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In a jet engine, the air-fuel ratio is

A. 30 : 1

B. 40 : 1

C. 50 : 1

D. 60 : 1

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  1. The ratio of work done per cycle to the swept volume in case of compressor is called
  2. In the aircraft propellers
  3. A rocket engine uses ________ for the combustion of its fuel.
  4. Intercooling in gas turbines
  5. The pressure of air at the beginning of the compression stroke is ________ the atmospheric pressure.
  6. A gas turbine used in air craft should have
  7. Reheating in gas turbine results in
  8. In multistage compressor, the isothermal compression is achieved by
  9. The compressor efficiency is the
  10. The reason for volumetric efficiency of reciprocating compressor being less than 100 percent is
  11. Pick up the wrong statement
  12. Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is
  13. For perfect intercooling in a three stage compressor
  14. Gas turbines for power generation are normally used
  15. Reheating in multistage expansion gas turbine results in
  16. The capacity of compressor will be highest when its intake temperature is
  17. The working fluid in a turbine is
  18. Maximum delivery pressure is a rotary air compressor is of the order of
  19. Which of the following statement is correct relating to rocket engines?
  20. In a jet engine, the air-fuel ratio is
  21. The air entry velocity m a rocket as compared to aircraft is
  22. An aftercooler is used to
  23. The work ratio of a gas turbine plant is defined as the ratio of
  24. The effective power of gas turbines is increased by adding the following in compressor
  25. A closed gas turbine in which fuel is burnt directly in the air is not possible because of
  26. A turboprop is preferred to turbojet because
  27. The clearance volume of the air compressor is kept minimum because
  28. A jet engine works on the principle of conservation of
  29. More than one stage will be preferred for reciprocating compressor if the delivery pressure is more…
  30. The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in…