問題一覧
1
3 and 5.
2
the same slot
3
should be performed parallel to the length of the blade using smooth contours to minimize stress points.
4
Direct the flow of gases to strike the turbine blades at the desired angle.
5
low-pressure rotor will increase in speed as the compressor load decreases in the lower density air.
6
Turbine, compressor, and combustion.
7
increase and the velocity to decrease.
8
number of compressor stages.
9
number of compressor stages.
10
compressor may be contaminated or damaged.
11
Split-spool, axial-flow.
12
The engine manufacturer.
13
1,2
14
creep
15
field cleaning.
16
increase the velocity of the gas flow.
17
A rise in the exhaust gas temperature.
18
Exhaust
19
erosion damage to the compressor and turbine sections.
20
Combustion section.
21
Rotor and stator.
22
impulse, reaction, and impulse-reaction.
23
vent some of the air overboard to prevent a compressor stall.
24
high peak efficiency.
25
The engine manufacturer.
26
Self-ionizing or shunted-gap type plug.
27
increases
28
a. a hot start is indicated if the exhaust gas temperature exceeds specified limits.
29
on a time or cycle basis.
30
Impeller and diffuser.
31
malfunctioning fuel nozzles.
32
Higher compression ratios can be obtained.
33
both No. 1 and No. 2 are true.
34
neither No. 1 nor No. 2 is true.
35
changing the velocity of the airflow.
36
1,2,5
37
increases
38
Across the leading or trailing edge at a right angle to the edge length.
39
pressure
40
A compressor with vanes on both sides of the impeller.
41
decreases
42
Starter, ignition, fuel.
43
Multiple-can, annular, and can-annular.
44
after the engine has reached self-accelerating speed.
45
Can
46
To straighten airflow to eliminate turbulence.
47
Pt7
48
prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path surfaces.
49
59°F
50
Labyrinth and/or carbon rubbing.
51
a faulty combustion chamber.
52
Turn off the fuel and continue engine rotation with the starter.
53
Engine main bearing distress.
54
convert velocity energy into pressure energy.
55
increase the velocity of the heated gases flowing past this point.
56
allow the turbine wheel to cool before the case contracts around it.
57
The turbine blades are shaped so that their ends form a band or shroud.
58
Variable guide vanes and/or compressor bleed valves.
59
seeks its own best operating speed.
60
In the entrance of the burner section.
61
reduce vibration.
62
1,4
63
Creep
64
Greater pressure ratio.
65
N(2) compressor.
66
stators
67
stator vanes.
68
29.92” Hg.
69
galling
70
Directs the air into the first stage rotor blades at the proper angle.
71
shrouded turbine rotor blades.
72
engine bleed air ducted through the critical areas.
73
Turbine blades.
74
a lean die-out.
75
Acceleration is produced when a force acts on a mass. The greater the mass, the greater the amount of force needed.
76
straighten the airflow and eliminate turbulence.
77
Number of stages in compressor.
78
straighten and collect the exhaust gases into a solid exhaust jet.
79
A reduced blade tip thickness.
80
1,4,5
81
Cracking
82
Impulse-reaction.
83
single entry and double entry.
84
Everybody persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force.
85
drives the compressor section.
86
low-pressure compressor.
87
pressure cycle.
88
The fuel is quickly cut off to the nozzles and the manifolds are drained preventing fuel boiling off as a result of residual engine heat.
89
fails to reach idle RPM.
90
the total pressure at station No. 7.
91
Over temperature condition.
92
Stator and rotor.
93
turbine inlet guide vanes.
94
Stress rupture.
95
decreases
96
To increase pressure and reduce velocity.
97
Turbine inlet temperature.
98
N(2) compressor.
99
Turbine inlet temperature.
100
neither No. 1 nor No. 2 is true.
