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AIRCRAFT ENGINES AND SYSTEMS > TURBINE TEST 2 > Flashcards

TURBINE TEST 2 Flashcards

1
Q 
Under normal operating conditions, what point in a jet engine has the highest temperature?
  The combustion chamber inlet.
  The exhaust nozzle.
  The turbine section inlet.
  The turbine discharge section.
A

The turbine section inlet.

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2
Q

The fan rotational speed of a dual axial compressor forward fan engine is the same as the:
None of the above.
Low-pressure compressor.
High-pressure compressor.

A

Low-pressure compressor.

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3
Q

The primary function of the compressor section in a gas turbine engine is:
Turn the turbines through a mechanical connection on a common shaft.
Compress air which is used to pressurize the cabin.
Provide bleed air for the anti-ice/deice system.
Progressively “squeeze” air in preparation for combustion.

A

Progressively “squeeze” air in preparation for combustion

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4
Q 
What is not a typical use for engine bleed air?
  Windshield de-ice.
  Wing anti-ice.
  Crossbleed engine start.
  Engine anti-ice.
A

Windshield de-ice.

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5
Q 
Ram effect increases thrust, intake pressure, and:
  Drag
  Air Mass Flow
  Cooling Effect
  Compression Rotation
A

Air Mass Flow

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6
Q

In the Combustion/Burner section of an engine, primary air is used for what purpose?
Mixing with fuel prior to combustion.
Serving as afterburner.
Flowing around the chamber for cooling and to control the flame.
Turning the turbine connected to the fan blades.

A

Mixing with fuel prior to combustion.

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7
Q

Which of the following could cause a compressor stall?
Low pressure in subsequent compressor stages.
A bleed air valve stuck in the open position.
Insufficient intake air.
Engine rpm is too low.

A

Insufficient intake air.

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8
Q

Reduction gear ratios within the accessory section are relatively high because:
The rotor operating pressure is so low.
The rotor operating rpm is so low.
The rotor operating pressure is so high.
The rotor operating rpm is so high.

A

The rotor operating rpm is so high.

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9
Q

The function of the exhaust cone assembly of a turbine engine is to:
De-energize airflow.
Disrupt airflow.
Straighten and collect the exhaust gases into a solid exhaust jet.

A

Straighten and collect the exhaust gases into a solid exhaust jet.

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10
Q

In what flight regime would you most likely encounter a compressor stall?
Initial deployment of thrust reversers on landing.
Descent in turbulence.
Takeoff with strong crosswind.
Engine start.

A

Takeoff with strong crosswind.

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11
Q

The factors that affect the thrust of a gas turbine engine include:
Air Density, Airspeed, and Engine RPM.
Airspeed, Weight, CG.
Altitude, Weight, CG.
Intake, Compression, Combustion, Exhaust.

A

Air Density, Airspeed, and Engine RPM.

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12
Q 
What is the first engine instrument indication of a successful start of a turbine engine?
  A rise in the exhaust gas temperature.
  N1 stabilized.
  Rise in oil pressure.
  A rise in oil temperature.
A

A rise in the exhaust gas temperature.

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13
Q 
The most common causes of compression stall are Mechanical Malfunction and:
  Airflow Temperature.
  Airflow Reversal.
  Airflow Distortion.
  Airflow Pressure.
A

Airflow Distortion.

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14
Q

The main systems on a 3-shaft turbine engine are:
Low pressure System, Intermediate Pressure System, High Pressure System.
Compressor System, Combustion System, Exhaust System.
Compressor System, Combustion System, Accessory System.
Air System, Fuel System, Ignition System.

A

Low pressure System, Intermediate Pressure System, High Pressure System

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15
Q 
What turbine engine section provides for proper mixing of the fuel and air?
  Turbine Section.
  Exhaust Section.
  Inlet Section.
  Combustion section.
A

Combustion section.

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16
Q 
Which of these items would not normally be fitted to the engine accessory system?
  N1
  Engine driven fuel pump
  N2
  EGT/TIT
A

EGT/TIT

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17
Q

Turbine blades are generally more susceptible to operating damage than compressor blades because of:
Exposure to high pressure.
Exposure to high velocities.
Exposure to high temperatures.

A

Exposure to high temperatures.

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18
Q

Your maintenance crew informs you that the accessory drive gear train has sheared and will likely cause a large delay. What is the primary function of the accessory section of a turbine engine?
It provides space for the mounting of accessories necessary for operation and control of the aircraft air intake section.
It provides space for the mounting of accessories necessary for operation and control of the engine.
It provides space for the mounting of accessories necessary for operation and control of the aircraft compressor section.
It provides space for the mounting of accessories necessary for operation and control of the aircraft turbine section.

A

It provides space for the mounting of accessories necessary for operation and control of the engine.

