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CDCs (Test May 3, 2015) > Volume 2 (Engine Theory and Construction) > Flashcards

Volume 2 (Engine Theory and Construction) Flashcards

0
Q

“An unbalanced force on a body produces or tends to produce acceleration in the direction of the force and that the acceleration, if any, is directly proportional to the force and inversely proportional to the mass of the body.” This statement is

A

Newton’s second law of motion

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1
Q

Which type of duct would decrease the velocity and increase the pressure of a gas as it passes through?

A

Divergent

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2
Q

What does fuel for an engine represent?

A

Potential energy

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3
Q

Which section of a jet engine continually supplies air and maintains pressure?

A

Compressor

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4
Q

Which section of a jet engine introduces and burns fuel?

A

Combustion

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5
Q

Which section of a jet engine keeps the compressor rotating?

A

Turbine

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6
Q

Through which section of a jet engine is energy expended into the atmosphere, resulting in thrust?

A

Exhaust

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7
Q

How many British thermal units (Btu) does the heat content per pound of kerosene produce?

A

18,500

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8
Q

To measure barometric pressure, you would use a

A

barometer

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9
Q

What is the sea-level atmosphere pressure in pounds per square inch (psi) at “standard day” conditions?

A

14.7 psi

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10
Q

What effect does moisture content or humidity have on density of air in a jet engine?

A

More moisture, less dense

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11
Q

What effect does the divergent design of a diffuser have on air pressure in a jet engine?

A

Increases pressure

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12
Q

The air temperature of a jet engine gradually rises across the compressor to the diffuser outlet as a result of

A

compression

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13
Q

Where is the highest point of temperature reached in a jet engine?

A

Combustion section

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14
Q

Which jet engine component meters fuel for combustion?

A

Fuel control

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15
Q

What is the required velocity for air and gases flowing through a jet engine?

A

Greater velocity exiting than entering

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16
Q

What is the general flow of gases from the combustion chamber of the jet engine?

A

Parallel to the axis of the rotor shaft

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17
Q

What directs the gases onto the first-stage turbine wheel blades in a jet engine?

A

Turbine stator

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18
Q

When two or more turbine wheels are used in a jet engine, which component is placed directly in front of each turbine wheel?

A

Turbine stator (nozzle diaphragm)

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19
Q

The operation of any gas turbine engine, regardless of type, requires the provisions to be made for three major functions. What are they?

A

Compression of air, expansion of air by burning fuel, and extraction of power from gases for driving the compressor and engine driven accessories

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20
Q

The three major sections of all jet engines are compressor, combustion, and

A

turbine

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21
Q

Vane-type fuel pumps used in jet engines are similar to

A

sliding-vane air compressors

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22
Q

Which condition reduces the efficiency of a centrifugal compressor?

A

Pressure pulsations

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23
Q

A constructional feature of the centrifugal compressor is that the impeller

A

is forged as a single unit

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24
Q

In a dual-spooled compressor, revolutions per minute (rpm) of the N2 compressor are determined by the

A

fuel control

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25
Q

The jet engine compressor that is cheaper to manufacture is the

A

centrifugal type, because of its fewer parts

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26
Q

Which is a constructional feature of an axial-flow compressor casing?

A

Split horizontal centerline

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27
Q

The percentage of combustion efficiency of a gas turbine is usually between

A

95 and 100

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28
Q

Which facet of jet engine design helps prevent igniter plug fouling?

A

Directing air around the plug

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29
Q

Carbon monoxide gas is poisonous and odorless, and has

A

no color

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30
Q

What is the most chemically correct ratio for burning fuel in a combustion chamber of a jet engine?

A

15:1

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31
Q

The excess airflow that is not burned in the combustion section of the jet engine is used to

A

cool the burner surfaces

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32
Q

The inner and outer surfaces of an annular-type combustion chamber are formed by

A

interlocking stainless-steel bands

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33
Q

Fuel that accumulates after a failed engine start is

A

drained overboard by a drain system

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34
Q

The parts of a can-annular combustion section must be removed in a specific order because of the

A

combustion chamber crossover tubes

35
Q

What is the most common type of fuel nozzle system?

A

Pressure-atomizing

36
Q

Three types of turbine and vane assemblies used in jet engines are impulse, reaction, and

A

reaction-impulse

37
Q

In the reaction type turbine, what in the design causes the rotor to burn?

A

The reduction in pressure and the increase in velocity of the exhaust gases occur in the passage between the rotor blades

38
Q

The “fir tree” method of attaching turbine blades (buckets) to the turbine rotor disc is preferred because

A

of the temperature differential between the turbine rotor disc and the blades

39
Q

Which method of attaching the turbine blades (buckets) to the turbine rotor disc is used most frequently?

A

Series of grooves or notches broached in the rim of the turbine rotor disc

40
Q

The fan exhaust duct connects the turbine outlet and the

A

jet nozzle

41
Q

The design of an exhaust duct straightens the exhausts gases as it leaves the last stage of the turbine section to provide for

A

larger total thrust in a more efficient manner

42
Q

The rear opening of the exhaust duct on the jet engine is referred to as the

A

exhaust nozzle

43
Q

Some jet engines are trimmed/adjusted to their correct exhaust gas temperature by an alteration of what?

