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TECHNICAL PAPERS: Gas Turbines: Advanced Energy Systems

Limitations on Gas Turbine Performance Imposed by Large Turbine Cooling Flows

[+] Author and Article Information
J. H. Horlock

Whittle Laboratory, Engineering Department, Cambridge University, Madinglet Road, Cambridge CB3 0DY UK

D. T. Watson

Rolls Royce plc, Derby, UK

T. V. Jones

Osney Laboratory, Engineering Science Department, Oxford University, Oxford, UK

J. Eng. Gas Turbines Power 123(3), 487-494 (Feb 01, 2001) (8 pages) doi:10.1115/1.1373398 History: Received September 01, 2000; Revised February 01, 2001
Copyright © 2001 by ASME
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References

Figures

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(a) Simple model for convective cooling, (b) simple model for film cooling, (c) simple model for transpiration cooling
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Approximate expressions for cooling mass flow fraction ξ as a function of cooling effectiveness, for first nozzle guide vane row
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The Shapiro/Hartsel model for simple mixing
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Thermal efficiency as a function of combustion temperature Tcot and pressure ratio r (for film cooling, mass flow ratio ξ=0.045W+)
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Specific work as a function of combustion temperature Tcot and pressure ratio r (for cooling mass flow ratio ξ=0.045W+)
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Thermal efficiency as a function of combustion temperature Tcot for r=30 and for coolant mass flow ratios; (i) ξ=0 (uncooled); (ii) ξ=0.045W+ (film cooling); (iii) ξ=0.037Tg1/2W+/pg (film cooling); (iv) transpiration cooling
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The effect of number of cooled stages

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