8th Edition

ISBN: 9780100257054

Author: CENGEL

Publisher: YUZU

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Chapter 9.12, Problem 167RP

Consider an ideal gas-turbine cycle with one stage of compression and two stages of expansion and regeneration. The pressure ratio across each turbine stage is the same. The high-pressure turbine exhaust gas enters the regenerator and then enters the low-pressure turbine for expansion to the compressor inlet pressure. Determine the thermal efficiency of this cycle as a function of the compressor pressure ratio and the high-pressure- turbine-to-compressor inlet temperature ratio. Compare your result with the efficiency of the standard regenerative cycle.

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Chapter 9.12, Problem 166RP

Chapter 9.12, Problem 169RP

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Chapter 9 Solutions

EBK THERMODYNAMICS: AN ENGINEERING APPR

Ch. 9.12 - What are the air-standard assumptions?Ch. 9.12 - What is the difference between air-standard...Ch. 9.12 - How does the thermal efficiency of an ideal cycle,...Ch. 9.12 - What does the area enclosed by the cycle represent...Ch. 9.12 - Prob. 5P Ch. 9.12 - Prob. 6P Ch. 9.12 - Can the mean effective pressure of an automobile...Ch. 9.12 - Prob. 8P Ch. 9.12 - What is the difference between spark-ignition and...Ch. 9.12 - Prob. 10P

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Solution Summary: The author compares the thermal efficiency of the cycle as a function of compressor pressure ratio and high-pressure turbine-to-compressor inlet temperature ratio.

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