Other Gas Power System Applications
Air enters the diffuser of a turbojet engine with a mass flow rate of 85 lb/s at 9 lbf/in.2, 420°R, and a velocity of 750 ft/s. The pressure ratio for the compressor is 12, and its isentropic efficiency is 88%. Air enters the turbine at 2400°R with the same pressure as at the exit of the compressor. Air exits the nozzle at 9 lbf/in.2 The diffuser operates isentropically and the nozzle and turbine have isentropic efficiencies of 92% and 90%, respectively. On the basis of an air-standard analysis, calculate
(a) the rate of heat addition, in Btu/h.
(b) the pressure at the turbine exit, in lbf/in.2
(c) the compressor power input, in Btu/h.
(d) the velocity at the nozzle exit, in ft/s.
Neglect kinetic energy except at the diffuser inlet and the nozzle exit.
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