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Relevant bibliographies by topics / Gas turbine flow efficiency

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Academic literature on the topic 'Gas turbine flow efficiency'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "Gas turbine flow efficiency"

1

Kosowski, Krzysztof, and Marian Piwowarski. "Design Analysis of Micro Gas Turbines in Closed Cycles." Energies 13, no. 21 (November 5, 2020): 5790. http://dx.doi.org/10.3390/en13215790.

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The problems faced by designers of micro-turbines are connected with a very small volume flow rate of working media which leads to small blade heights and a high rotor speed. In the case of gas turbines this limitation can be overcome by the application of a closed cycle with very low pressure at the compressor inlet (lower than atmospheric pressure). In this way we may apply a micro gas turbine unit of accepted efficiency to work in a similar range of temperatures and the same pressure ratios, but in the range of smaller pressure values and smaller mass flow rate. Thus, we can obtain a gas turbine of a very small output but of the efficiency typical of gas turbines with a much higher power. In this paper, the results of the thermodynamic calculations of the turbine cycles are discussed and the designed gas turbine flow parts are presented. Suggestions of the design solutions of micro gas turbines for different values of power output are proposed. This new approach to gas turbine arrangement makes it possible to build a gas turbine unit of a very small output and a high efficiency. The calculations of cycle and gas turbine design were performed for different cycle parameters and different working media (air, nitrogen, hydrogen, helium, xenon and carbon dioxide).

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Yang, Xiaoyong, Zhenjia Yu, Xiaoli Yu, and Jie Wang. "ICONE19-43289 EFFECTS OF FLOW LOSSES ON EFFICIENCY OF HTGR GAS TURBINE CYCLE." Proceedings of the International Conference on Nuclear Engineering (ICONE) 2011.19 (2011): _ICONE1943. http://dx.doi.org/10.1299/jsmeicone.2011.19._icone1943_125.

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Valenti, Michael. "Keeping it Cool." Mechanical Engineering 123, no. 08 (August 1, 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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Wilson, Jay M., and Henry Baumgartner. "A New Turbine for Natural Gas Pipelines." Mechanical Engineering 121, no. 05 (May 1, 1999): 72–74. http://dx.doi.org/10.1115/1.1999-may-7.

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The new Cooper-Bessemer power turbine is a high-efficiency, center frame-mounted, three-stage unit that can be driven by either the existing RB211-24 gas generator or the new improved version. The upgraded gas generator combined with the new power turbine offers an increase in nominal output from 28.4 MW (38,000 hp) to 31.8 MW (42,600 hp). The new coupled turbine, now being tested, is called the Coberra 6761. Besides improving core engine performance, the program's objectives included improved fuel efficiency and reliability, and easier site serviceability; extension of the modular concept from the gas generator into the power turbine with improvements in sealing, materials, and temperature capability as well as interchangeability of both upgraded turbines with existing hardware. The Rolls-Royce industrial RB211 turbine, derived from an aircraft engine, is the basis for the gas generator end of Cooper Energy Services' Coberra coupled turbines. The power turbine design capacity has a significant effect on the power at a given speed. The flow capacity was optimized to achieve the best thermal efficiency and lower IP speeds to optimize IP compressor efficiency and permit future throttle push.

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Rodgers, C. "Impingement Starting and Power Boosting of Small Gas Turbines." Journal of Engineering for Gas Turbines and Power 107, no. 4 (October 1, 1985): 821–27. http://dx.doi.org/10.1115/1.3239817.

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The technology of high-pressure air or hot-gas impingement from stationary shroud supplementary nozzles onto radial outflow compressors and radial inflow turbines to permit rapid gas turbine starting or power boosting is discussed. Data are presented on the equivalent turbine component performance for convergent/divergent shroud impingement nozzles, which reveal the sensitivity of nozzle velocity coefficient with Mach number and turbine efficiency with impingement nozzle admission arc. Compressor and turbine matching is addressed in the transient turbine start mode with the possibility of operating these components in braking or reverse flow regimes when impingement flow rates exceed design.

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Крюков, Алексей, and Aleksei Kriukov. "Three dimensional gas-dynamic calculation of nozzle block of small flow-rate centripetal turbine." Vestnik of Astrakhan State Technical University. Series: Marine engineering and technologies 2019, no. 4 (November 15, 2019): 89–95. http://dx.doi.org/10.24143/2073-1574-2019-4-89-95.

