. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m,...
. A turbofan aircraft engine is flying at 720 km/h at an
altitude of 6100 m, where the ambient conditions are 50 kPa and
-12°C (a negative value). The pressure ratio across the compressor
is 13, and the turbine inlet temperature (TIT) is 1330 K. Assuming
ideal operation for all components and constant specific heats for
the air at room temperature (cold air model).
(a) Sketch the T-s diagram of the cycle, and determine:
(b) The Mach number of the flight.
(c) The total mass flow rate through the engine.
(d) The total mass flow rate through the fan and the
compressor.
(e) The exit velocity of the exhaust gases from the engine.
(f) The air temperature at the fan outlet needed to produce the
engine thrust (50,000 N)
This is from Chapter 9: Gas Power Cycles (Section: Jet-Propulsion Cycles)
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