « Comparative Thermodynamic Analysis of Gas Turbine Systems with Turbine Blade Film Cooling ». Advanced Materials Research 505 (avril 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 et Ai Peng Jiang. « Measurement and Control of the Gas Turbine Inlet Air Cooling System ». Applied Mechanics and Materials 220-223 (novembre 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 et Hyung Jong Ko. « Effects of Wet Compression on Performance of Regenerative Gas Turbine Cycle with Turbine Blade Cooling ». Applied Mechanics and Materials 224 (novembre 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 et 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, no 5 (10 mai 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 et S. Karellas. « Inlet Air Cooling Methods for Gas Turbine Based Power Plants ». Journal of Engineering for Gas Turbines and Power 128, no 2 (23 septembre 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 et Feng Guo. « INVESTIGATION OF CONJUGATED HEAT TRANSFER FOR A RADIAL TURBINE WITH IMPINGEMENT COOLING ». Journal of Physics : Conference Series 2087, no 1 (1 novembre 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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Thèses sur le sujet "Gas Turbine Cooling System"

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Son, Changmin. « Gas turbine impingement cooling system studies ». Thesis, University of Oxford, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.670200.

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Luque, Martínez Salvador G. « A fully-integrated approach to gas turbine cooling system research ». Thesis, University of Oxford, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.558543.

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A novel experimental facility for the testing of modern high pressure nozzle guide vanes, the Annular Sector Heat Transfer Facility, is described in this thesis. Non- dimensionally similar conditions to a thermal paint test are reproduced, in a warm flow field, by the use of actual engine hardware, contoured sidewalls, and an innova- tive system of deswirl vanes in a five-passage annular sector cascade. External Mach and Reynolds numbers, inlet turbulence intensity, and coolant-to-mainstream pres- sure ratio are all matched to engine conditions. The test vanes are heavily cooled both internally (by convection and impingement) and externally (by film cooling). Detailed aerodynamic measurements are discussed, which demonstrate that a peri- odic, transonic, and highly engine-realistic flow is established in the cascade. High resolution full coverage maps of overall cooling effectiveness are presented, acquired on the vane surfaces at steady state conditions by wide-band liquid crys- tals and infrared thermography. Experimental measurements are then scaled to en- gine conditions by a new theoretical procedure, argued from first principles, which extends the principle of superposition to fully-cooled compressible flows. A newly- defined recovery temperature is proposed, which accounts for the redistribution of heat between the internal and external vane flows in a fully-integrated manner. This technique makes the results analogous to those of a thermal paint test, but allows for fundamental research and early and inexpensive cooling system validation. Overall cooling effectiveness measurements are complemented by those of the re- quired cooling flow capacity to achieve them, conducted in a second test rig commis- sioned during this research: the Flow Testing Facility. To conclude, the approach developed is applied to the global thermal assessment of the dendritic geometry, an innovative turbine cooling system. Experimental results show promising benefits over the baseline vane, especially in regions of low coolant-to-mainstream pressure margin.
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Gillespie, David R. H. « Intricate internal cooling systems for gas turbine blading ». Thesis, University of Oxford, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365831.

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Lameen, Tariq M. H. « Development of a photovoltaic reverse osmosis demineralization fogging for improved gas turbine generation output ». Thesis, Cape Peninsula University of Technology, 2018. http://hdl.handle.net/20.500.11838/2756.

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Thesis (Master of Engineering in Electrical Engineering)--Cape Peninsula University of Technology, 2018.
Gas turbines have achieved widespread popularity in industrial fields. This is due to the high power, reliability, high efficiency, and its use of cheap gas as fuel. However, a major draw-back of gas turbines is due to the strong function of ambient air temperature with its output power. With every degree rise in temperature, the power output drops between 0.54 and 0.9 percent. This loss in power poses a significant problem for utilities, power suppliers, and co-generations, especially during the hot seasons when electric power demand and ambient temperatures are high. One way to overcome this drop in output power is to cool the inlet air temperature. There are many different commercially available means to provide turbine inlet cooling. This disserta-tion reviews the various technologies of inlet air cooling with a comprehensive overview of the state-of-the-art of inlet fogging systems. In this technique, water vapour is being used for the cooling purposes. Therefore, the water quality requirements have been considered in this thesis. The fog water is generally demin-eralized through a process of Reverse Osmosis (RO). The drawback of fogging is that it re-quires large amounts of demineralized water. The challenge confronting operators using the fogging system in remote locations is the water scarcity or poor water quality availability. However, in isolated hot areas with high levels of radiation making use of solar PV energy to supply inlet cooling system power requirements is a sustainable approach. The proposed work herein is on the development of a photovoltaic (PV) application for driv-ing the fogging system. The design considered for improved generation of Acaica power plant in Cape Town, South Africa. In addition, this work intends to provide technical infor-mation and requirements of the fogging system design to achieve additional power output gains for the selected power plant.
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Chua, Khim Heng. « Experimental characterisation of the coolant film generated by various gas turbine combustor liner geometries ». Thesis, Loughborough University, 2005. https://dspace.lboro.ac.uk/2134/12704.