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The article describes the low-consumption turbines as reliable, productive, small-sized actuating mechanisms in various units and machines. Experience in production and use of low-cost turbine stages contributes to improving the efficiency along with simplifying and re-ducing the cost of manufacturing of the blades and the stage in general. Improving the efficiency of low-consumption turbines requires solving the problem of aerodynamic improvement of the flow part and the calculated determination of the optimal geometry and operating modes of the impeller flow. One of the innovative ways to improve the design efficiency of low-consumption turbines is the automation of the development process using modern modeling systems based on the developed software systems. Due to the small size of the design, the design calculations of turbine stages of this type have been made in a one-dimensional formulation with the involvement of various analogies with classical stages. Using three-dimensional gas dynamic calculations based on the ANSYS CFX platform will significantly improve the quality of design of flow parts of low-flow turbines. Implementation of three-dimensional gas-dynamic calculation of the nozzle unit using the software package ANSYS CFX low-consumption turbine stage can solve this problem. The geometric model is built using AutoCAD software, the grid is selected, the boundary conditions are set. The values of the experimental coefficients of the nozzle velocity, neck velocity and the tangential component of velocity at the nozzle outlet have been compared with the coefficients obtained when using the software package. There have been built the velocity fields and made conclusions about feasibility of using the ANSYS CFX software package to determine the main parameters of a three-dimensional flow of the turbine stage.

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Vidian, Fajri, Putra Anugrah Peranginangin, and Muhamad Yulianto. "Cycle-Tempo Simulation of Ultra-Micro Gas Turbine Fueled by Producer Gas Resulting from Leaf Waste Gasification." Journal of Mechanical Engineering 24, no. 3 (September 30, 2021): 14–20. http://dx.doi.org/10.15407/pmach2021.03.014.

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Leaf waste has the potential to be converted into energy because of its high availability both in the world and Indonesia. Gasification is a conversion technology that can be used to convert leaves into producer gas. This gas can be used for various applications, one of which is using it as fuel for gas turbines, including ultra-micro gas ones, which are among the most popular micro generators of electric power at the time. To minimize the risk of failure in the experiment and cost, simulation is used. To simulate the performance of gas turbines, the thermodynamic analysis tool called Cycle-Tempo is used. In this study, Cycle-Tempo was used for the zero-dimensional thermodynamic simulation of an ultra-micro gas turbine operated using producer gas as fuel. Our research contributions are the simulation of an ultra-micro gas turbine at a lower power output of about 1 kWe and the use of producer gas from leaf waste gasification as fuel in a gas turbine. The aim of the simulation is to determine the influence of air-fuel ratio on compressor power, turbine power, generator power, thermal efficiency, turbine inlet temperature and turbine outlet temperature. The simulation was carried out on condition that the fuel flow rate of 0.005 kg/s is constant, the maximum air flow rate is 0.02705 kg/s, and the air-fuel ratio is in the range of 1.55 to 5.41. The leaf waste gasification was simulated before, by using an equilibrium constant to get the composition of producer gas. The producer gas that was used as fuel had the following molar fractions: about 22.62% of CO, 18.98% of H2, 3.28% of CH4, 10.67% of CO2 and 44.4% of N2. The simulation results show that an increase in air-fuel ratio resulted in turbine power increase from 1.23 kW to 1.94 kW. The generator power, thermal efficiency, turbine inlet temperature and turbine outlet temperature decreased respectively from 0.89 kWe to 0.77 kWe; 3.17% to 2.76%; 782 °C to 379 °C and 705°C to 304 °C. The maximums of the generator power and thermal efficiency of 0.89 kWe and 3.17%, respectively, were obtained at the 1.55 air-fuel ratio. The generator power and thermal efficiency are 0.8 kWe and 2.88%, respectively, with the 4.64 air-fuel ratio or 200% excess air. The result of the simulation matches that of the experiment described in the literature.

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Rice, I. G. "Split Stream Boilers for High-Temperature/High-Pressure Topping Steam Turbine Combined Cycles." Journal of Engineering for Gas Turbines and Power 119, no. 2 (April 1, 1997): 385–94. http://dx.doi.org/10.1115/1.2815586.

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Research and development work on high-temperature and high-pressure (up to 1500°F TIT and 4500 psia) topping steam turbines and associated steam generators for steam power plants as well as combined cycle plants is being carried forward by DOE, EPRI, and independent companies. Aeroderivative gas turbines and heavy-duty gas turbines both will require exhaust gas supplementary firing to achieve high throttle temperatures. This paper presents an analysis and examples of a split stream boiler arrangement for high-temperature and high-pressure topping steam turbine combined cycles. A portion of the gas turbine exhaust flow is run in parallel with a conventional heat recovery steam generator (HRSG). This side stream is supplementary fired opposed to the current practice of full exhaust flow firing. Chemical fuel gas recuperation can be incorporated in the side stream as an option. A significant combined cycle efficiency gain of 2 to 4 percentage points can be realized using this split stream approach. Calculations and graphs show how the DOE goal of 60 percent combined cycle efficiency burning natural gas fuel can be exceeded. The boiler concept is equally applicable to the integrated coal gas fuel combined cycle (IGCC).