airlaw
airlaw
ユーザ名非公開 · 119問 · 1年前airlaw
airlaw
119問 • 1年前pcar & afcar
pcar & afcar
ユーザ名非公開 · 80問 · 1年前pcar & afcar
pcar & afcar
80問 • 1年前new set
new set
ユーザ名非公開 · 22問 · 1年前new set
new set
22問 • 1年前human factor
human factor
ユーザ名非公開 · 100問 · 1年前human factor
human factor
100問 • 1年前human factor 2
human factor 2
ユーザ名非公開 · 29問 · 1年前human factor 2
human factor 2
29問 • 1年前Engine instrument system
Engine instrument system
ユーザ名非公開 · 54問 · 1年前Engine instrument system
Engine instrument system
54問 • 1年前Propellers
Propellers
ユーザ名非公開 · 100問 · 1年前Propellers
Propellers
100問 • 1年前Propellers (2)
Propellers (2)
ユーザ名非公開 · 16問 · 1年前Propellers (2)
Propellers (2)
16問 • 1年前Induction and engine airflow system
Induction and engine airflow system
ユーザ名非公開 · 42問 · 1年前Induction and engine airflow system
Induction and engine airflow system
42問 • 1年前Ignition starting system
Ignition starting system
ユーザ名非公開 · 100問 · 1年前Ignition starting system
Ignition starting system
100問 • 1年前Ignition starting system (2)
Ignition starting system (2)
ユーザ名非公開 · 29問 · 1年前Ignition starting system (2)
Ignition starting system (2)
29問 • 1年前Auxiliary power unit
Auxiliary power unit
ユーザ名非公開 · 10問 · 1年前Auxiliary power unit
Auxiliary power unit
10問 • 1年前Reciprocating engines
Reciprocating engines
ユーザ名非公開 · 100問 · 1年前Reciprocating engines
Reciprocating engines
100問 • 1年前Turbine engines (2)
Turbine engines (2)
ユーザ名非公開 · 20問 · 1年前Turbine engines (2)
Turbine engines (2)
20問 • 1年前Fuel metering systems
Fuel metering systems
ユーザ名非公開 · 98問 · 1年前Fuel metering systems
Fuel metering systems
98問 • 1年前Aircraft landing gear system
Aircraft landing gear system
ユーザ名非公開 · 79問 · 1年前Aircraft landing gear system
Aircraft landing gear system
79問 • 1年前Sheetmetal & Non sheetmetalic structure
Sheetmetal & Non sheetmetalic structure
ユーザ名非公開 · 100問 · 1年前Sheetmetal & Non sheetmetalic structure
Sheetmetal & Non sheetmetalic structure
100問 • 1年前Sheetmetal and non sheetmetalic structure
Sheetmetal and non sheetmetalic structure
ユーザ名非公開 · 30問 · 1年前Sheetmetal and non sheetmetalic structure
Sheetmetal and non sheetmetalic structure
30問 • 1年前Aircraft fuel system
Aircraft fuel system
ユーザ名非公開 · 100問 · 1年前Aircraft fuel system
Aircraft fuel system
100問 • 1年前問題一覧
1
3 and 5.
2
the same slot
3
should be performed parallel to the length of the blade using smooth contours to minimize stress points.
4
Direct the flow of gases to strike the turbine blades at the desired angle.
5
low-pressure rotor will increase in speed as the compressor load decreases in the lower density air.
6
Turbine, compressor, and combustion.
7
increase and the velocity to decrease.
8
number of compressor stages.
9
number of compressor stages.
10
compressor may be contaminated or damaged.
11
Split-spool, axial-flow.
12
The engine manufacturer.
13
1,2
14
creep
15
field cleaning.
16
increase the velocity of the gas flow.
17
A rise in the exhaust gas temperature.
18
Exhaust
19
erosion damage to the compressor and turbine sections.
20
Combustion section.
21
Rotor and stator.
22
impulse, reaction, and impulse-reaction.
23
vent some of the air overboard to prevent a compressor stall.
24
high peak efficiency.
25
The engine manufacturer.
26
Self-ionizing or shunted-gap type plug.
27
increases
28
a. a hot start is indicated if the exhaust gas temperature exceeds specified limits.
29
on a time or cycle basis.
30
Impeller and diffuser.
31
malfunctioning fuel nozzles.
32
Higher compression ratios can be obtained.
33
both No. 1 and No. 2 are true.
34
neither No. 1 nor No. 2 is true.
35
changing the velocity of the airflow.
36
1,2,5
37
increases
38
Across the leading or trailing edge at a right angle to the edge length.
39
pressure
40
A compressor with vanes on both sides of the impeller.
41
decreases
42
Starter, ignition, fuel.
43
Multiple-can, annular, and can-annular.
44
after the engine has reached self-accelerating speed.
45
Can
46
To straighten airflow to eliminate turbulence.
47
Pt7
48
prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path surfaces.
49
59°F
50
Labyrinth and/or carbon rubbing.
51
a faulty combustion chamber.
52
Turn off the fuel and continue engine rotation with the starter.
53
Engine main bearing distress.
54
convert velocity energy into pressure energy.
55
increase the velocity of the heated gases flowing past this point.
56
allow the turbine wheel to cool before the case contracts around it.
57
The turbine blades are shaped so that their ends form a band or shroud.
58
Variable guide vanes and/or compressor bleed valves.
59
seeks its own best operating speed.
60
In the entrance of the burner section.
61
reduce vibration.
62
1,4
63
Creep
64
Greater pressure ratio.
65
N(2) compressor.
66
stators
67
stator vanes.
68
29.92” Hg.
69
galling
70
Directs the air into the first stage rotor blades at the proper angle.
71
shrouded turbine rotor blades.
72
engine bleed air ducted through the critical areas.
73
Turbine blades.
74
a lean die-out.
75
Acceleration is produced when a force acts on a mass. The greater the mass, the greater the amount of force needed.
76
straighten the airflow and eliminate turbulence.
77
Number of stages in compressor.
78
straighten and collect the exhaust gases into a solid exhaust jet.
79
A reduced blade tip thickness.
80
1,4,5
81
Cracking
82
Impulse-reaction.
83
single entry and double entry.
84
Everybody persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force.
85
drives the compressor section.
86
low-pressure compressor.
87
pressure cycle.
88
The fuel is quickly cut off to the nozzles and the manifolds are drained preventing fuel boiling off as a result of residual engine heat.
89
fails to reach idle RPM.
90
the total pressure at station No. 7.
91
Over temperature condition.
92
Stator and rotor.
93
turbine inlet guide vanes.
94
Stress rupture.
95
decreases
96
To increase pressure and reduce velocity.
97
Turbine inlet temperature.
98
N(2) compressor.
99
Turbine inlet temperature.
100
neither No. 1 nor No. 2 is true.