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In modern, low emission, gas turbine combustion systems the amount of air available for cooling of the flame tube liner is limited. This has led to the development of more complex cooling systems such as cooling tiles i.e. a double skin system, as opposed to the use of more conventional cooling slots i.e. a single skin system. An isothennal experimental facility has been constructed which can incorporate 10 times full size single and double skin (cooling tile) test specimens. The specimens can be tested with or without effusion cooling and measurements have been made to characterise the flow through each cooling system along with the velocity field and cooling effectiveness distributions that subsequently develop along the length of each test section. The velocity field of the coolant film has been defined using pneumatic probes, hot-wire anemometry and PIV instrumentation, whilst gas tracing technique is used to indicate (i) the adiabatic film cooling effectiveness and (ii) mixing of the coolant film with the mainstream flow. Tests have been undertaken both with a datum low turbulence mainstream flow passing over the test section, along with various configurations in which large magnitudes and scales of turbulence were present in the mainstream flow. These high turbulence test cases simulate some of the flow conditions found within a gas turbine combustor. Results are presented relating to a variety of operating conditions for both types of cooling system. The nominal operating condition for the double skin system was at a coolant to mainstream blowing ratio of approximately 1.0. At this condition, mixing of the mainstream and coolant film was relatively small with low mainstream turbulence. However, at high mainstream turbulence levels there was rapid penetration of the mainstream flow into the coolant film. This break up of the coolant film leads to a significant reduction in the cooling effectiveness. In addition to the time-averaged characteristics, the time dependent behaviour of the .:coolantfilm was. also investigated. In particular, unsteadiness associated with large scale structures in the mainstream flow was observed within the coolant film and adjacent to the tile surface. Relative to a double skin system the single skin geometry requires a higher coolant flow rate that, along with other geometrical changes, results in typically higher coolant to mainstream velocity ratios. At low mainstream turbulence levels this difference in velocity between the coolant and mainstream promotes the generation of turbulence and mixing between the streams so leading to some reduction in cooling effectiveness. However, this higher momentum coolant fluid is more resistant to high mainstream turbulence levels and scales so that the coolant film break up is not as significant under these conditions as that observed for the double skin system. For all the configurations tested the use of effusion cooling helped restore the coolant film along the rear of the test section. For the same total coolant flow, the minimum value of cooling effectiveness observed along the test section was increased relative to the no effusion case. In addition the effectiveness of the effusion patch depends on the amount of coolant injected and the axial location of the patch. The overall experimental data suggested the importance of the initial cooling film conditions together with better understanding of the possible mechanisms that results in the rapid cooling film break-up, such as high turbulence mainstream flow and scales, and this will lead to a more effective cooling system design. This experimental data is also thought to be ideal for the validation of numerical predictions.
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Roy, Rajkumar. « Adaptive search and the preliminary design of gas turbine blade cooling systems ». Thesis, University of Plymouth, 1997. http://hdl.handle.net/10026.1/2664.

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This research concerns the integration of Adaptive Search (AS) technique such as the Genetic Algorithms (GA) with knowledge based software to develop a research prototype of an Adaptive Search Manager (ASM). The developed approach allows to utilise both quantitative and qualitative information in engineering design decision making. A Fuzzy Expert System manipulates AS software within the design environment concerning the preliminary design of gas turbine blade cooling systems. Steady state cooling hole geometry models have been developed for the project in collaboration with Rolls Royce plc. The research prototype of ASM uses a hybrid of Adaptive Restricted Tournament Selection (ARTS) and Knowledge Based Hill Climbing (KBHC) to identify multiple "good" design solutions as potential design options. ARTS is a GA technique that is particularly suitable for real world problems having multiple sub-optima. KBHC uses information gathered during the ARTS search as well as information from the designer to perform a deterministic hill climbing. Finally, a local stochastic hill climbing fine tunes the "good" designs. Design solution sensitivity, design variable sensitivities and constraint sensitivities are calculated following Taguchi's methodology, which extracts sensitivity information with a very small number of model evaluations. Each potential design option is then qualitatively evaluated separately for manufacturability, choice of materials and some designer's special preferences using the knowledge of domain experts. In order to guarantee that the qualitative evaluation module can evaluate any design solution from the entire design space with a reasonably small number of rules, a novel knowledge representation technique is developed. The knowledge is first separated in three categories: inter-variable knowledge, intra-variable knowledge and heuristics. Inter-variable knowledge and intra-variable knowledge are then integrated using a concept of compromise. Information about the "good" design solutions is presented to the designer through a designer's interface for decision support.
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Kakade, Vinod. « Fluid Dynamic and Heat Transfer Measurements in Gas Turbine Pre-Swirl Cooling Systems ». Thesis, University of Bath, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.503370.