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Godin, T., S. Harvey, and P. Stouffs. "High-Temperature Reactive Flow of Combustion Gases in an Expansion Turbine." Journal of Turbomachinery 119, no. 3 (July 1, 1997): 554–61. http://dx.doi.org/10.1115/1.2841157.

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The analysis of the chemical behavior of the working fluid in gas turbines is usually restricted to the combustion chamber sections. However, the current trend toward higher Turbine Inlet Temperatures (TIT), in order to achieve improved thermal efficiency, will invalidate the assumption of frozen composition of the gases in the first stages of the expansion process. It will become necessary to consider the recombination reactions of the dissociated species, resulting in heat release during expansion. In order to quantify the influence of this reactivity on the performance of high TIT gas turbines, a one-dimensional model of the reactive flow has been developed. Preliminary results were reported in a previous paper. The authors concluded that, in the case of expansion of combustion gases in a subsonic static uncurved distributor nozzle, the residual reactivity must be taken into account above a temperature threshold of around 2000 K. The present study extends these results by investigating the reactive flow in a complete multistage turbine set, including a transonic first-stage nozzle. A key result of this study is that heat release during the expansion process itself will be considerable in future high-temperature gas turbines, and this will have significant implications for turbine design techniques. Furthermore, we show that, at the turbine exit, the fractions of NO and CO are very different from the values computed at the combustor outlet. In particular, NO production in the early part of the expansion process is very high. Finally, the effects of temperature fluctuations at the turbine inlet are considered. We show that residual chemical reactivity affects the expansion characteristics in gas turbines with TITs comparable to those attained by modern high-performance machines.

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Choi, Seok Min, Seungyeong Choi, and Hyung Hee Cho. "Effect of Various Coolant Mass Flow Rates on Sealing Effectiveness of Turbine Blade Rim Seal at First Stage Gas Turbine Experimental Facility." Energies 13, no. 16 (August 7, 2020): 4105. http://dx.doi.org/10.3390/en13164105.

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The appropriate coolant mass flow of turbine blade rim seal has become an important issue as turbine blades are exposed to increasingly higher thermal load owing to increased turbine inlet temperature. If the coolant is deficient, hot gas ingresses to the rim seal, or if sufficient, the efficiency of turbine decreases. Therefore, we analyzed sealing effectiveness of rim seal derive appropriate coolant mass flow rate at various conditions. The experimental facility was modified from one designed for an aero-engine gas turbine. Rotational Reynolds number varied from 3 × 105 to 5 × 105 based on rotational speed. Pressure was measured at various locations in the shroud, endwall, and rim seal. CO2 concentration was measured at various rim seal locations to analyze sealing effectiveness. Measured results showed that 1.35% coolant mass flow rate of rim seal exhibited a little ingress effect, whereas lower coolant mass flow rates exhibited higher ingress effect. A predicted correlation for sealing effectiveness of rim seal was derived at various rotational Reynolds number and coolant mass flow rate. The correlation will be useful for turbine cooling design, helping to predict sealing effectiveness of rim seals during preliminary design processes for new gas turbines.

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Dissertations / Theses on the topic "Gas turbine flow efficiency"

1

Johnson, A. B. "The aerodynamic effects of nozzle guide vane shock wave and wake on a transonic turbine rotor." Thesis, University of Oxford, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.329958.

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Plewacki, Nicholas. "Modeling High Temperature Deposition in Gas Turbines." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587714424017527.

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Templalexis, I. K. "Gas turbine performance with distorted inlet flow." Thesis, Cranfield University, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.427101.

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Batt, J. J. M. "Three-dimensional unsteady gas turbine flow measurement." Thesis, University of Oxford, 1997. http://ora.ox.ac.uk/objects/uuid:3302ca8f-0618-4440-9e23-3bf99bc3705d.

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The high pressure turbine stage can be considered the most important component for the efficiency and longevity of a modern gas turbine. The flow field within this stage is highly complex and is both unsteady and three-dimensional. Understanding this flow field is essential if improvements are to be made to future engine designs. Increasingly designers are placing more emphasis on the use of Computational Fluid Dynamics (CFD) rather than experimental results. CFD methods can be more flexible and cost effective. However before these predictions can be used they must be validated against experimental data at engine conditions. The hostile environment and complexity of flows within a gas turbine engine mean that collection of experimental data is extremely challenging. This thesis describes the development of an instrumentation technique for unsteady gas turbine flow measurement capable of resolving unsteady three-dimensional flow. The technique is based on an aerodynamic probe constructed with miniature semiconductor pressure transducers manufactured by Kulite Semiconductor Inc. Measurements recorded using this instrumentation technique from the Oxford Rotor experiment are presented to illustrate its use, and these in turn are compared with a CFD prediction of the rotor flow-field. This work was funded by the Engineering and Physical Sciences Research Council and Kulite Semiconductor Inc. The Oxford Rotor project is jointly funded by the Engineering and Physical Sciences Research Council (EPSRC), and Rolls-Royce Plc.