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19
Q

Turbine nozzle diaphragms located on the upstream side of each turbine wheel, are used in the gas turbine engine to:
Decrease the velocity of the heated gases flowing past this point.
Increase the velocity of the cooled gases flowing past this point.
Increase the velocity of the heated gases flowing past this point.

A

Increase the velocity of the heated gases flowing past this point.

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20
Q 
What are the two functional elements in a centrifugal compressor?
  Compressor and diffuser.
  Impeller and diffuser 
  Impeller and compressor.
  Diffuser and combustion.
A

Impeller and diffuser.

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21
Q 
Oil extracts the most heat from which turbine engine components?
  Compressor bearings.
  Constant speed drive bearings.
  Turbine bearings.
  Accessory drive bearings.
A

Turbine bearings.

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22
Q 
At what point in an axial-flow turbojet engine will the highest gas pressures occur?
  Exhaust Section.
  At the Inlet.
  Turbine Section.
  At the compressor outlet.
A

At the compressor outlet.

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23
Q 
The section of an engine which increases the energy of the air received from the entrance duct, then discharges into the diffuser section and the combustion chamber is called:
  Stage Turbine.
  Convergent Duct.
  Compressor.
  Divergent Duct.
A

Compressor.

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24
Q

A turbine engine usually has an accessory section gear train given by:
The engine low-pressure compressor through an accessory drive shaft gear coupling.
The engine high-pressure compressor through an accessory drive shaft gear coupling.
The engine high-pressure fan turbine trough an accessory drive shaft gear coupling.
The engine low-pressure fan turbine trough an accessory drive shaft gear coupling.

A

The engine high-pressure compressor through an accessory drive shaft gear coupling.

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25
Q

The diffuser section of a jet engine is located between:
The compressor section and the burner section.
The burner section and exhaust section.
The inlet section and the compressor.
The combustion section and the turbine section.

A

The compressor section and the burner section.

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26
Q

How does a dual axial-flow compressor improve the efficiency of a turbojet engine?
Higher compression ratios can be obtained.
Lower compression and efficiencies.
Higher temperatures.
Higher fuel flows.

A

Higher compression ratios can be obtained.

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27
Q

The primary function of the oil system in the modern gas turbine engine is to:
Move the variable geometry diffusers and inlet guide vanes.
Heat the fuel just prior to entering the fuel filters.
Operate the thrust reversers.
Cool and lubricate the main bearings and accessory drive gears.

A

Cool and lubricate the main bearings and accessory drive gears.

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28
Q

The basic elements of the accessory section of a turbofan engine are:
The engine starter, auxiliary power unit, oil pump and filter, and the gear train, which is housed inside the accessory case.
The accessory gearbox, which has machined mounting pads for the engine-driven accessories, and the gear train, which is housed outside the accessory case.
The engine starter, auxiliary power unit, oil pump and filter, and the gear train, which is housed outside the accessory case.
The accessory gearbox, which has machined mounting pads for the engine-driven accessories, and the gear train, which is housed inside the accessory case.

A

The accessory gearbox, which has machined mounting pads for the engine-driven accessories, and the gear train, which is housed inside the accessory case.

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29
Q

The turbine ignition system:
Needs to be timed to spark during an exact point in the operational cycle.
Does not need to be timed to spark during an exact point in the operational cycle.
Needs to be turned on during an exact point in the operational cycle.
Does not need to be turned on during an exact point in the operational cycle.

A

Does not need to be timed to spark during an exact point in the operational cycle.

30
Q 
On a jet engine. The process of taking high velocity, low pressure air, and turning it into low velocity, high pressure air is the primary function of the:
  Diffuser.
  Combustion chamber.
  Turbine.
  Compressor.
A

Diffuser.

31
Q

Which of these is the best indication that the engine has seized in flight?
Oil pressure at zero.
Residual voltage on the associated generator.
Fuel flow abnormally high.
EGT/TIT at or near zero.

A

Oil pressure at zero.

32
Q 
On a turbofan engine the amount of air that bypasses the gas generator in comparison with the amount of air that passes through the gas generator is called:
  Bypass Flow.
  Bypass Ratio.
  Bypass Differential.
  Bypass Pressure.
A

Bypass Ratio.

33
Q

How does “ram effect” affect performance of a turbine engine?
Increases pressure at the engine inlet, thus increasing performance.
Increases temperature at the engine inlet, thus increasing performance.
Increases pressure at the engine inlet, thus decreasing performance.
Decreasing air density at the engine inlet, thus decreasing performance.

A

Increases pressure at the engine inlet, thus increasing performance.

34
Q 
Under normal operating conditions, what point in a jet engine has the highest static pressure?
  The exhaust nozzle.
  The turbine discharge section.
  The turbine inlet section.
  The combustion chamber inlet.
A

The combustion chamber inlet.

