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Module 14 - Example Questions > Examples > Flashcards

Examples Flashcards

1
Q

The operating principle of air passing through a gas turbine engine is based on?

A

Newton’s Third Law of Motion

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2
Q

The Brayton is plotted against changes in?

A

Pressure and volume

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3
Q

Gas flow in the propelling nozzle:

a) reaches a supersonic speed of Mach 1.1 when the nozzle is choked
b) becomes subsonic when the nozzle is choked
c) accelerates until the nozzle is choked

A

Accelerates until the nozzle is choked

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4
Q

Power is the rate of doing work?

A

With time taken into account

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5
Q

In a reverse flow turbo prop engine, the engine reverses the gas flow:

a) after the turbine to increase power output
b) before the turbine to reduce engine size
c) to produce reverse thrust on landing

A

Before the turbine to reduce engine size

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6
Q

A choked nozzle produces thrust that is:

a) always present in a running turbojet engine
b) always greater than momentum thrust
c) a proportion of gross thrust

A

A proportion of gross thrust

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7
Q

Bypass ratio of a turbo fan engine is the ratio between?

A

The volume of air between the fan and the core engine

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8
Q

The largest pressure change in air passing through an engine occurs in the?

A

Compressor of a turbojet engine

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9
Q

Operation of an engine at a fixed RPM at take off causes:

a) low thrust when high humidity is present
b) excess thrust when temperature is high
c) low thrust when low temperature is present

A

Low thrust when high humidity is present

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10
Q

A pitot intake is:

a) more efficient at high supersonic speeds
b) unaffected by oblique shock waves at the intake lip
c) less affected by aircraft attitude changes

A

Less affected by aircraft attitude changes

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11
Q

A variable throat intake is required to accommodate the:

a) changing volume of air at higher and lower aircraft speeds
b) changing pressure due to temperature decrease
c) changes in aircraft altitude

A

Changing volume of air at higher and lower aircraft speeds

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12
Q

Engine compressor stall may be induced during rapid attitude changes if the aircraft has:

a) engine pods mounted under the wings
b) engine intakes mounted close to the fuselage
c) long engine intakes

A

Engine intakes mounted close to the fuselage

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13
Q

A centrifugal compressor diffuser:

a) is fixed and converts pressure energy into kinetic energy
b) rotates and induces a change in airflow direction
c) converts kinetic energy into pressure energy

A

Converts kinetic energy into pressure energy

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14
Q

Axial flow compressor blade angles are:

a) fixed and are correct for take-off RPM
b) variable and are correct for take-off RPM
c) fixed and are incorrect for take-off RPM

A

Fixed and are incorrect for take-off RPM

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15
Q

Compressor stall can be recognised by:

a) exhaust gas temperature creeping higher and slow fluctuation in N2
b) banging in the intake along with a rapid rise in engine gas temperature
c) banging in the jet pipe along with an engine pressure ratio rise

A

Banging in the intake along with a rapid rise in engine gas temperature

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16
Q

Combustion chamber airflow is divided between combustion and cooling approximately:

a) 20% combustion and 80% cooling
b) 30% cooling and 70% combustion
c) 60% cooling and 40% combustion

A

20% combustion and 80% cooling

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17
Q

A combustion chamber is usually cooled by:

a) impingement air on the inside surface only
b) HP core air on the inside and outside surfaces
c) By-pass air producing or boundary layer on inside surface only

A

HP core air on the inside and outside surfaces

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18
Q

Turbine blades employing fir tree fixing are:

a) stiffened by centrifugal loading when the turbine is rotating
b) locked into place by a grub locking screw
c) manufactured in sets to increase blade stiffness

A

Stiffened by centrifugal loading when the turbine is rotating

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19
Q

Nozzle guide vanes are cooled by:

a) HP compressor delivery air at compressor delivery temperature
b) combustion chamber cooling air at turbine entry temperature
c) combustion chamber cooling air

A

HP compressor delivery air at compressor delivery temperature

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20
Q

Thrust reverse may be selected at:

a) high aircraft speeds and high engine power settings
b) low aircraft speeds and any power setting
c) landing speeds and engine at idle power settings

A

Landing speeds and engine at idle power settings

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21
Q

One of the main features of thrust reverser safety devices is to:

a) allow deployment at cruise power settings only
b) ensure deployment of at least one engine
c) make an uncommanded deployment unlikely