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Palafox, Pepe. "Gas turbine tip leakage flow and heat transfer." Thesis, University of Oxford, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.427699.

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6

Stitzel, Sarah M. "Flow Field Computations of Combustor-Turbine Interactions in a Gas Turbine Engine." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/30992.

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The current demands for higher performance in gas turbine engines can be reached by raising combustion temperatures to increase thermal efficiency. Hot combustion temperatures create a harsh environment which leads to the consideration of the durability of the combustor and turbine sections. Improvements in durability can be achieved through understanding the interactions between the combustor and turbine. The flow field at a combustor exit shows non-uniformities in pressure, temperature, and velocity in the pitch and radial directions. This inlet profile to the turbine can have a considerable effect on the development of the secondary flows through the vane passage. This thesis presents a computational study of the flow field generated in a non-reacting gas turbine combustor and how that flow field convects through the downstream stator vane. Specifically, the effect that the combustor flow field had on the secondary flow pattern in the turbine was studied. Data from a modern gas turbine engine manufacturer was used to design a realistic, low speed, large scale combustor test section. This thesis presents the results of computational simulations done in parallel with experimental simulations of the combustor flow field. In comparisons of computational predictions with experimental data, reasonable agreement of the mean flow and general trends were found for the case without dilution jets. The computational predictions of the combustor flow with dilution jets indicated that the turbulence models under-predicted jet mixing. The combustor exit profiles showed non-uniformities both radially and circumferentially, which were strongly dependent on dilution and cooling slot injection. The development of the secondary flow field in the turbine was highly dependent on the incoming total pressure profile. For a case with a uniform inlet pressure in the near-wall region no leading edge vortex was formed. The endwall heat transfer was found to also depend strongly on the secondary flow field, and therefore on the incoming pressure profile from the combustor.
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Hollis, David. "Particle image velocimetry in gas turbine combustor flow fields." Thesis, Loughborough University, 2004. https://dspace.lboro.ac.uk/2134/7640.

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Current and future legislation demands ever decreasing levels of pollution from gas turbine engines, and with combustor performance playing a critical role in resultant emissions, a need exists to develop a greater appreciation of the fundamental causes of unsteadiness. Particle Image Velocimetry (PIV) provides a platform to enable such investigations. This thesis presents the development of PIV measurement methodologies for highly turbulent flows. An appraisal of these techniques applied to gas turbine combustors is then given, finally allowing a description of the increased understanding of the underlying fluid dynamic processes within combustors to be provided. Through the development of best practice optimisation procedures and correction techniques for the effects of sub-grid filtering, high quality PN data has been obtained. Time average statistical data at high spatial resolution has been collected and presented for generic and actual combustor geometry providing detailed validation of the turbulence correction methods developed, validation data for computational studies, and increased understanding of flow mechanisms. These data include information not previously available such as turbulent length scales. Methodologies developed for the analysis of instantaneous PIV data have also allowed the identification of transient flow structures not seen previously because they are invisible in the time average. Application of a new `PDF conditioning' technique has aided the explanation of calculated correlation functions: for example, bimodal primary zone recirculation behaviour and jet misalignments were explained using these techniques. Decomposition of the velocity fields has also identified structures present such as jet shear layer vortices, and through-port swirling motion. All of these phenomena are potentially degrading to combustor performance and may result in flame instability, incomplete combustion, increased noise and increased emissions.

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Alhajeri, Hamad. "Heat removal in axial flow high pressure gas turbine." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/11465.