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Fransen, Rémy. « LES based aerothermal modeling of turbine blade cooling systems ». Phd thesis, Toulouse, INPT, 2013. http://oatao.univ-toulouse.fr/10012/1/fransen.pdf.

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This PhD dissertation, conducted as part of a CIFRE research project between TURBOMECA and CERFACS in partnership with the VKI, deals with improving performance of axial turbines from helicopter engines. One of the most critical design points of such engines is the control of the high pressure turbine blade lifetime which face the high temperatures from the combustor. Today, industrial numerical aerothermal predictions of the flows around the blade (in the vein and in its cooling system) are performed with the Reynolds Averaged Navier-Stokes (RANS). Thanks to the increasing computational power, Large Eddy Simulation (LES) becomes affordable to offer further flow predictions. Therefore, this thesis focuses on the capabilities of the LES to estimate the flow in turbine blade internal cooling channels. To simplify this analysis where several physical phenomenon are present, the problem is described in three parts with increasing complexity. The first part addresses simplified typical geometries of cooling channel (U-bend and ribbed channel) in a static configuration. Considering the flow regime, a wall-resolved approach using a hybrid unstructured mesh is proposed in view of the application on an industrial case. The second part extends the study of the ribbed channel in rotation using an inertial reference frame. LES provides mean and unsteady results in good agreement with the available experimental data and previous works, for the flow dynamic and the heat transfer. Finally, the third part presents the application of the method to an industrial case with conjugate heat transfer between a complex cooling channel and the blade. This last section is not present in the public manuscrit for confidential reasons. Results of the use of the wall-resolved approach in rotation in an inertial frame of reference are compared to RANS predictions and show the potential of the method with high local differences.
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Isaksson, Frida. « Pressure loss characterization for cooling and secondary air system components in gas turbines ». Thesis, Luleå tekniska universitet, Institutionen för teknikvetenskap och matematik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-64528.

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There is a constant struggle to increase the efficiency in gas turbines, where one method is to have a higher inlet temperature to the turbine. Often, this results in temperatures higher than the critical temperature of the materials, which makes cooling of the components an important part of the turbine. The cooling air is tapped from the compressor, and has hence required work while being compressed, but since it is removed from the thermodynamic cycle it will not provide any work in the turbine stages. Therefore, it is important to understand the losses in the cooling system to be able to use the smallest amount of cooling air possible, while still cool sufficiently to not decrease the turbine’s lifetime. The pressure losses in the cooling and secondary air systems are due to either friction or minor losses; contractions, expansions and bends. The losses can be described by a discharge coefficient, ; a rate of how close the actual mass flow is to the ideal mass flow, or a pressure loss coefficient, ; a rate of the pressure drop. In the cooling and secondary air systems there are orifices and cooling geometries. These can have different geometrical properties depending on application, and thereby have different heat transfer performances and causing a higher or lower pressure drop. At Siemens Industrial Turbomachinery AB, SIT AB, a one-dimensional in-house program named C3D is used for thermal calculations and calculations of flow properties of internal cooling flow networks. The program uses hydraulic networks consisting of nodes and branches to simulate the flow inside the components. Correlations used for describing pressure losses have been collected and divided depending on their valid ranges, with the aim to make pressure loss calculations easier. A MATLAB code have been developed, which, depending on input parameters, separates the correlations and returns a plot with the correlations that can be used. In order to make the code as useful as possible, a few assumptions were made; curve fitting of correlations which were only available as plots and interpolation to get larger valid ranges for some cases. These assumptions will influence the results, but the code will still be able to give an indication of which correlation to use, and hence, the objective is fulfilled. Simulations in one dimension are commonly used, since it is less time consuming than three-dimensional modelling. Therefore, with focus on the pressure losses, a one-dimensional model of a blade in the in-house program C3D has been evaluated using a three-dimensional model in the CFD program Ansys CFX. Also, two new models were created in C3D; both with geometrical properties and pressure loss coefficients adjusted to the CFX model, but the first model is using the same hydraulic network as in the evaluated, reference, model while the second is using a new network, built according to the streamlines in CFX. The resulting mass flows in the C3D models were compared to the mass flows in the CFX model, which ended in the conclusion that it is hard for the one-dimensional models to understand the complex, three-dimensional flow situations, even when adjusting them to the CFX model. Anyhow, the adjustments made the model somewhat closer to the three-dimensional case, and hence CFX should be used in an earlier stage when developing C3D models.
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A'Barrow, Chris. « Aerodynamic design of the coolant delivery system for an intercooled aero gas turbine engine ». Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/13539.

