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NOTE
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51. The compression ratio of a jet engine is.
A. the compressor outlet pressure divided by the number of compressor stages.
B. the ratio between turbine pressure and compressor outlet pressure.
C. the ratio between compressor outlet pressure and compressor inlet pressure.
52. Variable inlet guide vanes help to prevent.
A. compressor runaway.
B. ice build up on compressor blades.
C. compressor stalling.
53. Air through the compressor, before entering the combustion chamber, passes.
A. through divergent passage to increase the pressure.
B. through nozzles to increase the velocity.
C. through divergent passage to decrease the pressure.
54. Low mass airflow through a compressor will produce.
A. stalling of rear stages.
B. stalling of early stages.
C. no effect.
55. A bleed valve.
A. relieves compressor choking at low RPM.
B. controls air intake pressure.
C. bleeds air from compressor for intake deicing.
56. If a compressor has a compression ratio of 9:1 and an intake compression of 2:1, what is the overall compression ratio?.
A. 9:1 intake compression does not add to the overall compression ratio of the system.
B. 18:1.
C. 11:1.
57. A compressor stage stalls when.
A. adiabatic temperature rise is too high.
B. compression ratio is too high.
C. smooth airflow is disrupted.
58. Inlet guide vanes are fitted to.
A. control the quantity of air entering the intake.
B. guide the airflow onto the turbine rotor first stage.
C. control the angle of airflow into the compressor.
59. Why, in an axial flow compressor is the cross sectional area of the compressor air duct reduced at each stage?.
A. To decrease the velocity of the air rising under pressure.
B. To maintain the velocity of the air under rising pressure.
C. To permit stronger, shorter blades to be used in the later stages.
60. An abradable lining around the fan is to.
A. provide less leakage for anti-icing.
B. prevent fan blade tip rub.
C. strengthen the EPR value.
ABOVE QUESTIONS WITH ANSWERS
51. The compression ratio of a jet engine is.
A. the compressor outlet pressure divided by the number of compressor stages.
B. the ratio between turbine pressure and compressor outlet pressure.
C. the ratio between compressor outlet pressure and compressor inlet pressure.
Ans : the ratio between compressor outlet pressure and compressor inlet pressure.
Explanation: The higher the ratio the more efficient the engine.
52. Variable inlet guide vanes help to prevent.
A. compressor runaway.
B. ice build up on compressor blades.
C. compressor stalling.
Ans : compressor stalling.
Explanation: Rolls Royce The Jet Engine page 28 refers.
53. Air through the compressor, before entering the combustion chamber, passes.
A. through divergent passage to increase the pressure.
B. through nozzles to increase the velocity.
C. through divergent passage to decrease the pressure.
Ans : through divergent passage to increase the pressure.
Explanation: All compressor blades and stators are divergent, and all increase pressure.
54. Low mass airflow through a compressor will produce.
A. stalling of rear stages.
B. stalling of early stages.
C. no effect.
Ans : stalling of early stages.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 3-25 refers.
55. A bleed valve.
A. relieves compressor choking at low RPM.
B. controls air intake pressure.
C. bleeds air from compressor for intake deicing.
Ans : relieves compressor choking at low RPM.
Explanation: Rolls Royce The Jet Engine Page 29 refers.
56. If a compressor has a compression ratio of 9:1 and an intake compression of 2:1, what is the overall compression ratio?.
A. 9:1 intake compression does not add to the overall compression ratio of the system.
B. 18:1.
C. 11:1.
Ans : 18:1.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 3-20 refers.
57. A compressor stage stalls when.
A. adiabatic temperature rise is too high.
B. compression ratio is too high.
C. smooth airflow is disrupted.
Ans : smooth airflow is disrupted.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 3-25 refers.
58. Inlet guide vanes are fitted to.
A. control the quantity of air entering the intake.
B. guide the airflow onto the turbine rotor first stage.
C. control the angle of airflow into the compressor.
Ans : control the angle of airflow into the compressor.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 3-24 refers.
59. Why, in an axial flow compressor is the cross sectional area of the compressor air duct reduced at each stage?.
A. To decrease the velocity of the air rising under pressure.
B. To maintain the velocity of the air under rising pressure.
C. To permit stronger, shorter blades to be used in the later stages.
Ans : To maintain the velocity of the air under rising pressure.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 3-24 refers.
60. An abradable lining around the fan is to.
A. provide less leakage for anti-icing.
B. prevent fan blade tip rub.
C. strengthen the EPR value.
Ans : strengthen the EPR value.
Explanation: Prevents fan blade tip losses.
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