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The demand for high power in aircraft gas turbine engines as well as industrial gas turbine prime mover promotes increasing the turbine entry temperature, the mass flow rate and the overall pressure ratio. High turbine entry temperature is however the most convenient way to increase the thrust without requiring a large change in the engine size. This research is focused on improving the internal cooling of high pressure turbine blade by investigating a range of solutions that can contribute to the more effective removal of heat when compared with existing configuration. The role played by the shape of the internal blade passages is investigated with numerical methods. In addition, the application of mist air as a means of enhanced heat removal is studied. The research covers three main area of investigation. The first one is concerned with the supply of mist on to the coolant flow as a mean to enhancing heat transfer. The second area of investigation is the manipulation of the secondary flow through cross-section variation as a means to augment heat transfer. Lastly a combination of a number of geometrical features in the passage is investigated. A promising technique to significantly improve heat transfer is to inject liquid droplets into the coolant flow. The droplets which will evaporate after travelling a certain distance, act as a cooling sink which consequently promote added heat removal. Due to the promising results of mist cooling in the literature, this research investigated its effect on a roughened cooling passage with five levels of mist mass percentages. In order to validate the numerical model, two stages were carried out. First, one single-phase flow case was validated against experimental results available in the open literature. Analysing the effect of the rotational force, on both flow physics and heat transfer, on the ribbed channel was the main concern of this investigation. Furthermore, the computational results using mist injection were also validated against the experimental results available in the literature. Injection of mist in the coolant flow helped achieve up to a 300% increase in the average flow temperature of the stream, therefore in extracting significantly more heat from the wall. The Nusselt number increased by 97% for the rotating leading edge at 5% mist injection. In the case of air only, the heat transfers decrease in the second passage, while in the mist case, the heat transfer tends to increase in the second passage. Heat transfer increases quasi linearly with the increase of the mist percentage when there is no rotation. However, in the presence of rotation, the heat transfers increase with an increase in mist content up to 4%, thereafter the heat transfer whilst still rising does so more gradually. The second part of this research studies the effect of non-uniform cross- section on the secondary flow and heat transfer in order to identify a preferential design for the blade cooling internal passage. Four different cross-sections were investigated. All cases start with square cross-section which then change all the way until it reaches the 180 degree turn before it changes back to square cross-section at the outlet. All cases were simulated at four different speeds. At low speeds the rectangle and trapezoidal cross-section achieved high heat transfer. At high speed the pentagonal and rectangular cross-sections achieved high heat transfer. Pressure loss is accounted for while making use of the thermal performance factor parameter which accounts for both heat transfer and pressure loss. The pentagonal cross-section showed high potential in terms of the thermal performance factor with a value over 0.8 and higher by 33% when compared to the rectangular case. In the final section multiple enhancement techniques are combined in the sudden expansion case, such as, ribs, slots and ribbed slot. The maximum heat enhancement is achieved once all previous techniques are used together. Under these circumstances the Nusselt number increased by 60% in the proposed new design.

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Janakiraman, S. V. "Fluid flow and heat transfer in transonic turbine cascades." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06112009-063614/.

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Ghulam, Mohamad. "Characterization of Swirling Flow in a Gas Turbine Fuel Injector." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563877023803877.

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Books on the topic "Gas turbine flow efficiency"

1

Janicka, Johannes. Flow and Combustion in Advanced Gas Turbine Combustors. Dordrecht: Springer Netherlands, 2013.

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Janicka, Johannes, Amsini Sadiki, Michael Schäfer, and Christof Heeger, eds. Flow and Combustion in Advanced Gas Turbine Combustors. Dordrecht: Springer Netherlands, 2013. http://dx.doi.org/10.1007/978-94-007-5320-4.

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3

Shyy, W. A numerical study of flow in gas-turbine combustor. New York: AIAA, 1987.

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4

Standardization, International Organization for. Measurement of gas flow in closed conduits - turbine meters. Geneva: International Organization for Standardization, 1993.

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5

Hermsmeyer, Stephan. Improved methods for modelling turbine engine gas flow properties. Birmingham: University of Birmingham, 1996.

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6

Arts, T. Three dimensional rotational inviscid flow calculation in axial turbine blade rows. Rhode Saint Genese, Belgium: Von Karman Institute, 1985.

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Lin, Chin-Shun. Numerical calculations of turbulent reacting flow in a gas-turbine combustor. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

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G, Williams J. Estimating engine airflow in gas-turbine powered aircraft with clean and distorted inlet flows. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1996.

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9

Graham, Robert W. Recent progress in research pertaining to estimates of gas-side heat transfer in an aircraft gas turbine. [Washington, D.C.]: NASA, 1990.

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10

Gorla, Rama S. R. Probabilistic analysis of solid oxide fuel cell based hybrid gas turbine system. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Book chapters on the topic "Gas turbine flow efficiency"

1

Siegmann, J., G. Becker, J. Michaelis, and M. Schäfer. "Efficient Numerical Schemes for Simulation and Optimization of Turbulent Reactive Flows." In Flow and Combustion in Advanced Gas Turbine Combustors, 297–323. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_10.

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Ulbrich, S., and R. Roth. "Efficient Numerical Multilevel Methods for the Optimization of Gas Turbine Combustion Chambers." In Flow and Combustion in Advanced Gas Turbine Combustors, 379–411. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_13.

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Zohuri, Bahman. "Gas Turbine Working Principles." In Combined Cycle Driven Efficiency for Next Generation Nuclear Power Plants, 147–71. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15560-9_7.

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Zohuri, Bahman, and Patrick McDaniel. "Gas Turbine Working Principals." In Combined Cycle Driven Efficiency for Next Generation Nuclear Power Plants, 149–74. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-70551-4_7.

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Chow, S. K., D. G. N. Tse, and J. H. Whitelaw. "Review of Recent Measurements in Gas Turbine Combustors." In Combustings Flow Diagnostics, 375–97. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2588-8_14.

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Rieger, Neville F. "Flow Efficiency and Excitation in Turbine Stages." In Vibration and Wear in High Speed Rotating Machinery, 413–43. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-1914-3_24.