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The Advisory Council of Aeronautical Research in Europe (ACARE) has set record emission reduction targets for 2020, in response to increased awareness of global warming issues and the forecast high level of growth in global air traffic. In order to meet this legislation engine designers have to consider new and unconventional designs. An intercooled aero-engine with a heat exchanger (HX) positioned between the IP and HP compressors has the potential to reduce emissions and/or reduce specific fuel consumption relative to conventional engine cycles. In such an engine a coolant delivery system is required to bleed a proportion of the bypass flow, from behind the fan outlet guide vane (FOGV), rapidly diffuse the flow (to reduce pressure loss through the HX modules) and present it to the intercooler (i.e. heat exchanger) modules for cooling. This spent cooling air is then fed back into the bypass duct. To realise the benefits of the intercooled cycle the coolant delivery system must diffuse the flow, within the geometrical constraints, with minimal pressure loss and present it to the heat exchanger modules with suitable flow characteristics over a range of operating conditions. Therefore, a predominately experimental study, complemented with CFD predictions, was undertaken to investigate the design and performance of a coolant delivery system aimed at providing high pressure recovery in a relatively short length. For this to be achieved some pre-diffusion of the flow is required upstream of the offtake (i.e. by making the offtake larger than the captured streamtube), with a controlled diffuser or hybrid diffuser arrangement located downstream of the offtake. Although targeted at an intercooled aero-engine the concept of a system that produces a high pressure recovery in a limited length is applicable to a variety of applications. Experimental data were obtained on a modified existing low speed isothermal annular test facility operating at nominally atmospheric conditions. The offtake must operate aft of the FOGV in a highly complex flow field environment. Hence, a 1½ stage axial flow compressor (IGV, rotor and modified OGV) was used to simulate the unsteady blade wakes, secondary flows, loss cores and other turbo-machinery features that can significantly influence offtake performance. Preliminary numerical (CFD) studies enabled an offtake configuration to be determined and provided understanding of the governing fluid mechanic processes. A relatively small scale, low speed test facility was designed that had the capability to evaluate aerodynamic processes in isolation (i.e. pre-diffusion, controlled diffusion, hybrid diffusion) and full system modelling to enable the complex interaction between these flow processes to be assessed. Hence an optimal system could be characterised in terms of total pressure loss, static pressure recovery and flow profiles at HX inlet. Measurements and numerical predictions are initially presented for a baseline configuration with no offtake present. This enabled the OGV near field region to be characterised and provided a datum, relative to which the effects of introducing an offtake could be assessed. The results showed that in the near field region (i.e. within one chord downstream of the FOGV) the high velocity gradients in the circumferential direction, and associated turbulent shear stresses, dominate the profile mixing and loss production. There is little mixing out of profiles in the radial direction. Furthermore, the relatively large amount of kinetic energy associated with the compressor efflux and its subsequent mixing to a more uniform profile (i.e. reduced blockage) results in a significant static pressure recovery (Cp=5.5%). With the offtake present a variety of configurations were investigated including different levels of pre-diffusion, prior to the offtake, and different offtake positions. This enabled evaluation of the upstream pressure effects and interaction with the upstream FOGV. For very compact systems of short length, such that the gap between the OGV and offtake is relatively small, the amount of pre-diffusion achievable is limited by the offtake pressure field and its impact on the upstream OGV row. This pressure field is also influenced by parameters such as the non-dimensional offtake height and splitter thickness. For systems of increased length a significant amount of flow pre-diffusion can be achieved with little performance penalty (relative to the datum configuration). Hence, the loss associated with mixing blade wakes and secondary flows in an adverse pressure gradient is relatively small. However, the pre-diffusion level is eventually limited, to approximately 1.5, by the increased distortion and pressure losses associated with the captured streamtube. Further measurements were made with various controlled diffuser and hybrid diffusers (of varying area ratio) downstream of the offtake and various levels of pre-diffusion. The flow profile that is presented to the controlled diffuser is directly influenced by the upstream pre-diffusion process. Hence, in this case the upstream-downstream interaction is relatively strong. Conversely, the downstream-upstream interaction, between the controlled diffuser and pre-diffusion process, is relatively weak and thus has little effect on the upstream flow field. The data enabled an optimal system to be characterised (pre-diffusion/controlled diffusion split) in terms of total pressure loss, static pressure recovery and flow profiles at HX inlet. A total system diffusion of 1.8 was achievable with a pre-diffusion of 1.4 and controlled diffusion of 1.25, with further increases in either the pre-diffusion level or the controlled diffuser area ratio destabilising the system. This was achieved with an absolute mass weighted total pressure loss of 11% measured from FOGV inlet to the controlled diffuser exit plane. Utilising a hybrid bled diffuser, combined with the pre-diffusion, enabled a total system diffusion of 2.24 to be achieved. The system incorporated a 6% bleed from the hybrid diffuser and a system total pressure loss of 13%. Experimental and computational results obtained in the current research have provided an understanding of the governing flow mechanisms and quantified the geometric and aerodynamic interaction of the offtake with the FOGV and between the diffusion processes. This has enabled a design methodology to be outlined that provides approximate information on system geometry and performance (in terms of optimal diffusion split and total pressure loss) for future coolant delivery systems with minimal effort. Preliminary design maps have been developed to define the magnitude of the interaction between the offtake and FOGV in terms of the offtake height, pre-diffusion level, the splitter thickness and the axial distance between the fan OGV and offtake. In this way systems of optimal diffusion split, minimum pressure loss and minimal axial length can be determined.
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Livres sur le sujet "Gas Turbine Cooling System"

