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A compressor at high altitude will draw

A. More power

B. Less power

C. Same power

D. More/less power depending on other factors

Correct Answer : B.


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  1. A closed cycle gas turbine consists of a
  2. The pressure and temperature conditions of air at the suction of compressor are
  3. The work done per unit mass of air in compression will be least when n is equal to
  4. The thrust of a jet propulsion power unit can be increased by
  5. Pick up the wrong statement about advantages of multistage compression
  6. The criterion of the thermodynamic efficiency for rotary compressor is
  7. The pressure of air at the beginning of the compression stroke is ________ the atmospheric pressure.
  8. Standard air is the air at ________ and relative humidity of 36 percent.
  9. Phenomenon of choking in compressor means
  10. The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity)
  11. The volumetric efficiency of a compressor
  12. Which is false statement about advantages of multistage compressor in comparison to single stage compressor?
  13. In jet engines, for the efficient production of large power, fuel is burnt in an atmosphere of
  14. Intercooling in gas turbines
  15. Ramjet engine
  16. The ratio of the volume of free air delivery per stroke to the swept volume of the piston, is known…
  17. Losses in a centrifugal compressor are due to
  18. If the clearance ratio for a reciprocating air compressor is 'K', then its volumetric efficiency is…
  19. Diffuser in a compressor is used to
  20. The main purpose of reheating in gas turbine is to
  21. The compressor capacity is defined as the
  22. If the flow of air through the compressor is perpendicular to its axis, then it is a
  23. Reheating in a multistage expansion gas turbine __________ compressor work.
  24. In jet engines, paraffin is usually used as the fuel because of its
  25. The net work input required for compressor with increase in clearance volume
  26. During base load operation, the best method of controlling compressor is
  27. The overall isothermal efficiency of compressor is defined as the ratio of
  28. The efficiency of a jet engine is higher at
  29. Ratio of indicated h.p. to shaft h.p. in known as
  30. In the aircraft propellers