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15/3/4

15/3/4
32問 • 1年前
  • Guevara Official
    • 通報

    問題一覧

  • 1

    In turbojet engine the function of the air intake section is to

    deliver a smooth and uniform stream of air to the compressor inlet

  • 2

    Pitot intake is

    divergent duct (front to rear) and best suited for subsonic aircrafts

  • 3

    Pitot intake typical efficiency is

    96-99%

  • 4

    Convergent-Divergent intake,

    fixed duct design convergent then divergent duct. Used to slow down air flow speed to subsonic before compressor

  • 5

    In an aircraft flying at supersonic speed to reduce the air velocity at compressor the variable intake

    throat area decreased

  • 6

    Anti Icing System Function

    used to prevent ice formation of engine intake

  • 7

    Intake & inlet guide vanes are anti iced using

    bled hot air from the compressor

  • 8

    Icing condition when OAT is

    (10°+ C) with visible moisture.

  • 9

    Turboprop intake and propeller use electrical heater mats

    operated part continuous & part intermittent

  • 10

    The advantage of electrical anti-icing system used on engine inlets is

    to minimal loss of engine power or thrust

  • 11

    The centrifugal compressor is ideally suited

    to reverse flow turboprop engines

  • 12

    double entry compressor problem is

    difficulty in designing.

  • 13

    Compressor stage

    is a raw of rotor and a raw of stator

  • 14

    Stator

    increase pressure and control the direction of airflow.

  • 15

    Rotor

    increase air velocity

  • 16

    Compressor blades and diameter getting smaller (front to rear) to maintain........ through the compressor.

    axial velocity

  • 17

    ......... is the ratio between compressor outlet pressure to compressor inlet pressure

    Compressor pressure ratio

  • 18

    The primary factor

    that control the pressure ratio is number of stages in the compressor

  • 19

    The highest gas pressure through gas turbine engine

    at compressor outlet

  • 20

    Root

    is lowest stagger angle at the root

  • 21

    Compressor RPM is

    limited by blade tip speed

  • 22

    To calculate compressor outlet pressure you need to

    multiply inlet pressure with compression ratio

  • 23

    A combination type (Hybrid compressor) used in

    small gas turbine engines with reverse flow combustion

  • 24

    Engine design point is the point which engine will operate during most of its service,

    it is based on cruise speed and altitude (air density)

  • 25

    Twin spool compressor is more

    flexibility of operation and greater resistance to surge

  • 26

    Low pressure compressor runs at

    lower RPM than high pressure compressor

  • 27

    Single spool compressor is

    less efficient

  • 28

    Variable stator vanes and bleed valve used to

    avoid surge.

  • 29

    In a centrifugal flow compressor the high efficiency of compressor achieved by

    keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage

  • 30

    The function of snubber mid span shroud used on fan blade

    to support fan blade and prevent aerodynamic instability

  • 31

    centrifugal compressor Advantage .

    Simple ,Low weight & cost and High pressure rise per stage

  • 32

    Centerifugal compressor Disadvantage

    Large frontal area and limited number of stages.

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    問題一覧

  • 1

    In turbojet engine the function of the air intake section is to

    deliver a smooth and uniform stream of air to the compressor inlet

  • 2

    Pitot intake is

    divergent duct (front to rear) and best suited for subsonic aircrafts

  • 3

    Pitot intake typical efficiency is

    96-99%

  • 4

    Convergent-Divergent intake,

    fixed duct design convergent then divergent duct. Used to slow down air flow speed to subsonic before compressor

  • 5

    In an aircraft flying at supersonic speed to reduce the air velocity at compressor the variable intake

    throat area decreased

  • 6

    Anti Icing System Function

    used to prevent ice formation of engine intake

  • 7

    Intake & inlet guide vanes are anti iced using

    bled hot air from the compressor

  • 8

    Icing condition when OAT is

    (10°+ C) with visible moisture.

  • 9

    Turboprop intake and propeller use electrical heater mats

    operated part continuous & part intermittent

  • 10

    The advantage of electrical anti-icing system used on engine inlets is

    to minimal loss of engine power or thrust

  • 11

    The centrifugal compressor is ideally suited

    to reverse flow turboprop engines

  • 12

    double entry compressor problem is

    difficulty in designing.

  • 13

    Compressor stage

    is a raw of rotor and a raw of stator

  • 14

    Stator

    increase pressure and control the direction of airflow.

  • 15

    Rotor

    increase air velocity

  • 16

    Compressor blades and diameter getting smaller (front to rear) to maintain........ through the compressor.

    axial velocity

  • 17

    ......... is the ratio between compressor outlet pressure to compressor inlet pressure

    Compressor pressure ratio

  • 18

    The primary factor

    that control the pressure ratio is number of stages in the compressor

  • 19

    The highest gas pressure through gas turbine engine

    at compressor outlet

  • 20

    Root

    is lowest stagger angle at the root

  • 21

    Compressor RPM is

    limited by blade tip speed

  • 22

    To calculate compressor outlet pressure you need to

    multiply inlet pressure with compression ratio

  • 23

    A combination type (Hybrid compressor) used in

    small gas turbine engines with reverse flow combustion

  • 24

    Engine design point is the point which engine will operate during most of its service,

    it is based on cruise speed and altitude (air density)

  • 25

    Twin spool compressor is more

    flexibility of operation and greater resistance to surge

  • 26

    Low pressure compressor runs at

    lower RPM than high pressure compressor

  • 27

    Single spool compressor is

    less efficient

  • 28

    Variable stator vanes and bleed valve used to

    avoid surge.

  • 29

    In a centrifugal flow compressor the high efficiency of compressor achieved by

    keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage

  • 30

    The function of snubber mid span shroud used on fan blade

    to support fan blade and prevent aerodynamic instability

  • 31

    centrifugal compressor Advantage .

    Simple ,Low weight & cost and High pressure rise per stage

  • 32

    Centerifugal compressor Disadvantage

    Large frontal area and limited number of stages.