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Stewart, William E. Design guide : Combustion turbine inlet air cooling systems. Atlanta, Ga : American Society of Heating, Refrigerating and Air-Conditioning Engineers, 1999.

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Ghodke, Chaitanya D. Gas Turbine Blade Cooling. Warrendale, PA : SAE International, 2018. http://dx.doi.org/10.4271/0768095069.

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Ghodke, Chaitanya. Gas Turbine Blade Cooling. Warrendale, PA : SAE International, 2018. http://dx.doi.org/10.4271/pt-196.

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Sandīpa, Datta, et Ekkad Srinath 1958-, dir. Gas turbine heat transfer and cooling technology. 2e éd. Boca Raton, FL : Taylor & Francis, 2012.

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1953-, Dutta Sandip, et Ekkad Srinath 1958-, dir. Gas turbine heat transfer and cooling technology. New York : Taylor & Francis, 2000.

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Naval Education and Training Program Management Support Activity (U.S.), dir. Gas turbine system technician (electrical) 3 & 2. [Pensacola, Fla.] : The Activity, 1988.

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Gonser, Robert W. Gas turbine system technician (electrical) 3 & 2. [Pensacola, Fla.] : The Activity, 1988.

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Ahern, John J. Gas turbine system technician (mechanical) 3 & 2. [Pensacola, Fla.] : The Center, 1985.

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Al-Khusaibi, T. M. S. Gas turbine models for power system analysis. Manchester : UMIST, 1993.

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Ahern, John J. Gas turbine system technician (mechanical) 3 & 2. Pensacola, Fla : The Activity, 1987.

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Chapitres de livres sur le sujet "Gas Turbine Cooling System"

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Radchenko, Andrii, Lukasz Bohdal, Yang Zongming, Bohdan Portnoi et Veniamin Tkachenko. « Rational Designing of Gas Turbine Inlet Air Cooling System ». Dans Lecture Notes in Mechanical Engineering, 591–99. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-40724-7_60.

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Lytvynenko, Oksana, Oleksandr Tarasov, Iryna Mykhailova et Olena Avdieieva. « Possibility of Using Liquid-Metals for Gas Turbine Cooling System ». Dans Advances in Design, Simulation and Manufacturing III, 312–21. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-50491-5_30.

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Konovalov, Dmytro, Halina Kobalava, Mykola Radchenko, Viktor Gorbov et Ivan Kalinichenko. « Development of the Gas-Dynamic Cooling System for Gas Turbine Over-Expansion Circuit ». Dans Lecture Notes in Mechanical Engineering, 249–58. Cham : Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-06044-1_24.

