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Mechanical Engineering :: Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines - section-1
  1. Inter cooling in compressors

    2. A.

     Cools the delivered air
    B.

     Results in saving of power in compressing a given volume to given pressure
    C.

     Is the standard practice for big compressors
    D.

     Enables compression in two stages

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  2. Isothermal compression efficiency can be attained by running the compressor

    3. A.

     At very high speed
    B.

     At very slow speed
    C.

     At average speed
    D.

     At zero speed

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  3. Fighter bombers use following type of engine

    4. A.

     Turbojet
    B.

     Turbo-propeller
    C.

     Rocket
    D.

     Ramjet

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  4. The process, which causes the air to enter the impeller blades of a centrifugal compressor at ________ velocity (without effecting the mass of air to flow and velocity of flow) is known as prewhirl.

    5. A.

     Reduced
    B.

     Increased
    C.

     Zero
    D.

     None of these

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  5. For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will

    6. A.

     Increase
    B.

     Decrease
    C.

     Remain unaffected
    D.

     Other factors control it

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  6. High air-fuel ratio in gas turbines

    7. A.

     Increases power output
    B.

     Improves thermal efficiency
    C.

     Reduces exhaust temperature
    D.

     Do not damage turbine blades

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  7. In the axial flow gas turbine, the work ratio is the ratio of

    8. A.

     Compressor work and turbine work
    B.

     Output and input
    C.

     Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet
    D.

     Actual compressor work and theoretical compressor work

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  8. Which of the following statement is correct relating to rocket engines?

    9. A.

     The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel
    B.

     The stagnation conditions exist at the combustion chamber
    C.

     The exit velocities of exhaust gases are much higher than those in jet engine
    D.

     All of the above

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  9. The power available for takeoff and climb in case of turbojet engine as compared to reciprocating engine is

    10. A.

     Less
    B.

     More
    C.

     Same
    D.

     May be less or more depending on ambient conditions

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  10. Gas turbines use following type of air compressor

    11. A.

     Centrifugal type
    B.

     Reciprocating type
    C.

     Lobe type
    D.

     Axial flow type

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