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The maximum combustion pressure in gas turbine as compared to I.C. engine is

A. More

B. Less

C. Same

D. Depends on other factors

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  1. In which case the air-fuel ratio is likely to be maximum?
  2. The volumetric efficiency for reciprocating air compressors is about
  3. A closed cycle gas turbine gives ________ efficiency as compared to an open cycle gas turbine.
  4. In a compressor, free air delivered is the actual volume delivered at the stated pressure reduced to
  5. Gas turbine works on
  6. Separators in compressor installations are located
  7. In the aircraft propellers
  8. Pick up the false statement
  9. The compressor capacity with decrease in suction temperature
  10. In a reciprocating air compressor, the compression work per kg of air
  11. A centrifugal compressor works on the principle of
  12. The advantage of multistage compression over single stage compression is
  13. Pressure ratio in gas turbines is the ratio of
  14. In turbo fan engine, the jet velocity as compared to turbojet engine is
  15. The capacity of a compressor is 5 m /min refers to
  16. Pick up the correct statement
  17. The maximum compression ratio in an actual single stage axial flow compressor is of the order of
  18. High air-fuel ratio in gas turbines
  19. A jet engine works on the principle of conservation of
  20. In open cycle turbojet engines used in military aircraft, reheating the exhaust gas from the turbine…
  21. Diffuser in a compressor is used to
  22. The overall efficiency of the compressed air system is the
  23. A compressor at high altitudes will require ________ power.
  24. For minimum work required to compress and deliver a quantity of air by multistage compression
  25. Stalling of blades in axial flow compressor is the phenomenon of
  26. The performance of air compressor at high altitudes will be ________ as compared to that at sea level.
  27. The volumetric efficiency of a compressor
  28. For speed above 3000 km/hour, it is more advantageous to use
  29. The following property is most important for material used for gas turbine blade
  30. A turboprop is preferred to turbojet because