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Mert, Mehmet Selçuk, Mehmet Direk, Ümit Ünver, Fikret Yüksel et Mehmet İsmailoğlu. « Exergetic Analysis of a Gas Turbine with Inlet Air Cooling System ». Dans Exergy for A Better Environment and Improved Sustainability 1, 1101–14. Cham : Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-62572-0_70.

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Ünver, Ümit, Mehmet Selçuk Mert, Mehmet Direk, Fikret Yüksel et Muhsin Kılıç. « Design of an Inlet Air-Cooling System for a Gas Turbine Power Plant ». Dans Exergy for A Better Environment and Improved Sustainability 1, 1089–100. Cham : Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-62572-0_69.

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Cho, Hyung Hee, Kyung Min Kim, Sangwoo Shin, Beom Seok Kim et Dong Hyun Lee. « Multi-Scale Thermal Measurement and Design of Cooling Systems in Gas Turbine ». Dans Fluid Machinery and Fluid Mechanics, 8–13. Berlin, Heidelberg : Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-89749-1_2.

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Firmansyah, Iman, et Prabowo. « The Effect of Inlet Air Cooling to Power Output Enhancement of Gas Turbine ». Dans Recent Advances in Renewable Energy Systems, 241–48. Singapore : Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1581-9_27.

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Talukdar, Kamaljyoti. « Use of Gas Turbine Operated by Municipal Solid Waste to Obtain Power and Cooling Assisted by Vapour Absorption Refrigeration System ». Dans Integrated Approaches Towards Solid Waste Management, 79–85. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-70463-6_8.

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Schobeiri, Meinhard T. « Gas Turbine Thermodynamic Process ». Dans Gas Turbine Design, Components and System Design Integration, 31–47. Cham : Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_2.

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Schobeiri, Meinhard T. « Gas Turbine Thermodynamic Process ». Dans Gas Turbine Design, Components and System Design Integration, 33–49. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_2.

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Actes de conférences sur le sujet "Gas Turbine Cooling System"

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Khodak, Evgeni A., et Gallna A. Romakhova. « Gas Turbine Model With Intensive Cooling ». Dans ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-464.

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A method of calculation of cooled gas turbine parameters is proposed. The method is based on the solution of the expansion process equation, heat transfer equations for cooled elements and on the results of the statistic processing of the parameters. The method is valid for the turbine with any cooling system and gaseous heat carrier. Turbine output determination error does not exceed 0,5–1,0%. The method allows to obtain the characteristics of gas turbines and gas turbine units (GTU) with open and closed air and steam cooling systems and to carry out an efficiency analysis of their performance in power generating units of various structure.
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Tanaka, T., A. Ishikawa, K. Aoyama, K. Kishimoto, Y. Yoshida, K. Toda, M. Atsumi et H. Kawamura. « Gas Turbine Inlet Air Cooling System With Liquid Air ». Dans ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-449.

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Gas turbine performance, especially power output and efficiency, is strongly dependent on ambient air temperature. Gas Turbine Inlet Air Cooling (GTIAC) has the effect of enhancing gas turbine capacity during peak hours in summer season. This paper presents an unique GTIAC system with liquid air, which will produce and store liquid air during off peak periods and spray it directly into the compressor inlet during peak hours. In the summer of 1996, an experimental study using a 150MW base load gas turbine was successfully performed on Chita Power Station to prove this new GTIAC performance. Test results show that the new GTIAC has a big advantage of increasing gas turbine capacity flexibly and economically for peak demands or emergencies.
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Galitseisky, Boris M., A. V. Loburev et M. S. Cherny. « THE METHOD OPTIMIZATION OF GAS TURBINE BLADES COOLING SYSTEM ». Dans International Heat Transfer Conference 11. Connecticut : Begellhouse, 1998. http://dx.doi.org/10.1615/ihtc11.1270.

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Bunce, Richard H., Francisco Dovali-Solis et Robert W. Baxter. « Particulate Monitor for Gas Turbine Cooling Air ». Dans ASME Turbo Expo 2008 : Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51135.

