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The axial flow compressor is preferred in aircraft gas turbines because of

A. Low frontal area

B. Higher thrust

C. High pressure rise

D. None of these

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  18. The overall isothermal efficiency of the compressor is defined as the ratio of
  19. Inter-cooling in gas turbine results in
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  22. In a centrifugal compressor, the flow of air is ________ to the axis of compressor.
  23. The efficiency of roots blower ________ with the increase in pressure ratio.
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