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The compressor efficiency is the

A. Isothermal H.P/indicated H.R

B. Isothermal H.P./shaft H.R

C. Total output/air input

D. Compression work/motor input

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  1. The work done per unit mass of air in compression will be least when n is equal to
  2. Inter-cooling in gas turbine results in
  3. The thermodynamic efficiency of rotary compressor is based on
  4. The ratio of isentropic work to Euler work is known as
  5. The following is true for an open cycle gas turbine having exhaust heat exchanger. Atmospheric air before…
  6. The workdone on a compressor will be minimum if air is taken from
  7. The maximum temperature in a gas turbine is
  8. Which of the following statement is correct?
  9. Which is false statement about multistage compression?
  10. The mean effective pressure of the compressor is the
  11. For an irreversible gas turbine cycle, the efficiency and work ratio both depend on
  12. The reason for volumetric efficiency of reciprocating compressor being less than 100 percent is
  13. Atmospheric pressure is 1.03 kg/cm and vapour pressure is 0.03 kg/cm. The air pressure will be
  14. Volumetric efficiency of air compressors is of the order of
  15. Pick up the wrong statement about advantages of multistage compression
  16. In axial flow compressor, exit flow angle deviation from the blade angle is a function of
  17. Reheating in gas turbine results in
  18. The work ratio of a gas turbine plant is defined as the ratio of
  19. For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling…
  20. Rotary compressors are used for delivering
  21. Maximum work is done in compressing air when the compression is
  22. A rocket engine for the combustion of its fuel
  23. An aftercooler is used to
  24. The efficiency of a jet engine is higher at
  25. The velocity of air entering in a rocket is ________ as compared to an aircraft.
  26. In a jet propulsion
  27. The efficiency of jet engine is
  28. Gas turbine works on
  29. Gas turbines use following type of air compressor
  30. The thrust of a jet propulsion power unit can be increased by