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It is important to monitor the quality of the air used in the cooling system of a gas turbine engine. There can be many reasons that particulates smaller than the minimum size removed by typical engine air filters can enter the secondary air system piping in a gas turbine engine system. Siemens has developed a system that provide real time monitoring of particulate concentrations by adapting a commercial electrodynamic devise for use within the confines of the gas turbine secondary air system with provision for a grab sample option to collect samples for laboratory analysis. This on-line monitoring system is functional at typical engine cooling system piping operating pressure and temperature. The system is calibrated for detection of iron oxide particles in the 1 to 100 micrometer range at concentration of from 1 to 50 parts per million mass wet (ppmmw) The electro dynamic device is nominally operable at 800°C. The particulate monitoring system requires special mounting and antenna. This system may be adjusted for other materials, sizes and concentrations. The system and its developmental application are described. The system has been tested and test results are reviewed. The test application was the cooling air piping of a Siemens gas turbine engine. Multiple locations were monitored. The cooling system in this engine incorporates an air cooler and the particulate monitoring system was tested upstream and downstream of the air cooler for temperature contrast. The monitor itself is limited to the piping system and not the engine gas-path.
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Reichert, A. W., et M. Janssen. « Cooling and Sealing Air System in Industrial Gas Turbine Engines ». Dans ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-256.

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Siemens heavy duty Gas Turbines have been well known for their high power output combined with high efficiency and reliability for more than 3 decades. Offering state of the art technology at all times, the requirements concerning the cooling and sealing air system have increased with technological development over the years. In particular the increase of the turbine inlet temperature and reduced NOx requirements demand a highly efficient cooling and sealing air system. The new Vx4.3A family of Siemens gas turbines with ISO turbine inlet temperatures of 1190°C in the power range of 70 to 240 MW uses an effective film cooling technique for the turbine stages 1 and 2 to ensure the minimum cooling air requirement possible. In addition, the application of film cooling enables the cooling system to be simplified. For example, in the new gas turbine family no intercooler and no cooling air booster for the first turbine vane are needed. This paper deals with the internal air system of Siemens gas turbines which supplies cooling and sealing air. A general overview is given and some problems and their technical solutions are discussed. Furthermore a state of the art calculation system for the prediction of the thermodynamic states of the cooling and sealing air is introduced. The calculation system is based on the flow calculation package Flowmaster (Flowmaster International Ltd.), which has been modified for the requirements of the internal air system. The comparison of computational results with measurements give a good impression of the high accuracy of the calculation method used.
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Najar, F. A., et G. A. Harmain. « Novel Approach Towards Thrust Bearing Pad Cooling ». Dans ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8165.

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The present paper analyzes the thermal effect on a sector shaped pad extensively used in thrust bearings which supports the heavy axial loads. Large hydro-generator thrust bearings are susceptible to too much thermo-elastic deformation when oil film thickness is subjected to high pressure and temperature which can even lead to the bearing failure. So as a remedy, this study is an effort towards reducing the oil film temperature by incorporating a suitable cooling treatment. The cooling circuit, in this study, essentially follows a path of hot spots observed by solving Reynolds equation, energy equation and generalized Fourier heat conduction equation. The numerical scheme followed during investigation is finite difference method (FDM). The water circuit developed is just beneath the Babbitt lining of the pads. It has been observed that overall temperature has reduced significantly as compared to traditional cooling systems.
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Yamazaki, Hiroyuki, Yoshiaki Nishimura, Masahiro Abe, Kazumasa Takata, Satoshi Hada et Junichiro Masada. « Development of Next Generation Gas Turbine Combined Cycle System ». Dans ASME Turbo Expo 2016 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56322.

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Tohoku Electric Power Company, Inc. (Tohoku-EPCO) has been adopting cutting-edge gas turbines for gas turbine combined cycle (GTCC) power plants to contribute for reduction of energy consumption, and making a continuous effort to study the next generation gas turbines to further improve GTCC power plants efficiency and flexibility. Tohoku-EPCO and Mitsubishi Hitachi Power Systems, Ltd (MHPS) developed “forced air cooling system” as a brand-new combustor cooling system for the next generation GTCC system in a collaborative project. The forced air cooling system can be applied to gas turbines with a turbine inlet temperature (TIT) of 1600deg.C or more by controlling the cooling air temperature and the amount of cooling air. Recently, the forced air cooling system verification test has been completed successfully at a demonstration power plant located within MHPS Takasago Works (T-point). Since the forced air cooling system has been verified, the 1650deg.C class next generation GTCC power plant with the forced air cooling system is now being developed. Final confirmation test of 1650deg.C class next generation GTCC system will be carried out in 2020.
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Nilsson, Ulf E., Lars O. Lindqvist, Ingemar A. G. Eriksson et Jonas N. Hylén. « Experimental Investigation of GTX100 Combustor Liner Cooling System ». Dans ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-539.

