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15/1/2

15/1/2
29問 • 1年前
  • Guevara Official
    • 通報

    問題一覧

  • 1

    Newton’s 2nd law used

    to calculate the amount of thrust produced by the engine

  • 2

    Thrust can be increased by increasing

    increasing air mass flown to engine or gases acceleration through the engine

  • 3

    Thrust in a gas turbine engine is produced by

    Compressor (increase air pressure) and Combustor (increase gases acceleration

  • 4

    The output of the engine when the aircraft in flight is called

    net thrust

  • 5

    ESHP

    = SHP + Jet Thrust Addition of SHP to jet thrust. 1hp=745.7

  • 6

    Propulsive efficiency

    is the ability of engine to drive the aircraft in flight

  • 7

    The specific fuel consumption

    thrust produced per pound of fuel consumed

  • 8

    At 400 knots Ram effect

    increase

  • 9

    .... thrust increase with small increase in RPM

    At higher engine speeds

  • 10

    As altitude increase air pressure (density) & temperature

    decrease

  • 11

    Aircraft altitude & ambient temperature

    affect the inlet air density.

  • 12

    Gas turbine engine efficiency increases at altitude

    due to drag decrease

  • 13

    As temperature increase air density decrease

    which negatively effect engine thrust and vice versa

  • 14

    Lower temperature gives

    greater mass flow and greater thrust

  • 15

    the working cycle of the heat engine

    as constant-pressure cycle

  • 16

    gas inside the combustion section of gas turbine engine

    reduce from front to rear

  • 17

    Pressure in combustion chamber

    virtually constant.

  • 18

    The rocket is

    a non-air breathing engine means it does not use atmospheric air to support combustion

  • 19

    Pulse Jet

    it has additional spring loaded valves in the air intake

  • 20

    The turbofan mixture of a

    turbojet and a turboprop, literally handles a hot air mass and a cold air mass

  • 21

    ......... always maintain high pressure compressor speed constant.

    Governor

  • 22

    A high bypass engine is more efficient because it is similar to the

    to the propeller by accelerating large mass of air at a low rate of acceleration

  • 23

    Easier starting (the small.... needs to be rotated by the starter

    HP compressor only

  • 24

    ..... is gas coupling with compressor.... mechanically connected.

    Free turbine&not

  • 25

    ......... drives the output shaft which drives propeller in turbo-prop engine and rotor in turbo-shaft engines

    Free turbine

  • 26

    By pass ratio 5:1

    indicates that bypass flow is five times the hot stream

  • 27

    1st digit represent the

    bypass air

  • 28

    2nd digit represent to

    engine core air

  • 29

    The highest air pressure

    at compressor outlet

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    問題一覧

  • 1

    Newton’s 2nd law used

    to calculate the amount of thrust produced by the engine

  • 2

    Thrust can be increased by increasing

    increasing air mass flown to engine or gases acceleration through the engine

  • 3

    Thrust in a gas turbine engine is produced by

    Compressor (increase air pressure) and Combustor (increase gases acceleration

  • 4

    The output of the engine when the aircraft in flight is called

    net thrust

  • 5

    ESHP

    = SHP + Jet Thrust Addition of SHP to jet thrust. 1hp=745.7

  • 6

    Propulsive efficiency

    is the ability of engine to drive the aircraft in flight

  • 7

    The specific fuel consumption

    thrust produced per pound of fuel consumed

  • 8

    At 400 knots Ram effect

    increase

  • 9

    .... thrust increase with small increase in RPM

    At higher engine speeds

  • 10

    As altitude increase air pressure (density) & temperature

    decrease

  • 11

    Aircraft altitude & ambient temperature

    affect the inlet air density.

  • 12

    Gas turbine engine efficiency increases at altitude

    due to drag decrease

  • 13

    As temperature increase air density decrease

    which negatively effect engine thrust and vice versa

  • 14

    Lower temperature gives

    greater mass flow and greater thrust

  • 15

    the working cycle of the heat engine

    as constant-pressure cycle

  • 16

    gas inside the combustion section of gas turbine engine

    reduce from front to rear

  • 17

    Pressure in combustion chamber

    virtually constant.

  • 18

    The rocket is

    a non-air breathing engine means it does not use atmospheric air to support combustion

  • 19

    Pulse Jet

    it has additional spring loaded valves in the air intake

  • 20

    The turbofan mixture of a

    turbojet and a turboprop, literally handles a hot air mass and a cold air mass

  • 21

    ......... always maintain high pressure compressor speed constant.

    Governor

  • 22

    A high bypass engine is more efficient because it is similar to the

    to the propeller by accelerating large mass of air at a low rate of acceleration

  • 23

    Easier starting (the small.... needs to be rotated by the starter

    HP compressor only

  • 24

    ..... is gas coupling with compressor.... mechanically connected.

    Free turbine&not

  • 25

    ......... drives the output shaft which drives propeller in turbo-prop engine and rotor in turbo-shaft engines

    Free turbine

  • 26

    By pass ratio 5:1

    indicates that bypass flow is five times the hot stream

  • 27

    1st digit represent the

    bypass air

  • 28

    2nd digit represent to

    engine core air

  • 29

    The highest air pressure

    at compressor outlet