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1
You would expect to find the highest gas velocity in a turbojet engine
at the end of the exhaust nozzle
2
The purpose of a diffuser in a gas turbine engine is to
raise pressure and lower velocity
3
The correct statement regarding the aviation of MSL full throttle thrust of a jet engine is
thrust decreases as air temperature increases
4
You would expect to find the highest gas pressure in a turbojet engine
in the diffuser
5
You would expect to find the highest gas temperature in a turbojet engine
in the combustion chamber
6
The ‘Engine Core’ of a turbofan engine refers to
the compressor, combustion chambers, turbines and exhaust
7
The maximum thrust output of a turbojet engine will increase with
a decrease in ambient air temperature
8
The effect an increase in altitude alone will have on the Low Pressure compressor of a gas turbine engine if constant thrust is maintained is
rpm will increase
9
A pure turbojet engine in comparison to a turbofan engine has
no bypass air
10
Subsonic gas flow decreases in velocity and increases in pressure when flowing through
a divergent duct
11
Ram effect
raises the thrust output of a jet engine as aircraft speed increases
12
In passing through the turbine section of a pure turbojet engine
gas pressure reduces, velocity increases and temperature decreases
13
'Tertiary creep' in a turbine blade of a gas turbine engine means
blade creep to the point where it would be detrimental to continue to run the engine
14
Gas turbine engine compressor stall may be caused by
an unstable airflow through the compressor
15
The maximum gas pressure in a gas turbine is obtained
at the compressor exit
16
For a given RPM, thrust output from a gas turbine engine will be greatest
at MSL (Mean Sea Level) under ISA conditions
17
If compressor blade stall occurs in a gas turbine engine
the smooth flow of air over the blading breaks away and causes an interruption of airflow through the engine.
18
The purpose of variable inlet guide vanes in a gas turbine engine is to
prevent compressor blade stall during operation off design rpm
19
Turbojet aircraft range increases as altitude increases toward the optimum Flight Level becuase at high altitude
the engine can operate at design RPM to maintain an efficient wing angle of attack.
20
The use of bleed air from a gas turbine engine compressor for anti-icing equipment will result in
An increase in the gas temperature, reduced thrust and an increase in SFC
21
Maximum gas pressure in a gas turbine engine is found
between the final compressor stage and the inlet to the combustion chamber
22
The main reason for a limit on the maximum gas temperature in a gas turbine engine is
to prevent overheating of the turbine
23
Burning fuel in the combustion chambers of a gas turbine engine is necessary to
increase the volume and velocity of the gases
24
On leaving the compressor in a gas turbine engine, the air passes through
divergent ducts which lower the velocity and raise the pressure of the air
25
When an aircraft is parked overnight, to reduce fuel tank condensation you would
keep the tanks as full as possible.
26
In a free turbine turboprop engine, the propeller is driven by
only the rear Low Pressure Turbine(s)
27
The action which should be taken if a gas turbine compressor begins to stall during engine acceleration on start-up is
shut off the fuel supply and maintain starter motor rotation.
28
The term SFC (Specific Fuel Consumption) means
units of fuel used per unit of thrust per hour
29
Some turbojet engine turbine blades shrouded at the tips to
prevent gas leaking past blade tips, increase rigidity and reduce vibration
30
The fuel flow in a jet engine is increased. Thrust increases because exhaust gas
velocity increases
31
The times the surge bleed valve is open and closed during normal gas turbine engine operation are
open from idling to nearly design RPM, then closed up to max RPM
32
The propulsive efficiency of a turboprop decreases with an increase in a speed because
of compressibility effects on the blades
33
The gas turbine (Bryaton) cycle is called an open or continuous cycle because
all events are occurring at the same time.
34
A modest increase in speed in a slow flying jet aircraft leads to a small initial decrease in maximum thrust available because
the difference between exhaust and intake velocities is reduced
35
Pressure through the combustion chambers in a gas turbine engine
is constant or falls slightly
36
To prevent melting of the turbine wheels, the hot gases from the combustion chamber in a gas turbine engine are cooled by
Air
37
Engine Pressure Ratio (EPR) is the ratio of
Engine compressor inlet pressure to jet pipe pressure
38
When climbing in a jet engined aircraft, the engine parameter which would stay constant if the thrust lever setting remained unchanged is
RPM
39
Thrust is produced in a jet engine by
The force required to accelerate a mass of air trhough the engine.
40
Fuel boost pumps in a jet aircraft fuel system are usually located in
the fuel tanks