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The liner cooling for GTX100’s annular combustor has been successfully tested. Because of high heat load at the flame attachment point, a good design is very important. The design presented here offers robustness and high performance, combined with no dilution. The cooling system is a turbulated convective design, which were experimentally investigated in a plastic (perspex) model of a full scale 60° sector of the combustor. The importance of a high performance liner cooling is obvious. This design generates low pressure drop, better combustion (circumferential even flow from the liner cooling) and it gives lower flame temperature (minimizes the emissions). The influence of disturbances on the cooling and burner performance is presented in this paper.
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Ebenhoch, G., et T. M. Speer. « Simulation of Cooling Systems in Gas Turbines ». Dans ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-049.

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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 modelled 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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Sharma, Meeta, et Onkar Singh. « Energy and Exergy Investigations Upon Tri-Generation Based Combined Cooling, Heating, and Power (CCHP) System for Community Applications ». Dans ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4559.

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The continually increasing demand for electricity, cooling and heating accompanied by depleting energy sources, makes it inevitable to use the technologies to harness the available resources to their maximum capacity. The tri-generation systems are the advanced and popular technological option for efficient, reliable, flexible, and less polluting alternatives to utilize the conventional energy resources in an optimal way. In this work, the energy available with conventional fuel is utilized along with solar energy collected through parabolic trough collectors which are integrated with steam injected gas turbine cycle for combined power, heating and cooling requirements. Here a thermodynamic model has been developed for the considered tri-generation combined cooling, heating, and power (CCHP) system and the detailed energy and exergy analysis is performed. The results obtained, by the thermodynamic modeling and analyses of CCHP system based on the first and second law of thermodynamics have been presented and conclusions are drawn from their analysis. This work provides the energy efficient solution for combined heating, cooling, and power for medium load in community usage which may require plant size in the range of 10–50 MW. However, the cost effectiveness depends on the relative cost of gas turbine fuel with respect to other alternate systems with alternate fuels.
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Rapports d'organisations sur le sujet "Gas Turbine Cooling System"

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Ames, Forrest Edward, et Sumanta Acharya. Thermally Effective and Efficient Cooling Technologies for Advanced Gas Turbine Systems. Office of Scientific and Technical Information (OSTI), décembre 2017. http://dx.doi.org/10.2172/1415043.

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Leylek, James H., D. K. Walters, William D. York, D. S. Holloway et Jeffrey D. Ferguson. Computational Film Cooling Methods for Gas Turbine Airfoils. Fort Belvoir, VA : Defense Technical Information Center, mars 2002. http://dx.doi.org/10.21236/ada400186.

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Coulthard, Sarah M. Effects of Pulsing on Film Cooling of Gas Turbine Airfoils. Fort Belvoir, VA : Defense Technical Information Center, mai 2005. http://dx.doi.org/10.21236/ada437128.

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Metz, Stephen D., et David L. Smith. Survey of Gas Turbine Control for Application to Marine Gas Turbine Propulsion System Control. Fort Belvoir, VA : Defense Technical Information Center, janvier 1989. http://dx.doi.org/10.21236/ada204713.

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Brown, D. R., S. Katipamula et J. H. Konynenbelt. A comparative assessment of alternative combustion turbine inlet air cooling system. Office of Scientific and Technical Information (OSTI), février 1996. http://dx.doi.org/10.2172/211362.

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Acharya, Sumanta. A 3D-PIV System for Gas Turbine Applications. Fort Belvoir, VA : Defense Technical Information Center, août 2002. http://dx.doi.org/10.21236/ada406716.

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LeCren, R., L. Cowell, M. Galica, M. Stephenson et C. Wen. Advanced coal-fueled industrial cogeneration gas turbine system. Office of Scientific and Technical Information (OSTI), juillet 1991. http://dx.doi.org/10.2172/5585871.

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LeCren, R. T., L. H. Cowell, M. A. Galica, M. D. Stephenson et C. S. When. Advanced coal-fueled industrial cogeneration gas turbine system. Office of Scientific and Technical Information (OSTI), juin 1992. http://dx.doi.org/10.2172/6552127.

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LeCren, R. T., L. H. Cowell, M. A. Galica, M. D. Stephenson et C. S. Wen. Advanced coal-fueled industrial cogeneration gas turbine system. Office of Scientific and Technical Information (OSTI), juillet 1990. http://dx.doi.org/10.2172/5858228.

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Price, Jeffrey. Advanced Materials for Mercury 50 Gas Turbine Combustion System. Office of Scientific and Technical Information (OSTI), septembre 2008. http://dx.doi.org/10.2172/991117.

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