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15/5/6

15/5/6
39問 • 1年前
  • Guevara Official
    • 通報

    問題一覧

  • 1

    Diffuser It is a divergent shape located between compressor and combustion chamber

    used to decrease the velocity of the air.

  • 2

    Compressed air is mixed with fuel, in the

    combustion chamber.

  • 3

    Over rich mixture will produce

    exhaust smoke and carbon particles formed inside combustion chamber.

  • 4

    The method used a network of passages between two laminated skins forming the flame tube is

    a transpiration cooling

  • 5

    The purpose of dilution zone in the combustion chamber is

    to protect combustion chamber from melting.

  • 6

    The overall fuel/air ratio entering combustion chamber is approximately

    (45:1 – 130:1)

  • 7

    Reverse Flow Combustion is best suited for

    turbo-prop and turbo-shaft engines.

  • 8

    Combustion in Multiple-can Combustion Chamber occurs in

    two cans by igniter plugs then moved through interconnector tubes to the remaining cans

  • 9

    Compressor outlet and the duct at the forward part of the combustion is

    snout shape.

  • 10

    Another name for can – annular combustion chamber is.

    A tubo-annular.

  • 11

    Can-annular compared to a multiple can design is

    smaller and lighter

  • 12

    Rich mixture that has

    too much fuel for the primary air in the combustion chamber

  • 13

    The best ratio of air fuel mixture within

    the primary dilution zone is 15:1

  • 14

    The primary condition that are necessary for safe and correct combustion

    is correct mixture ratio and air velocity must be slow enough

  • 15

    can annular combustion chamber

    has a set of flame tubes with common outer casing and

  • 16

    Annular combustion chamber

    disadvantages Removal difficult and time consuming

  • 17

    Annular combustion chamber

    advantages; Better thermal load distribution for the turbine

  • 18

    Swirl vanes cause

    air flow vortex and help air fuel mixing

  • 19

    Combustion stability means

    smooth burning coupled with ability to remain alight over a large range of air fuel ratio and air mass flow

  • 20

    Turbine section converting gas stream kinetic energy

    into mechanical energy to drive compressor

  • 21

    Turbine Blades Material

    Nickel alloy.

  • 22

    Impulse type Turbine Blades used in

    (Starter blades)

  • 23

    Impulse-reaction type used in

    (all modern jet engines).

  • 24

    Turbine blade secured to the disc using

    fir tree root with locking plate

  • 25

    Cooling air enters the fir-tree turbine blades though the

    base of the root.

  • 26

    Fir-Tree turbine blades attachment .

    allows slight movement

  • 27

    The space between two nozzle guide vanes forms

    a convergent duct in order to increase velocity.

  • 28

    the cooling air flows through the hollow nozzle vanes and rotor blades

    this method is known as Convection cooling

  • 29

    Blade Twist

    To ensure equal work done all over the blade length (root to tip)

  • 30

    Nozzle Guide Vanes Function

    direct gases in proper angle to first stage turbine nozzle

  • 31

    Nozzle Guide Vanes

    Cooling by ceramic coating and bleed air.

  • 32

    Creep is permanent elongation in rotor blades, resulting of

    thermal stress and high centrifugal force .

  • 33

    Most creep resistant blades are

    single structure blades

  • 34

    ACC cools turbine casing to

    reduce tip losses and improve efficiency in the cruise

  • 35

    Shrouded turbine rotor blades used

    to reduce vibration and improve air flow.

  • 36

    The efficiency of a turbine blade increases proportional, as its

    rotational speed increases

  • 37

    The nozzle guide vanes and at the rotor blades are cooled by the method of

    film cooling .

  • 38

    Running clearance on a turbine disk is kept to a minimum to reduce

    tip losses

  • 39

    advantage of an axial turbine is that it

    allows very high airflow which is needed to create the high thrust of modern engines

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    問題一覧

  • 1

    Diffuser It is a divergent shape located between compressor and combustion chamber

    used to decrease the velocity of the air.

  • 2

    Compressed air is mixed with fuel, in the

    combustion chamber.

  • 3

    Over rich mixture will produce

    exhaust smoke and carbon particles formed inside combustion chamber.

  • 4

    The method used a network of passages between two laminated skins forming the flame tube is

    a transpiration cooling

  • 5

    The purpose of dilution zone in the combustion chamber is

    to protect combustion chamber from melting.

  • 6

    The overall fuel/air ratio entering combustion chamber is approximately

    (45:1 – 130:1)

  • 7

    Reverse Flow Combustion is best suited for

    turbo-prop and turbo-shaft engines.

  • 8

    Combustion in Multiple-can Combustion Chamber occurs in

    two cans by igniter plugs then moved through interconnector tubes to the remaining cans

  • 9

    Compressor outlet and the duct at the forward part of the combustion is

    snout shape.

  • 10

    Another name for can – annular combustion chamber is.

    A tubo-annular.

  • 11

    Can-annular compared to a multiple can design is

    smaller and lighter

  • 12

    Rich mixture that has

    too much fuel for the primary air in the combustion chamber

  • 13

    The best ratio of air fuel mixture within

    the primary dilution zone is 15:1

  • 14

    The primary condition that are necessary for safe and correct combustion

    is correct mixture ratio and air velocity must be slow enough

  • 15

    can annular combustion chamber

    has a set of flame tubes with common outer casing and

  • 16

    Annular combustion chamber

    disadvantages Removal difficult and time consuming

  • 17

    Annular combustion chamber

    advantages; Better thermal load distribution for the turbine

  • 18

    Swirl vanes cause

    air flow vortex and help air fuel mixing

  • 19

    Combustion stability means

    smooth burning coupled with ability to remain alight over a large range of air fuel ratio and air mass flow

  • 20

    Turbine section converting gas stream kinetic energy

    into mechanical energy to drive compressor

  • 21

    Turbine Blades Material

    Nickel alloy.

  • 22

    Impulse type Turbine Blades used in

    (Starter blades)

  • 23

    Impulse-reaction type used in

    (all modern jet engines).

  • 24

    Turbine blade secured to the disc using

    fir tree root with locking plate

  • 25

    Cooling air enters the fir-tree turbine blades though the

    base of the root.

  • 26

    Fir-Tree turbine blades attachment .

    allows slight movement

  • 27

    The space between two nozzle guide vanes forms

    a convergent duct in order to increase velocity.

  • 28

    the cooling air flows through the hollow nozzle vanes and rotor blades

    this method is known as Convection cooling

  • 29

    Blade Twist

    To ensure equal work done all over the blade length (root to tip)

  • 30

    Nozzle Guide Vanes Function

    direct gases in proper angle to first stage turbine nozzle

  • 31

    Nozzle Guide Vanes

    Cooling by ceramic coating and bleed air.

  • 32

    Creep is permanent elongation in rotor blades, resulting of

    thermal stress and high centrifugal force .

  • 33

    Most creep resistant blades are

    single structure blades

  • 34

    ACC cools turbine casing to

    reduce tip losses and improve efficiency in the cruise

  • 35

    Shrouded turbine rotor blades used

    to reduce vibration and improve air flow.

  • 36

    The efficiency of a turbine blade increases proportional, as its

    rotational speed increases

  • 37

    The nozzle guide vanes and at the rotor blades are cooled by the method of

    film cooling .

  • 38

    Running clearance on a turbine disk is kept to a minimum to reduce

    tip losses

  • 39

    advantage of an axial turbine is that it

    allows very high airflow which is needed to create the high thrust of modern engines