35
Q

What is the purpose of the diffuser section in a turbine engine?
To increase pressure and reduce velocity.
To decrease pressure and increase velocity.
To maintain constant velocity.
To increase pressure and temperature.

A

To increase pressure and reduce velocity.

36
Q

Since turbine ignition system are operated mostly for brief period during the engine-starting cycle they are:
As a rule, more typical of a diesel engine ignition system design
As a rule, less trouble-free than the typical reciprocating engine ignition system.
As a rule, more typical of a reciprocating engine ignition system design.
As a rule, more trouble-free than the typical reciprocating engine ignition system.

A

As a rule, more trouble-free than the typical reciprocating engine ignition system.

37
Q

The turbine section of an engine is responsible for:
Providing the means for proper mixing of the fuel and air prior to combustion.
Driving the compressor and the accessories.
Directing the flow of hot gases rearward to cause a high exit velocity.
Dividing the airflow into primary and secondary air.

A

Driving the compressor and the accessories.

38
Q

Which statements are true regarding aircraft engine propulsion?

  1. An engine driven propeller imparts a relatively small amount of acceleration to a large mass of air.
  2. Turbojet and turbofan engines impart a relatively large amount of acceleration to a smaller mass of air.
  3. In modern turboprop engines, nearly 50 percent of the exhaust gas energy is extracted by turbines to drive the propeller and compressor with the rest providing exhaust thrust.
    All of the statements are true.
    Only number 1 is true.
    None of the statements are true.
    1 and 2 are true.
A

1 and 2 are true.

39
Q

One function of the nozzle diaphragm in a turbine engine is to:
Direct the flow of gases to strike the turbine blades at the desired angle.
To compress air flow.
To assist with combustion.

A

Direct the flow of gases to strike the turbine blades at the desired angle.

40
Q

When starting a turbine engine,
A hung start is indicated if the compressor gas temperature exceeds specified limits.
A hot start is indicated if the exhaust gas temperature exceeds specified limits.
A hung start is indicated if the exhaust gas temperature exceeds specified limits.
A hot start is indicated if the exhaust pressure exceeds specified limits.

A

A hot start is indicated if the exhaust gas temperature exceeds specified limits.

41
Q 
The reduction gearing within the accessory section casing provides suitable drive speed for:
  The engine air intake section.
  The engine turbine section.
  Each engine accessory or component.
  The engine compressor section.
A

Each engine accessory or component.

42
Q

What is one purpose of the stator blades in the compressor section of a turbine engine?
To raise the temperature prior to the diffuser.
Control the direction of the airflow.
To Increase the velocity of the airflow.

A

Control the direction of the airflow.

43
Q

What effect, if any, does high ambient temperature have upon the thrust of a turbine engine?
The thrust will be reduced due to the increase in air density.
The thrust will be reduced due to the decrease in air density.
Thrust will remain the same, but turbine temperature will be higher.
Thrust will be higher because more heat energy is extracted from the hotter air.

A

The thrust will be reduced due to the decrease in air density.

44
Q 
Which engine instrument will best indicate engine damage?
  N1
  EGT
  N2
  Fuel Flow
A

N2

45
Q

Engine pressure ratio is determined by:
Multiplying engine inlet total pressure by turbine outlet total pressure.
Dividing turbine outlet total pressure by ambient air pressure.
Dividing turbine outlet total pressure by engine inlet total pressure
Dividing engine inlet total pressure by turbine outlet total pressure.

A

Dividing turbine outlet total pressure by engine inlet total pressure

46
Q 
What factors increase thrust from a turbofan engine?
  Decreased atmospheric pressure.
  Increased airspeed.
  Decreased humidity.
  Increased temperature.
A

Increased airspeed.

47
Q

An advantage of the axial-flow compressor is its-
High peak efficiency.
Lower compression.
Lower temperatures.

A

High peak efficiency.

48
Q 
Which engine component(s) would be most damaged by excessive EGT?
  Exhaust nozzle.
  Turbine blades.
  Burner section.
  Compressor blades.
A

Turbine blades.

49
Q

The primary function of the turbine section in a gas turbine engine is to:
Help direct and compress the flow of air between each set of rotor blades.
Drive the compressors through common shafts.
Accelerate air from the combustion section and subsequently provide thrust through the exhaust nozzles.
Progressively “squeeze” air in preparation for combustion.

A

Drive the compressors through common shafts.

50
Q

A principle disadvantage of a centrifugal flow compressor compared to an axial flow compressor on a turbine engine is:
It is more susceptible to foreign-object damage.
Its total compression section is heavier.
The provision of more than one or two stages is rarely feasible.
It is more expensive to manufacture.

A

The provision of more than one or two stages is rarely feasible.

51
Q

If the oil cooler relief valve should stick in the open position, what would be the probable result?
Increased oil temperature.
Decreased oil temperature.
Pressurization of the case and oil leakage.
Increase in oil pressure.

