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TECHNICAL PAPERS

The Basic Thermodynamics of Turbine Cooling

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

Whittle Laboratory, Engineering Department, Cambridge University, United Kingdom

J. Turbomach 123(3), 583-592 (Mar 01, 2000) (10 pages) doi:10.1115/1.1370156 History: Received March 01, 2000
Copyright © 2001 by ASME
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References

Figures

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(a) Basic Joule-Brayton cycle, [CHT]RU; (b) reversible cycle with single-step cooling, [CHT]RC1
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Breakdown of [CHT]RC1 cycle
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(a) Reversible cycle with two-step cooling, [CHT]RC2; (b) reversible cycle with two step cooling, low pressure air throttled, [CHT]RC2T
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Multistep reversible cooling
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(a) Irreversible cycle with single-step cooling, [CHT]IC1; (b) irreversible cycle with two step cooling, low pressure air throttled, [CHT]IC2T
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Diagrams showing variations in thermal efficiency with maximum temperatures
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Real gas thermal efficiency calculations, [CHT]IU and [CHT]IC1. For r=30,ηc=0.8,ηt=0.9,TBL=1123 K, convective cooling (using the Elmasri expression for cooling fraction, with K=0.05, no mixing losses). Maximum temperatures absolute (K ).
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Real gas calculations of thermal efficiency and specific work, for single step cooling cycle [CHT]IC1pcpt=0.9,TBL=1073 K, film cooling with combustion and mixing stagnation pressure losses, after Horlock et al. 5.
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Real gas calculations of thermal efficiency and specific work, for three-step cooling cycle [CHT]IC3Tpcpt=0.9,TBL=1073 K, film cooling, with combustion and mixing stagnation pressure losses, after Horlock, Watson, and Jones 5.

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