15/1to6
問題一覧
1
to calculate the amount of thrust produced by the engine
2
increasing air mass flown to engine or gases acceleration through the engine
3
Compressor (increase air pressure) and Combustor (increase gases acceleration
4
net thrust
5
= SHP + Jet Thrust Addition of SHP to jet thrust. 1hp=745.7
6
is the ability of engine to drive the aircraft in flight
7
thrust produced per pound of fuel consumed
8
increase
9
At higher engine speeds
10
decrease
11
affect the inlet air density.
12
due to drag decrease
13
which negatively effect engine thrust and vice versa
14
greater mass flow and greater thrust
15
as constant-pressure cycle
16
reduce from front to rear
17
virtually constant.
18
a non-air breathing engine means it does not use atmospheric air to support combustion
19
it has additional spring loaded valves in the air intake
20
turbojet and a turboprop, literally handles a hot air mass and a cold air mass
21
Governor
22
to the propeller by accelerating large mass of air at a low rate of acceleration
23
HP compressor only
24
Free turbine¬
25
Free turbine
26
indicates that bypass flow is five times the hot stream
27
bypass air
28
engine core air
29
at compressor outlet
30
deliver a smooth and uniform stream of air to the compressor inlet
31
divergent duct (front to rear) and best suited for subsonic aircrafts
32
96-99%
33
fixed duct design convergent then divergent duct. Used to slow down air flow speed to subsonic before compressor
34
throat area decreased
35
used to prevent ice formation of engine intake
36
bled hot air from the compressor
37
(10°+ C) with visible moisture.
38
operated part continuous & part intermittent
39
to minimal loss of engine power or thrust
40
to reverse flow turboprop engines
41
difficulty in designing.
42
is a raw of rotor and a raw of stator
43
increase pressure and control the direction of airflow.
44
increase air velocity
45
axial velocity
46
Compressor pressure ratio
47
that control the pressure ratio is number of stages in the compressor
48
at compressor outlet
49
is lowest stagger angle at the root
50
limited by blade tip speed
51
multiply inlet pressure with compression ratio
52
small gas turbine engines with reverse flow combustion
53
it is based on cruise speed and altitude (air density)
54
flexibility of operation and greater resistance to surge
55
lower RPM than high pressure compressor
56
less efficient
57
avoid surge.
58
keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage
59
to support fan blade and prevent aerodynamic instability
60
Simple ,Low weight & cost and High pressure rise per stage
61
Large frontal area and limited number of stages.
62
used to decrease the velocity of the air.
63
combustion chamber.
64
exhaust smoke and carbon particles formed inside combustion chamber.
65
a transpiration cooling
66
to protect combustion chamber from melting.
67
(45:1 – 130:1)
68
turbo-prop and turbo-shaft engines.
69
two cans by igniter plugs then moved through interconnector tubes to the remaining cans
70
snout shape.
71
A tubo-annular.
72
smaller and lighter
73
too much fuel for the primary air in the combustion chamber
74
the primary dilution zone is 15:1
75
is correct mixture ratio and air velocity must be slow enough
76
has a set of flame tubes with common outer casing and
77
disadvantages Removal difficult and time consuming
78
advantages; Better thermal load distribution for the turbine
79
air flow vortex and help air fuel mixing
80
smooth burning coupled with ability to remain alight over a large range of air fuel ratio and air mass flow
81
into mechanical energy to drive compressor
82
Nickel alloy.
83
(Starter blades)
84
(all modern jet engines).
85
fir tree root with locking plate
86
base of the root.
87
allows slight movement
88
a convergent duct in order to increase velocity.
89
this method is known as Convection cooling
90
To ensure equal work done all over the blade length (root to tip)
91
direct gases in proper angle to first stage turbine nozzle
92
Cooling by ceramic coating and bleed air.
93
thermal stress and high centrifugal force .
94
single structure blades
95
reduce tip losses and improve efficiency in the cruise
96
to reduce vibration and improve air flow.
97
rotational speed increases
98
film cooling .
