Compressors, Gas Turbines and Jet Engines

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

A. the propulsive matter is caused to flow around the propelled body
B. propulsive matter is ejected from within the propelled body
C. its functioning does not depend on presence of air
D. all of the above
E. none of the above

A. decreasing the compression work
B. increasing the compression work
C. increasing the turbine work
D. decreasing the turbine work
E. A. and C. above