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Schobeiri, Meinhard T. "Turbine and Compressor Cascade Flow Forces." In Gas Turbine Design, Components and System Design Integration, 133–57. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_5.

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Schobeiri, Meinhard T. "Turbine and Compressor Cascade Flow Forces." In Gas Turbine Design, Components and System Design Integration, 129–56. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_5.

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Schobeiri, Meinhard T. "Efficiency of Multi-Stage Turbomachines." In Gas Turbine Design, Components and System Design Integration, 215–24. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_7.

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Schobeiri, Meinhard T. "Efficiency of Multi-Stage Turbomachines." In Gas Turbine Design, Components and System Design Integration, 213–23. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_7.

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Conference papers on the topic "Gas turbine flow efficiency"

1

Schlein, Barry. "Gas Turbine Combustion Efficiency." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-121.

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A method of correlating combustor efficiency as a function of geometry and operating conditions is presented. A simple equation correlates all the data for a given engine type with a single parameter. The correlating parameter is a function of fuel flow, pressure, temperature and volume in a form similar to others in the literature. The unique feature of the correlating parameter is its use of internal gas temperature rather than the commonly used combustor inlet temperature. The result is an equation requiring an iterative solution since combustion efficiency is a part of the correlating parameter. With use of a computer this is easily handled. The correlation fits engine data over all flight conditions from high altitude, high Mach number to sea level idle. The correlation is compared to engine test data for several engines.

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Shobhavathy, M. T., and Premakara Hanoca. "CFD Analysis to Understand the Flow Behaviour of a Single Stage Transonic Axial Flow Compressor." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3592.

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This paper comprises the Computational Fluid Dynamic (CFD) analysis to investigate the flow behaviour of a high speed single stage transonic axial flow compressor. Steady state analyses were carried out at design and part speed conditions to obtain the overall performance map using commercial CFD software ANSYS FLUENT. Radial distribution of flow parameters were obtained at 90% of design speed for the choked flow and near stall flow conditions. The predicted data were validated against available experimental results. The end wall flow fields were studied with the help of velocity vector plots and Mach number contours at peak efficiency and near stall flow conditions at 60% and 100% design speeds. This study exhibited the nature of a transonic compressor, having strong interaction between the rotor passage shock and the tip leakage vortex at design speed, which generates a region of high blockage in the rotor blade passage. The influence of this interaction extends around15% of the blade outer span at design speed and in the absence of blade passage shock at 60% design speed, the influence of tip leakage flow observed was around 8%.

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Arcoumanis, C., I. Hakeem, L. Khezzar, R. F. Martinez-Botas, and N. C. Baines. "Performance of a Mixed Flow Turbocharger Turbine Under Pulsating Flow Conditions." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-210.

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The performance of a high pressure ratio (P.R.=2.9) mixed flow turbine for an automotive turbocharger has been investigated and the results revealed its better performance relative to a radial-inflow geometry under both steady and pulsating flow conditions. The advantages offered by the constant blade angle rotor allow better turbocharger-engine matching and maximization of the energy extracted from the pulsating engine exhaust gases. In particular, the mixed inlet blade geometry resulted in high efficiency at high expansion ratios where the engine-exhaust pulse energy is maximum. The efficiency characteristics of the mixed flow turbine under steady conditions were found to be fairly uniform when plotted against the velocity ratio, with a peak efficiency at the design speed of 0.75. The unsteady performance as indicated by the mass-averaged total-to-static efficiency and the swallowing capacity exhibited a departure from the quasi-steady assumption which is analysed and discussed.

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Rajamani, Keerthivasan, Madhu Ganesh, Karthikeyan Paramanandam, Chandiran Jayamurugan, Sridharan R. Narayanan, Balamurugan Srinivasan, and A. Chandra. "Cooling Efficiency Enhancement Using Impingement Cooling Technique for Turbine Blades." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3803.

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The effect of impingement cooling on the internal surface (cooling passage) of the leading edge region in a commercial turbine high pressure first stage rotor blade is investigated using Computational Fluid Dynamics (CFD) simulations. The flow domain is obtained by stretching the middle cross section (50% span) of the above mentioned blade. The simulations are performed for 3 different profiles in the cooling flow passage. In all the cases, the nozzle position and Mach number of cooling fluid is kept constant at E/D = 4.32 and 0.4 respectively. In the first case, the suction side profile is modified to facilitate shift in the vortex. This may reduce the crossflow effect, which will enhance the Nuavg. However, simulation results showed that Nuavg is reduced by 2% when compared to base case. In the second case, the coolant flow passage is smoothened at the apex to reduce dead zone and to enhance spreading of the jet. In this case, a 3% increase in Nuavg is obtained. Based on the analysis of velocity contours in the second case, the coolant flow passage in the third case is further modified to improve the spreading of flow. This resulted in 5% increase in the Nuavg when compared to base case.