A

Exhaust nozzle area

44
Q

How many different types of loads can be imposed on a jet engine bearing?

A

Three

45
Q

Before inspecting new jet engine bearings, you should

A

remove the preservative coating

46
Q

Next to contamination and improper lubrication, what is the greatest enemy of anti friction bearings?

A

Improper removal

47
Q

The most commonly used bearing removal tools include

A

arbor presses and bearing pullers

48
Q

Which type of defect appears on bearings as a result of bearing parts striking together?

A

Nicks

49
Q

Which type of bearing defect results from inadequate lubrication?

A

Galling

50
Q

Excessive bearing wear can usually be detected by

A

roughness of the metal

51
Q

Before you install separable bearings in a jet engine, you must make sure the

A

bearings are a matched set

52
Q

To cause an accessory in a jet engine to operate at its most optimum speed, design engineers must

A

change the gear ratio

53
Q

On an F108 engine, the radial drive shaft connects the core engine to the

A

accessory drive assembly

54
Q

Which F108 major engine module provides for mounting of the front of the engines to the airframe?

A

Fan major module

55
Q

Power to drive the accessory gearbox (AGB) on the F108 engine is transmitted from the

A

accessory major module

56
Q

F108 structural rigidity is obtained with a short length and by having only two main structures that are called

A

mainframes

57
Q

Primary airflow in the F108 engine is through all of the following components except the

A

accessory gearbox

58
Q

Which types of load does the No. 2 bearing take up in the F108 engine?

A

Radial

59
Q

The F108 engine has an air duct through the inside diameter of the core compressor rotor that forms a flow path for

A

pressurizing and cooling airflow

60
Q

On the F108 engine, the combustion chamber is of which design type?

A

Annular

61
Q

On the F108 engine, the low-pressure turbine (LPT) shaft assembly connects the fan shaft with the

A

LPT rotor

62
Q

On the F108 engine, as gases flow through the convergent passageways of the low-pressure turbine (LPT) nozzle their pressure drops, and their axial velocity

A

increases

63
Q

The F108 engine turbine frame is the engine rear main structural component, and it supports the

A

LPT rotor rear section

64
Q

On the F108 engine, what connects the inlet gearbox (IGB) to the transfer gearbox (TGB) bevel gears?

A

Radial drive shaft

65
Q

On the F108 engine, how is the transfer gearbox (TGB) mounted to the fan case?

A

By a single clevis-and-link rod-mounting arrangement

66
Q

On the TF34 jet engine, the fan forward shaft, bolted to the aft side of the double disc, is supported by

A

both the No. 1 thrust ball bearing and the No. 2 roller bearing

67
Q

The single-stage fan rotor on the TF34 jet engine provides what percentage of the engines thrust?

A

85 percent

68
Q

On the TF34 jet engine, which strut does the fan speed pickup protrude through to the number two bearing locknut?

A

9 o’clock

69
Q

The compressor inlet temperature sensor is mounted on the outer surface of the splitter nose at what “o’clock” position on the TF34 jet engine?

A

9 o’clock

70
Q

How many stages of compressor blades are in the TF34 engine?

A

14

71
Q

Why is the compressor stator case split horizontally?

A

To allow access to the compressor rotor

72
Q

What stages of compressor vanes are variable in the TF34 engine?

A

Stages 1-5

73
Q

What type of combustion liner does the TF34 have?

A

Annular

74
Q

On the TF34 jet engine, the first-stage nozzle consists of 24 cast segments with how many vanes in each segment?

A

2

75
Q

What is the purpose of the low-pressure turbine (LPT) transition assembly?

A

To funnel hot gases from the HPT rotor to the larger diameter LPT rotor

76
Q

On the TF34 jet engine, which strut is used to port seventh stage compressor air into the C-sump area to pressurize the number six carbon seal?

A

12 o’clock

77
Q

Which of these items does not belong to the TF34 engine accessories section?

A

Compressor stator

78
Q

In order to facilitate borescoping the engine, what is provided for rotating the high-pressure rotor system and where is it located?

A

A gearbox cranking pad located between the lube and fuel pump pads

79
Q

Which one of these compressor section subsystems does not belong on the F117-PW-100 jet engine?

A

High-pressure turbine (HPT) group

80
Q

The high-pressure compressor (HPC) group on the F117-PW-100 jet engine consists of how many rotor stages and how many stages of rotors surrounded by a two section titanium and steel case?

A

12 rotors and 12 stators

81
Q

How many exit vanes make up the compressor exit stator assembly on the F117-PW-100 jet engine?

A

72

82
Q

The combustion chamber assembly provides the optimum environment for combustion and directs the flow of

A

hot gases to the turbine nozzle

83
Q

Which of these turbine section subsystems does not belong on the F117-PW-100 jet engine?

A

Low-pressure compressor (LPC) nozzle group

84
Q

Which one of these components is not an engine accessory component on the F117-PW-100 jet engine?

A

Radial drive shaft

85
Q

Which one of the listed components is not an aircraft accessory component on the F117-PW-100 jet engine?

A

Low-pressure turbine (LPT) module

CDCs (Test May 3, 2015) (3 decks)

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