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Turbine engines (2)
20問 • 1年前
  • ユーザ名非公開
  • 通報

    問題一覧

  • 1

    What is the major function of the turbine assembly in a turbojet engine?

    Supplies the power to turn the compressor.

  • 2

    Turbine blades are generally more susceptible to operating damage than compressor blades because of

    exposure to high temperatures.

  • 3

    If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they

    must be degaussed before use.

  • 4

    Stator blades in the compressor section of an axial-flow turbine engine

    decrease the air velocity and prevent swirling.

  • 5

    What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?

    Retrim the engine.

  • 6

    The air passing through the combustion chamber of a turbine engine is

    used to support combustion and to cool the engine.

  • 7

    During inspection, turbine engine components exposed to high temperatures may only be marked with such materials as allowed by the manufacturer. These materials generally include 1. layout dye. 2. commercial felt tip marker. 3. wax or grease pencil. 4. chalk. 5. graphite lead pencil.

    1, 2, and 4.

  • 8

    What is one purpose of the stator blades in the compressor section of a turbine engine?

    Control the direction of the airflow.

  • 9

    Why do some turbine engines have more than one turbine wheel attached to a single shaft?

    To extract more power from the exhaust gases than a single wheel can absorb.

  • 10

    Which of the following influences the operation of an automatic fuel control unit on a turbojet engine?

    Burner pressure.

  • 11

    (1) Accumulation of contaminates in the compressor of a turbojet engine reduces aerodynamic efficiency of the blades. (2) Two common methods for removing dirt deposits from turbojet engine compressor blades are a fluid wash and an abrasive grit blast. Regarding the above statements

    both No. 1 and No. 2 are true.

  • 12

    The diffuser section of a jet engine is located between

    the compressor section and the burner section

  • 13

    The compressor stators in a gas turbine engine act as diffusers to

    decrease the velocity of the gas flow.

  • 14

    Which statement is true regarding jet engines?

    At the higher engine speeds, thrust increases rapidly with small increases in RPM.

  • 15

    The exhaust section of a turbine engine is designed to

    impart a high exit velocity to the exhaust gases.

  • 16

    A turbine engine compressor which contains vanes on both sides of the impeller is a

    double entry centrifugal compressor.

  • 17

    condition known as ‘hot streaking’ in turbine engines is caused by

    a partially clogged fuel nozzle.

  • 18

    An advantage of the centrifugal-flow compressor is its high

    pressure rise per stage.

  • 19

    At what stage in a turbine engine are gas pressures the greatest?

    Compressor outlet.

  • 20

    At what point in an axial-flow turbojet engine will the highest gas pressures occur?

    At the compressor outlet.

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    54問 • 1年前
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    ユーザ名非公開 · 100問 · 1年前

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    ユーザ名非公開 · 16問 · 1年前

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    16問 • 1年前
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    ユーザ名非公開 · 10問 · 1年前

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    10問 • 1年前
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    ユーザ名非公開 · 100問 · 1年前

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    100問 • 1年前
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    ユーザ名非公開 · 100問 · 1年前

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    100問 • 1年前
    ユーザ名非公開

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    Fuel metering systems

    ユーザ名非公開 · 98問 · 1年前

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    98問 • 1年前
    ユーザ名非公開

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    ユーザ名非公開 · 79問 · 1年前

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    79問 • 1年前
    ユーザ名非公開

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    ユーザ名非公開 · 100問 · 1年前

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    100問 • 1年前
    ユーザ名非公開

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    ユーザ名非公開 · 30問 · 1年前

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    30問 • 1年前
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    ユーザ名非公開 · 100問 · 1年前

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    100問 • 1年前
    ユーザ名非公開

    問題一覧

  • 1

    What is the major function of the turbine assembly in a turbojet engine?

    Supplies the power to turn the compressor.

  • 2

    Turbine blades are generally more susceptible to operating damage than compressor blades because of

    exposure to high temperatures.

  • 3

    If, during inspection at engine overhaul, ball or roller bearings are found to have magnetism but otherwise have no defects, they

    must be degaussed before use.

  • 4

    Stator blades in the compressor section of an axial-flow turbine engine

    decrease the air velocity and prevent swirling.

  • 5

    What must be done after the fuel control unit has been replaced on an aircraft gas turbine engine?

    Retrim the engine.

  • 6

    The air passing through the combustion chamber of a turbine engine is

    used to support combustion and to cool the engine.

  • 7

    During inspection, turbine engine components exposed to high temperatures may only be marked with such materials as allowed by the manufacturer. These materials generally include 1. layout dye. 2. commercial felt tip marker. 3. wax or grease pencil. 4. chalk. 5. graphite lead pencil.

    1, 2, and 4.

  • 8

    What is one purpose of the stator blades in the compressor section of a turbine engine?

    Control the direction of the airflow.

  • 9

    Why do some turbine engines have more than one turbine wheel attached to a single shaft?

    To extract more power from the exhaust gases than a single wheel can absorb.

  • 10

    Which of the following influences the operation of an automatic fuel control unit on a turbojet engine?

    Burner pressure.

  • 11

    (1) Accumulation of contaminates in the compressor of a turbojet engine reduces aerodynamic efficiency of the blades. (2) Two common methods for removing dirt deposits from turbojet engine compressor blades are a fluid wash and an abrasive grit blast. Regarding the above statements

    both No. 1 and No. 2 are true.

  • 12

    The diffuser section of a jet engine is located between

    the compressor section and the burner section

  • 13

    The compressor stators in a gas turbine engine act as diffusers to

    decrease the velocity of the gas flow.

  • 14

    Which statement is true regarding jet engines?

    At the higher engine speeds, thrust increases rapidly with small increases in RPM.

  • 15

    The exhaust section of a turbine engine is designed to

    impart a high exit velocity to the exhaust gases.

  • 16

    A turbine engine compressor which contains vanes on both sides of the impeller is a

    double entry centrifugal compressor.

  • 17

    condition known as ‘hot streaking’ in turbine engines is caused by

    a partially clogged fuel nozzle.

  • 18

    An advantage of the centrifugal-flow compressor is its high

    pressure rise per stage.

  • 19

    At what stage in a turbine engine are gas pressures the greatest?

    Compressor outlet.

  • 20

    At what point in an axial-flow turbojet engine will the highest gas pressures occur?

    At the compressor outlet.