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Banerjee, Abhisek, Sukanta Roy, Prasenjit Mukherjee, and Ujjwal K. Saha. "Unsteady Flow Analysis Around an Elliptic-Bladed Savonius-Style Wind Turbine." In ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8141.

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Although considerable progress has already been achieved in the design of wind turbines, the available technical designs are not yet adequate to develop a reliable wind energy converter especially meant for small-scale applications. The Savonius-style wind turbine appears to be particularly promising for the small-scale applications because of its design simplicity, good starting ability, insensitivity to wind directions, relatively low operating speed, low cost and easy installation. However, its efficiency is reported to be inferior as compared to other wind turbines. Aiming for that, a number of investigations have been carried out to increase the performance of this turbine with various blade shapes. In the recent past, investigations with different blade geometries show that an elliptic-bladed turbine has the potential to harness wind energy more efficiently. In view of this, the present study attempts to assess the performance of an elliptic-bladed Savonius-style wind turbine using 2D unsteady simulations. The SST k-ω turbulence model is used to simulate the airflow over the turbine blades. The power and torque coefficients are calculated at rotating conditions, and the results obtained are validated with the wind tunnel experimental data. Both the computational and experimental studies indicate a better performance with the elliptical blades. Further, the present analysis also demonstrates improved flow characteristics of the elliptic-bladed turbine over the conventional semi-circular design.

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Dominy, Robert G., David A. Kirkham, and Andrew D. Smith. "Flow Development Through Inter-Turbine Diffusers." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-139.

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Inter-turbine diffusers offer the potential advantage of reducing the flow coefficient in the following stages leading to increased efficiency. The flows associated with these ducts differ from those in simple annular diffusers both as a consequence of their high-curvature S-shaped geometry and of the presence of wakes created by the upstream turbine. Experimental data and numerical simulations clearly reveal the generation of significant secondary flows as the flow develops through the diffuser in the presence of cross-passage pressure gradients. The further influence of inlet swirl is also demonstrated. Data from experimental measurements with and without an upstream turbine are discussed and computational simulations are shown not only to give a good prediction of the flow development within the diffuser but also to demonstrate the importance of modelling the fully three-dimensional nature of the flow.

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Moyle, Ian N. "Analysis of Efficiency Sensitivity Associated With Tip Clearance in Axial Flow Compressors." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-216.

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The effects of tip clearance changes on efficiency in axial compressors are typically established experimentally. The ratio of change of efficiency with change of clearance gap varies significantly for different compressors in the published data. An analysis of this sensitivity range in terms of the blade and stage design parameters was initiated. The analysis revealed that the sensitivity range largely resulted from a derivation at constant flow of the efficiency decrement. It was also found that a generalized loss method of generating the sensitivities produced a much improved correlation of the change in efficiency with change in clearance over a variety of machines, configurations and speeds.

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Krzyzanowski, J. A. "On Predicting Steam Turbine Blading Erosion and Turbine Efficiency Deterioration." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-224.

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Two-phase flow of wet steam is nowadays a subject of intensive research for different reasons. Prediction of erosion damage to turbine blading is one of important elements of this research. In the paper, a method of predicting this damage as a function of time is presented briefly. The emphasis is however put on the statistics of the accuracy of damage prediction as compared to field measurements. Also comments on erosion induced turbine efficiency deterioration are presented. The paper relates to the authors experience presented in references [1] and [2].

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Prasad, Santosh Kumar, Pradeep Sangli, Osman Buyukisik, and Dave Pugh. "Prediction of Gas Turbine Oil Scoop Capture Efficiency." In ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8329.

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The lubrication system in a gas turbine engine is akin to the human blood circulatory system. Providing right quantities of oil to the right components for cooling and lubrication is the primary function of the lubrication system. In the current analysis, at the downstream end of the lube oil supply line, a stationary oil nozzle sprays a jet of oil to a high speed rotating component called an oil scoop. The function of the oil scoop which rotates at speeds usually greater than 10000 RPM is to ‘Scoop’ or capture the oil and provide an under race oil transfer mechanism to the bearings rotating especially at such high speeds. If the oil capture is less than required by the downstream bearing components, it could lead to diminished bearing lives in the gas turbine. The oil scoop consists of two or more blades that are angled with respect to the radius of the Scoop to provide an entry to the oil jet. The ‘window’ of open space between the blades is important to capture the oil. The ratio of quantity of oil captured to the total oil sprayed on to oil scoop is termed as the oil capture efficiency. Several parameters like oil nozzle distance from the blade tip, spray characteristics, jet velocity, number of blades, blade angle, window width, rotational speeds, oil temperature etc. are important factors that determine the capture efficiency of the oil scoop. Prior to the availability of efficient CFD methodologies, it was extremely difficult to develop an oil scoop capture efficiency predictive tool that involves a complex 3D fluid flow from a stationary to a rotating component. The typical Reynolds number of the jet is around 13000 and the oil scoop tip speeds of the order of Mach 0.2 to 0.4. To evaluate various scoop design configurations and enhancements, a transient CFD methodology was developed using multiphase Volume of Fluid approach available in FLUENT® software. In this paper a technique or process is described and demonstrated to simulate the right ‘periodic’ nature of the oil capture and transfer mechanism. It is shown that the CFD methodology described compares well with experimental data. This robust CFD methodology predicts the complex 3D flow with sufficient accuracy and has the potential to be used to optimize the geometry for maximum oil capture efficiency of oil scoops in gas turbine lubrication system. Significant reduction of costly experiments is also an important benefit of developing this predictive methodology.

