Reheating in gas turbine results in

A. Increase of work ratio

B. Decrease of thermal efficiency

C. Decrease of work ratio

D. Both (A) and (B) above

Please do not use chat terms. Example: avoid using "grt" instead of "great".

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  1. In a compressor, free air delivered is the actual volume delivered at the stated pressure reduced to
  2. High air-fuel ratio is used in gas turbines
  3. Pick up the false statement
  4. The capacity of a compressor is expressed in
  5. A compressor at high altitude will draw
  6. In a four stage compressor, if the pressure at the first and third stage is 1 bar and 16 bar, then the…
  7. In gas turbines, high thermal efficiency is obtained in
  8. The maximum combustion pressure in gas turbine as compared to I.C. engine is
  9. Gas turbine as compared to steam turbine
  10. The compression ratio for the compressor is always __________ unity.
  11. Pick up the wrong statement about advantages of multistage compression
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  13. Compression efficiency is compared against
  14. The indicated work per unit mass of air delivered is
  15. Air-fuel ratio in a jet engine will be of the order of
  16. The efficiency of the vane blower is (where W₁ = Workdone due to compression, and W₂ =…
  17. In the axial flow gas turbine, the work ratio is the ratio of
  18. High air-fuel ratio in gas turbines
  19. The work done per unit mass of air in compression will be least when n is equal to
  20. Which of the following statement is correct?
  21. Rotary compressors are used for delivering
  22. For speed above 3000 km/hour, it is more advantageous to use
  23. For perfect intercooling in a two stage compressor
  24. Pick up the wrong statement
  25. Euler's equation is applicable for
  26. In air breathing jet engine, the jet is formed by expanding
  27. A rocket engine uses ________ for the combustion of its fuel.
  28. A turboprop is preferred to turbojet because
  29. The clearance volume of the air compressor is kept minimum because
  30. As the turbine inlet temperature increases, the thermal efficiency of gas turbine for the optimum pressure…