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 providea higher specific thrust; to increase the bypass ratio of a turbofan engine to improve its propulsive efficiency; to optimize 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 turboshaft 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.
Suciu, S. (1970), "High Temperature Turbine Design Considerations: A discussion of the major technological developments which have led to the trend of using higher temperatures in modern gas turbine aero engines from a paper first presented at an AGARD conference in September", Aircraft Engineering and Aerospace Technology, Vol. 42 No. 12, pp. 10-17. https://doi.org/10.1108/eb034699Download as .RIS
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