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Unformatted text preview: The Jet Engine). Due to their very small size, it is much harder to cool the compressor blades, so no active cooling is currently used.] a) For a turbojet engine with a compressor pressure ratio of 25, and a turbine inlet temperature of 1800K, under what flight conditions (Mach number) would the compressor inlet temperature limit be exceeded? Consider performance at sea-level (Tatm=300K) and at 10km (Tatm = 216K) b) At a constant flight Mach number of 1.2, how much do the thermal and propulsive efficiency change between altitudes of sea-level and 10km? Explain this behavior. c) If you were forced to reduce the turbine inlet temperature to 1400K because the turbine durability group was having difficulty designing the blades to withstand temperatures of 1800K, how would it impact the performance of the vehicle (consider M=1.2 and 10km only)?...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05