Gte Tutorial 2 MCQ

22 Questions | Total Attempts: 243

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GTE tutorial 2Term test practice


Questions and Answers
  • 1. 
    The energy required to accelerate a large mass of air to a low final velocity is, in comparison to that required to accelerate a small mass of air to a high velocity is:
    • A. 

      Higher

    • B. 

      The same

    • C. 

      Lower

  • 2. 
    A turbo-jet engine gives:
    • A. 

      A small acceleration to a large mass of air.

    • B. 

      A large acceleration to a large mass of air.

    • C. 

      A large acceleration to a small mass of air.

  • 3. 
    A turbo-prop engine gives:
    • A. 

      A small acceleration to a large mass of air.

    • B. 

      A large acceleration to a large mass of air.

    • C. 

      A large acceleration to a small mass of air.

  • 4. 
    Engine efficiencies may be compared using:
    • A. 

      Thrust : weight ratio

    • B. 

      Specific fuel consumption.

    • C. 

      Overall fuel consumption.

  • 5. 
    A by-pass ratio of 3:1 means the by-pass airflow is:
    • A. 

      Three times higher than the core flow.

    • B. 

      A third of the core flow.

    • C. 

      Twice the core flow.

  • 6. 
    The density of a gas may be expressed as:
    • A. 

      Pressure / Volume

    • B. 

      Volume / mass

    • C. 

      Mass / volume

  • 7. 
    As aircraft forward speed increases, the specific fuel consumption of an engine:
    • A. 

      Increases

    • B. 

      Decreases

    • C. 

      Does not change

  • 8. 
    Which of the following factors affect the thermal efficiency of a turbine engine? 1.Turbine inlet temperature. 2.Compression ratio. 3.Ambient temperature. 4.Speed of the aircraft. 5.Turbine and compressor efficiency. 6.Altitude of the aircraft.
    • A. 

      3, 4 and 6

    • B. 

      1, 2 and 5

    • C. 

      1, 2 and 6

  • 9. 
    In a gas turbine engine, combustion occurs at a constant
    • A. 

      Volume

    • B. 

      Pressure

    • C. 

      Density

  • 10. 
    As aircraft forward speed increases the propulsive efficiency of an engine:
    • A. 

      Increases

    • B. 

      Decreases

    • C. 

      Does not change

  • 11. 
    Bernoulli’s Theorem states that the total amount of energy in a gas flow:
    • A. 

      Remains constant

    • B. 

      Increases

    • C. 

      Decreases

  • 12. 
    Net thrust is:
    • A. 

      Momentum thrust plus pressure thrust

    • B. 

      Gross thrust minus momentum drag

    • C. 

      Gross thrust minus pressure thrust and momentum drag

  • 13. 
    The Brayton cycle is known as the constant
    • A. 

      Pressure cycle.

    • B. 

      Temperature cycle.

    • C. 

      Mass cycle.

  • 14. 
    In a gas turbine engine, combustion occurs at a constant __________.
    • A. 

      Volume.

    • B. 

      Pressure.

    • C. 

      Density.

  • 15. 
    When air intake thermal anti-icing protection is switched ON:
    • A. 

      The engine thrust and EGT are unaffected.

    • B. 

      The engine thrust reduces and the EGT rises.

    • C. 

      The engine thrust increases and the EGT rises.

  • 16. 
    Ram recovery is said to have occurred when the thrust increase it produces:
    • A. 

      Compensates for the thrust lost to momentum drag.

    • B. 

      Reaches the rated sea level thrust value.

    • C. 

      Matches the net thrust.

  • 17. 
    The maximum permissible air velocity entering a gas turbine compressor is:
    • A. 

      Mach 1

    • B. 

      Mach 0.4

    • C. 

      Mach 1.2

  • 18. 
    The vortex dissipators installed on some turbine-powered aircraft to prevent engine FOD utilize
    • A. 

      Variable inlet guide vanes (IGV) and/or variable first stage fan blades.

    • B. 

      Variable geometry inlet ducts.

    • C. 

      A stream of engine bleed air blown toward the ground ahead of the engine.

  • 19. 
    Anti-icing of jet engine air inlets is commonly accomplished by
    • A. 

      Electrical heating elements inside the inlet guide vanes.

    • B. 

      Engine bleed air ducted through the critical areas.

    • C. 

      Electrical heating elements located within the engine air inlet cowling.

  • 20. 
    The purpose of a bellmouth compressor inlet is to
    • A. 

      Provide an increased ram air effect at low airspeeds.

    • B. 

      Maximize the aerodynamic efficiency of the inlet.

    • C. 

      provide an increased pressure drop in the inlet.

  • 21. 
    When an engine with a subsonic divergent type inlet duct is running in place at high speed on the ground, the air pressure within the inlet is
    • A. 

      Positive.

    • B. 

      Negative.

    • C. 

      Ambient.

  • 22. 
    Ram pressure recovery is the slight increase in thrust caused by
    • A. 

      A reduction in air mass flow through the engine at altitude.

    • B. 

      An increase in air temperature due to ram air pressure in the inlet duct.

    • C. 

      An increase in air pressure due to ram recovery by the inlet duct.

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