A

Increased oil temperature.

52
Q

Describe the purpose of the compressor section of a turbojet engine.
Provide the engine’s thrust through compression.
Increase the speed of the air flowing through the engine.
Turn the turbine via their common shaft.
Increase the pressure of the air flowing through the engine.

A

Increase the pressure of the air flowing through the engine.

53
Q

What are the two basic elements of the turbine section in a turbine engine?
Stator and rotor.
Rod and compression tabs.
Blades and Rods.

A

Stator and rotor.

54
Q 
Where is the highest pressure in a gas turbine?
  Compressor inlet.
  Engine exhaust nozzle.
  Turbine discharge.
  Compressor discharge.
A

Compressor discharge.

55
Q

A principle advantage of an axial flow compressor compared to a centrifugal flow compressor on a turbine engine is:
It requires relatively low inlet velocities.
Simplicity.
Ability to handle large volumes of airflow.
High compressor ratio per stage.

A

Ability to handle large volumes of airflow.

56
Q 
Where is the highest gas pressure in a turbojet engine?
  Exhaust section.
  Low Pressure section.
  Turbine section.
  In the entrance of the burner section.
A

In the entrance of the burner section.

57
Q 
In a gas turbine engine, combustion occurs at a constant:
  Temperature.
  Speed.
  Velocity.
  Pressure.
A

Pressure.

58
Q 
Describe the purpose of the turbine section of a turbojet engine.
  Heat the air.
  Compress the air.
  Maintain a proper burn of the fuel.
  Turn the compressor.
A

Turn the compressor.

59
Q 
What is a primary design limitation of a turbojet engines?
  Compressor outlet temp.
  Compressor inlet temp.
  Turbine outlet temp.
  Turbine inlet temp.
A

Turbine inlet temp.

60
Q

In a gas turbine engine the inlet, compressor, and diffuser sections are responsible for?
Transferring compressed airflow into kinetic energy.
Building potential energy of the airflow.
Transferring static energy into thrust.
Building static energy of the airflow.

A

Building potential energy of the airflow.

61
Q

Normally, the turbine ignition system:
Is used to ignite the fuel in the combustor and then it is switched off.
Is used to turn the turbine fan, ignites the fuel in the combustion section and is then switched to continuous.
Is used to ignite the fuel in the combustor and then it is switched to continuous.
Is used to turn the turbine fan, ignites the fuel in the combustion section and is then switched off.

A

Is used to ignite the fuel in the combustor and then it is switched off.

62
Q

Non-typical modes of turbine ignition system operation are used for certain flight conditions, such as:
Continuous ignition that is used at a lower voltage and energy level.
Continuous ignition that is used at a higher voltage and energy level.
Generators that are used at a higher voltage and energy level.
Generators that are used at a lower voltage and energy level.

A

Continuous ignition that is used at a lower voltage and energy level.

63
Q

Why are fixed orifice nozzles used in the lubrication system of turbine engines?
To keep pressure on the oil pump, thus preventing air lock.
To provide a relatively constant oil flow to the main bearings at all engine speeds.
To keep pressure on the oil pump, thus preventing oil foaming.
To protect oil seals by preventing excessive pressure from entering the bearing cavities.

A

To provide a relatively constant oil flow to the main bearings at all engine speeds.

64
Q

Which of the following is the ultimate limiting factor of turbine engine operation?
Turbine inlet temperature.
Turbine pressure.
Turbine velocity.

A

Turbine inlet temperature.

65
Q 
The principal method of lubrication on modern aircraft engine is:
  Spray lubrication.
  Mist lubrication.
  Pressure lubrication.
  Splash lubrication.
A

Pressure lubrication.

66
Q

Which statement is true regarding jet engines?
At the lower engine speeds, thrust increases rapidly with small increases in RPM.
At the higher engine speeds, thrust increases rapidly with small increases in RPM.
At the higher engine speeds, thrust decreases rapidly with small increases in RPM.

A

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

67
Q

When starting a turbine engine, a hung start is indicated if the engine
Fails to reach idle RPM.
Required thrust.
Max temperature.

A

Fails to reach idle RPM.

68
Q

What is the function of the stator vane assembly at the discharge end of a typical axial-flow compressor?
To compress air flow.
To straighten airflow to eliminate turbulence.
To increase pressure.

A

To straighten airflow to eliminate turbulence.

69
Q

In the dual axial-flow or twin spool compressor system, the first stage turbine drives the:
Low pressure fan.
N( 2 ) Compressor.
N1 Compressor.

A

N( 2 ) Compressor.

70
Q

The turbine section of a jet engine:
Drives the the N1 fan.
Drives the low pressure fan.
Drives the compressor section.

A

Drives the compressor section.

AIRCRAFT ENGINES AND SYSTEMS (19 decks)

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