The pressure ratio of a gas turbine compressor is:
equal to the number of compression stages.
the ratio between compressor outlet and compressor inlet pressure.
the ratio between exhaust inlet and exhaust outlet pressure.
One stage of an axial flow compressor consists of:
one rotor assembly and one row of stator vanes.
one stator assembly and one row of guide vanes.
one rotor and one diffuser assembly.
As air passes through an axial flow compressor, a pressure rise takes place in:
both the rotor blades and the stator vanes.
the rotor blades only.
the stator vanes only.
The bypass ratio of an engine is the ratio of:
exhaust gas pressure to air intake pressure.
cold stream air to that flowing through the hot core of the engine.
Primary air to secondary air.
In the event of a surge occuring the correct action to be taken is:
to close the throttle quickly.
To close the throttle slowly.
to open the throttle fully.
The low pressure compressor of a high ratio bypass engine:
is driven by the rearmost turbine.
is driven by the high pressure turbine.
is always a centrifugal compressor.
Referring to the diagram, items A, B, C and D represents:
low pressure compressor, high pressure compressor, combustion section, low pressure turbine.
low pressure compressor, high pressure compressor, combustion section, high pressure turbine.
Intermediate pressure compressor, high pressure compressor, combustion section, low pressure turbine.
In a triple spool gas turbine engine, N1 refers to the % RPM of the:
low pressure compressor
high pressure turbine
high pressure compressor
An intermittent “bang” as backfires and flow reversals occur is an indication of:
Thrust reverser malfunction.
A transient compressor stall.
A steady, developed compressor stall.
Strong vibrations and a loud roar is an indication of:
Thrust reverser malfunction.
A transient compressor stall.
A steady, developed compressor stall.
Fill in the following blanks according to the picture below.
填空1 ____________
填空2 ____________
填空3 ____________
填空4 ____________
填空5 ____________
Which of the following has the greatest potential for severe engine damage?
Thrust reverser malfunction.
A transient compressor stall.
A steady, developed compressor stall.
Recovery from a developed compressor stall requires:
A reduction in fuel flow and angle of attack.
An increase in airspeed.
Both are correct.
If the flow through a compressor is said to be radial then the type would be:
centrifugal
axial
tangential
The pressure rise across each stage of an axial flow compressor is:
between 1.1 and 1.2 to one.
twice the inlet pressure.
greater than that of a centrifugal compressor.
