Gas Turbines and Jet Engines

A. using mulit-stage compressor with mfercooler
B. adding heat exchanger
C. injecting water in/around combustion chamber
D. reheating the air after partial expansion in the turbine
E. all of the above

A. speed
B. speed
C. altitude
D. Vspeed
E. does not Vary

A. turbo-jet engine
B. ram-jet engine
C. propellers
D. rockets
E. hydraulic jet propulsion

A. higher at ground
B. higher at high altitudes
C. same at all altitudes
D. higher at high speed
E. lower at low speed

A. gases
B. solids
C. liquid
D. plasma
E. highly heated atmospheric air

A. 2500°C
B. 2000°C
C. 1500°C
D. 1000°C
E. 700°C

A. high thermal efficiency
B. reduction in compressor work
C. decrease of heat loss in exhaust
D. maximum work output
E. none of the above

A. increases thermal efficiency
B. allows high compression ratio
C. decreases heat loss is exhaust
D. allows operation at very high altitudes
E. permits high moisture content fuel to be used

A. increase temperature
B. reduce turbine size
C. increase power output
D. increase speed
E. increase pressure ratio

A. net work output and work done by turbine
B. net work output and heat supplied
C. work done by turbine and heat supplied
D. work done by turbine and net work output
E. actual/heat drop and isentropic heat drop