A

Make an uncommanded deployment unlikely

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22
Q

The noise emitted by a propelling nozzle is influenced the greatest by the:

a) velocity of exit gases with the nozzle choked
b) pressure within the nozzle
c) nozzle cross sectional area

A

Velocity of exit gases with the nozzle choked

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23
Q

The main contributory factors causing turbine blade creep are high:

a) temperature and tensile loading
b) RPM and torque loading
c) RPM and high gas velocity

A

Temperature and tensile loading

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24
Q

In a free turbine engine, there is a:

a) clutch between the compressor and the power output shaft
b) turbine which is connected to the output drive only
c) mechanical connection between the free turbine and the compressor

A

Turbine which is connected to the output drive only

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25
Q

Fan RPM at take-off is:

a) lower than HP compressor RPM
b) higher than HP compressor RPM
c) essentially constant for all take-offs

A

Lower than HP compressor RPM

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26
Q

An increase in relative humidity:

a) increase mass flow and thrust
b) increases the quantity of water entering the engine
c) decreases mass flow and thrust

A

Decreases mass flow and thrust

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27
Q

Thrust can be defined as:

a) reaction on the engine static components
b) reaction on the engine rotating components
c) reaction in the static and rotating components

A

Reaction in the static and rotating components

28
Q

Pressure thrust is developed at the:

a) propelling nozzle
b) exhaust nozzle
c) combustion chamber

A

Propelling nozzle

29
Q

Net thrust is:

a) momentum thrust plus pressure thrust
b) gross thrust minus momentum drag
c) momentum drag plus gross thrust

A

Gross thrust minus momentum drag

30
Q

The passage between adjacent nozzle guide vanes form a:

a) parallel duct
b) convergent duct
c) divergent duct

A

Convergent duct

31
Q

On an axial flow, dual compressor forward fan engine, the fan turns the same speed as the:

a) high pressure compressor
b) low pressure turbine
c) forward turbine wheel

A

Low pressure turbine

32
Q

A by-pass engine LP compressor:

a) supplies less air than is required for combustion
b) supplies more air than is required for combustion
c) supplies only the required quantity for combustion

A

Supplies more air than is required for combustion

33
Q

A turbo jet engine gives:

a) small acceleration to a large mass of air
b) large acceleration to a small mass of air
c) large acceleration to a large weight of air

A

Large acceleration to a small mass of air

34
Q

A jet engine derives its thrust by:

a) drawing air into the compressor
b) impingement of the propelling gases on the outside air
c) reaction of the propelling gases

A

Reaction of the propelling gases

35
Q

In a reverse flow system, the last stage of an axial flow compressor is often centrifugal, this is to:

a) provide initial turning of the airflow
b) prevent compressor surge
c) increase the temperature rise

A

Provide initial turning of the airflow

36
Q

Ram effect due to the aircraft forward speed will cause the efficiency of the engine to:

a) remain constant
b) increase
c) decrease

A

Increase

37
Q

The efficiency of a gas turbine engine at altitude:

a) decreases
b) increases
c) remains constant

A

Increases

38
Q

A bypass ratio of 5:1 indicates that the bypass flow is:

a) equal to 1/5 of the hot stream
b) five times the cold stream
c) five times the hot stream

A

Five times the hot stream

39
Q

In a turbo jet engine, combustion occurs at:

a) constant velocity
b) constant volume
c) constant pressure

A

Constant pressure

40
Q

The working fluid of a gas turbine engine is:

a) air
b) gasoline
c) kerosene

A

Air

41
Q

As subsonic air flows through a convergent nozzle, the velocity:

a) increases
b) decreases
c) remains constant

A

Increases

42
Q

The stator vanes in an axial flow compressor:

a) convert velocity energy into pressure energy
b) convert pressure energy into velocity energy
c) direct air into the first stage rotor vanes at the proper angle

A

Convert velocity energy into pressure energy

43
Q

What units in a gas turbine engine aid in stabilisation of the compressor during low thrust engine operations:

a) bleed air valves
b) stator vanes
c) inlet guide vanes

A

Bleed air valves

44
Q

During the high RPM range of an axial flow gas turbine engine, in what position are the variable intake guide vanes and bleed valves:

a) at maximum swirl position, bleed valves open
b) at maximum swirl position, bleed valves closed
c) at minimum swirl position, bleed valves closed

