TY  - JOUR
AB  - 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.
VL  - 42
IS  - 12
SN  - 0002-2667
DO  - 10.1108/eb034699
UR  - https://doi.org/10.1108/eb034699
AU  - Suciu S.N.
PY  - 1970
Y1  - 1970/01/01
TI  - 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
T2  - Aircraft Engineering and Aerospace Technology
PB  - MCB UP Ltd
SP  - 10
EP  - 17
Y2  - 2024/04/24
ER  -