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Patel, Kashyap, Chaina Ram, and Vishal Rasaniya. "Numerical Analysis of Turbulent Mixing in Cross Flow Configurations." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2506.

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Abstract The gas turbine combustion chamber is a vital part of a gas turbine engine. Proper mixing of air in the combustor plays an important role in combustion. Increasing mixing rate is an important factor for better combustion efficiency. The injection of air in crossflow is widely studied over the years. The air injected at an angle in upstream direction gives better mixing by colliding with the crossflow. The computational analysis of the injected jet in cross flow is performed with different angles in the upstream direction. The k-omega SST turbulence model was used to investigate the mixing behavior. The air is injected at different angles and observed that with an increase in angle from 60° to 135°, the rate of mixing and turbulent intensity increased. The jet inclination in the upstream direction greatly influenced the mixing behavior. The jet penetration in perpendicular direction was almost the same for 120° and 135°. But there is added penalty in the form of the pressure loss at the angle 135°. So considering the pressure loss and ease of manufacturing the 120° jet inclination is preferable for better mixing among the four cases studied here. The idea of inclining jet in upstream direction can be implemented on the combustor for increased performance and shorter size.

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Reports on the topic "Gas turbine flow efficiency"

1

Dr. Adam London. A Low-Cost, High-Efficiency Periodic Flow Gas Turbine for Distributed Energy Generation. Office of Scientific and Technical Information (OSTI), June 2008. http://dx.doi.org/10.2172/932510.

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Norris, Thomas R. Test Program for High Efficiency Gas Turbine Exhaust Diffuser. Office of Scientific and Technical Information (OSTI), December 2009. http://dx.doi.org/10.2172/969712.

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W.L. Lundberg, G.A. Israelson, M.D. Moeckel, S.E. Veyo, R.A. Holmes, P.R. Zafred, J.E. King, and R.E. Kothmann. A High Efficiency PSOFC/ATS-Gas Turbine Power System. Office of Scientific and Technical Information (OSTI), February 2001. http://dx.doi.org/10.2172/859228.

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Steward, W. Gene. Flow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow. Office of Scientific and Technical Information (OSTI), November 1999. http://dx.doi.org/10.2172/764563.

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Wang, Anbo, Gary Pickrell, Russell May, and Adrian Roberts. High Temperature Optical Fiber Instrumentation for Gas Flow Monitoring in Gas Turbine Engines. Fort Belvoir, VA: Defense Technical Information Center, February 2002. http://dx.doi.org/10.21236/ada400148.

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K.R. Rajagopal and I.J. Rao. AN INVESTIGATION INTO THE MECHANICS OF SINGLE CRYSTAL TURBINE BLADES WITH A VIEW TOWARDS ENHANCING GAS TURBINE EFFICIENCY. Office of Scientific and Technical Information (OSTI), May 2006. http://dx.doi.org/10.2172/887494.

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Hsu, M., D. Nathanson, and D. T. Bradshaw. ZTEK`s ultra-high efficiency fuel cell/gas turbine system for distributed generation. Office of Scientific and Technical Information (OSTI), December 1996. http://dx.doi.org/10.2172/460195.

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Detor, Andrew, Richard DiDomizio, Don McAllister, Erica Sampson, Rongpei Shi, and Ning Zhou. A New Superalloy Enabling Heavy Duty Gas Turbine Wheels for Improved Combined Cycle Efficiency. Office of Scientific and Technical Information (OSTI), January 2017. http://dx.doi.org/10.2172/1337871.

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Solomon, P. R., Yuxin Zhao, and D. S. Pines. Feasibility study for an advanced coal fired heat exchanger/gas turbine topping cycle for a high efficiency power plant. Office of Scientific and Technical Information (OSTI), February 1993. http://dx.doi.org/10.2172/7089854.

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Solomon, P. R., Y. Zhao, D. Pines, R. C. Buggeln, and S. J. Shamroth. Feasibility study for an advanced coal fired heat exchanger/gas turbine topping cycle for a high efficiency power plant. Final report. Office of Scientific and Technical Information (OSTI), November 1993. http://dx.doi.org/10.2172/10135308.

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