A

At minimum swirl position, bleed valves closed

45
Q

The hydromechanical unit receives engine pressure and thrust lever position as an electrical signal to control the:

a) solenoid operated bore cooling valves
b) motor operated variable stator vanes
c) solenoid operated eleventh stage cooling valve

A

Motor operated variable stator vanes

46
Q

Air data is fed to a FADEC system:

a) since more thrust is required at high Mach numbers and high altitude
b) only during cruise in order to achieve efficiencies during this longest phase of flight
c) since the thrust varies with the rate of air mass flow which varies with speed and altitude

A

Since the thrust varies with the rate of air mass flow which varies with speed and altitude

47
Q

Torque measurement is taken from the:

a) free turbine shaft
b) reduction gearbox
c) prop shaft

A

Reduction gearbox

48
Q

Of the following, which engine type would most likely have a noise suppressor unit installed:

a) turboprop
b) turbojet
c) turboshaft

A

Turbojet

49
Q

Bleed valves are normally spring loaded to the:

a) closed position
b) mid position
c) open position

A

Open position

50
Q

A fixed throttle with increased mass airflow:

a) EPR goes up
b) EPR goes down
c) EPR remains constant

A

EPR remains constant

51
Q

When a volume of air is compressed:

a) no heat is lost or gained
b) heat is lost
c) heat is gained

A

Heat is gained

52
Q

On a FADEC engine, the EEC:

a) has electronic control of the hydro-mechanical fuel control unit in all modes
b) has electronic control of the hydro-mechanical fuel control in some modes
c) has mechanical control of the hydro-mechanical fuel control systems

A

Has electronic control of the hydro-mechanical fuel control unit in all modes

53
Q

Compression occurs:

a) across rotors
b) across stators
c) across stators and rotors

A

Across rotors and stators

54
Q

On a FADEC engine, the channel reset:

a) always selects A channel
b) selects standby which becomes active on the next start
c) selects B channel

A

Selects standby which becomes active on the next start

55
Q

HEIU works by:

a) a contact breaker
b) a discharging capacitor
c) AC busbar

A

A discharging capacitor

56
Q

On an EGT thermocouple system, the hot junction:

a) is placed downstream of the combustion chamber
b) is placed upstream of the combustion chamber
c) is placed in the cockpit

A

Is placed downstream of the combustion chamber

57
Q

Increasing ram effect with increased speed:

a) reduces thrust due to reduced turbine temperature
b) reduces thrust due to reduced compressor efficiency
c) increases thrust due to increased maximum airflow

A

Increases thrust due to increased maximum airflow

58
Q

On an RPM system using a synchronous generator, the pointer is deflected by:

a) potentiometer
b) AC servomotor
c) wheatstone bridge

A

AC servomotor

59
Q

A high bypass engine results in:

a) overall slower airflow and greater propulsive efficiency
b) overall faster airflow
c) greater propulsive efficiency

A

Overall slower airflow and greater propulsive efficiency

60
Q

Shrouded blades allow:

a) higher turbine inlet temperatures
b) thinner more efficient blade sections to be used
c) smaller inlets to be used

A

Thinner more efficient blade sections to be used

61
Q

NGV form:

a) parallel duct
b) convergent duct
c) divergent duct

A

Convergent duct

62
Q

In the combustion chamber:

a) pressure static and volume remains constant
b) pressure static decreases slightly and volume increases
c) pressure static and volume decreases

A

Pressure static decreases slightly and volume increases

63
Q

The drag cup in a tachogenerator is balanced by:

a) calibrated hairspring
b) adjustment screw
c) adjustable counterbalance weights

A

Calibrated hairspring

64
Q

In a choked nozzle, velocity increases:

a) pressure decreases
b) pressure increases
c) density decreases

A

Pressure increases

65
Q

When the engine is not running, the EPR gauge shows 1.0, then:

a) the transmitter is faulty
b) it is normal
c) the receiver is faulty

A

It is normal

66
Q

Fuel flow indication is taken from:

a) after the fuel heater
b) after the HP pump
c) after the LP pump

A

After the HP pump

Module 14 - Example Questions (1 decks)

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