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High Temperature Turbine Design Considerations

Published online by Cambridge University Press:  04 July 2016

S. N. Suciu
S. N. Suciu*
Affiliation:
Design Technology Operation, General Electric Company
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Extract

The effect of higher turbine inlet temperature on the performance of an aircraft gas turbine engine can be quite dramatic. It can be used to increase the exhaust velocity of a dry turbojet to provide a higher specific thrust; to increase the by-pass ratio of a turbofan engine to improve its propulsive efficiency; to optimise the thermodynamic cycle at a higher pressure ratio to improve its specific fuel consumption; to reduce the amount of afterburner fuel flow in an augmented turbojet to improve its specific fuel consumption, or to increase the work output of a turbo-shaft engine. If the thrust or power of the engine is held constant, a size, cost and/or weight reduction can result. If the size of the engine is held constant growth capability can be provided.

Type
Supplementary Papers
Information
The Aeronautical Journal , Volume 75 , Issue 728 , August 1971 , pp. 577 - 586
Copyright
Copyright © Royal Aeronautical Society 1971 

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