99
tip losses
100
allows very high airflow which is needed to create the high thrust of modern engines
15/1/2
15/1/2
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Guevara Official · 13問 · 1年前3.18
3.18
13問 • 1年前問題一覧
1
to calculate the amount of thrust produced by the engine
2
increasing air mass flown to engine or gases acceleration through the engine
3
Compressor (increase air pressure) and Combustor (increase gases acceleration
4
net thrust
5
= SHP + Jet Thrust Addition of SHP to jet thrust. 1hp=745.7
6
is the ability of engine to drive the aircraft in flight
7
thrust produced per pound of fuel consumed
8
increase
9
At higher engine speeds
10
decrease
11
affect the inlet air density.
12
due to drag decrease
13
which negatively effect engine thrust and vice versa
14
greater mass flow and greater thrust
15
as constant-pressure cycle
16
reduce from front to rear
17
virtually constant.
18
a non-air breathing engine means it does not use atmospheric air to support combustion
19
it has additional spring loaded valves in the air intake
20
turbojet and a turboprop, literally handles a hot air mass and a cold air mass
21
Governor
22
to the propeller by accelerating large mass of air at a low rate of acceleration
23
HP compressor only
24
Free turbine¬
25
Free turbine
26
indicates that bypass flow is five times the hot stream
27
bypass air
28
engine core air
29
at compressor outlet
30
deliver a smooth and uniform stream of air to the compressor inlet
31
divergent duct (front to rear) and best suited for subsonic aircrafts
32
96-99%
33
fixed duct design convergent then divergent duct. Used to slow down air flow speed to subsonic before compressor
34
throat area decreased
35
used to prevent ice formation of engine intake
36
bled hot air from the compressor
37
(10°+ C) with visible moisture.
38
operated part continuous & part intermittent
39
to minimal loss of engine power or thrust
40
to reverse flow turboprop engines
41
difficulty in designing.
42
is a raw of rotor and a raw of stator
43
increase pressure and control the direction of airflow.
44
increase air velocity
45
axial velocity
46
Compressor pressure ratio
47
that control the pressure ratio is number of stages in the compressor
48
at compressor outlet
49
is lowest stagger angle at the root
50
limited by blade tip speed
51
multiply inlet pressure with compression ratio
52
small gas turbine engines with reverse flow combustion
53
it is based on cruise speed and altitude (air density)
54
flexibility of operation and greater resistance to surge
55
lower RPM than high pressure compressor
56
less efficient
57
avoid surge.
58
keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage
59
to support fan blade and prevent aerodynamic instability
60
Simple ,Low weight & cost and High pressure rise per stage
61
Large frontal area and limited number of stages.
62
used to decrease the velocity of the air.
63
combustion chamber.
64
exhaust smoke and carbon particles formed inside combustion chamber.
65
a transpiration cooling
66
to protect combustion chamber from melting.
67
(45:1 – 130:1)
68
turbo-prop and turbo-shaft engines.
69
two cans by igniter plugs then moved through interconnector tubes to the remaining cans
70
snout shape.
71
A tubo-annular.
72
smaller and lighter
73
too much fuel for the primary air in the combustion chamber
74
the primary dilution zone is 15:1
75
is correct mixture ratio and air velocity must be slow enough
76
has a set of flame tubes with common outer casing and
77
disadvantages Removal difficult and time consuming
78
advantages; Better thermal load distribution for the turbine
79
air flow vortex and help air fuel mixing
80
smooth burning coupled with ability to remain alight over a large range of air fuel ratio and air mass flow
81
into mechanical energy to drive compressor
82
Nickel alloy.
83
(Starter blades)
84
(all modern jet engines).
85
fir tree root with locking plate
86
base of the root.
87
allows slight movement
88
a convergent duct in order to increase velocity.
89
this method is known as Convection cooling
90
To ensure equal work done all over the blade length (root to tip)
91
direct gases in proper angle to first stage turbine nozzle
92
Cooling by ceramic coating and bleed air.
93
thermal stress and high centrifugal force .
94
single structure blades
95
reduce tip losses and improve efficiency in the cruise
96
to reduce vibration and improve air flow.
97
rotational speed increases
98
film cooling .
99
tip losses
100
allows very high airflow which is needed to create the high thrust of modern engines