NOTE
TO CHECK YOUR PREPARATION ,PLZ WRITE DOWN YOUR SELECTED OPTIONS (A,B,C) ON ROUGH PAGE AND AT THE END OF QUIZ , VERIFY YOUR SELECTED OPTIONS WITH THE CORRECT OPTIONS GIVEN BELOW
11. The fan speed of a twin spool axial compressor engine is the same as the.
A. low pressure compressor.
B. forward turbine wheel.
C. high pressure compressor.
12. Bleed valves are normally spring loaded to the.
A. closed position.
B. open position.
C. mid-position.
13. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?.
A. To increase air swirling motion into the combustion chambers.
B. To direct the flow of gases into the combustion chambers.
C. To straighten airflow to eliminate turbulence.
14. In a turbine engine with a dual spool compressor, the low speed compressor.
A. always turns at the same speed as the high speed compressor.
B. seeks its own best operating speed.
C. is connected directly to the high speed compressor.
15. What units in a gas turbine engine aid in guiding the airflow during low thrust engine operations?.
A. Stator vanes.
B. Bleed air valves.
C. Inlet guide vanes.
16. What is one purpose of the stator blades in the compressor section?.
A. Increase the velocity of the airflow.
B. Stabilize the pressure of the airflow.
C. Control the direction of the airflow.
17. Compressor stall is caused by.
A. a low angle of attack airflow through the first stages of compression.
B. rapid engine deceleration.
C. a high angle of attack airflow through the first stages of compression.
18. What is used to aid in stabilization of compressor airflow?.
A. Variable guide vanes and/or compressor bleed valves.
B. Pressurization and dump valves.
C. Stator vanes and rotor vanes.
19. What is the primary factor which controls the pressure ratio of an axial flow compressor?.
A. Compressor inlet temperature.
B. Compressor inlet pressure.
C. Number of stages in compressor.
20. The non-rotating axial-flow compressor airfoils in an aircraft gas turbine are known as.
A. stator vanes.
B. bleed vanes.
C. pressurization vanes.
ABOVE QUESTIONS WITH ANSWERS
11. The fan speed of a twin spool axial compressor engine is the same as the.
A. low pressure compressor.
B. forward turbine wheel.
C. high pressure compressor.
Ans : low pressure compressor.
Explanation: Jeppesen A&P Powerplant Textbook 3-18.
12. Bleed valves are normally spring loaded to the.
A. closed position.
B. open position.
C. mid-position.
Ans : open position.
Explanation: Rolls Royce The Jet Engine Page 31 refers.
13. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?.
A. To increase air swirling motion into the combustion chambers.
B. To direct the flow of gases into the combustion chambers.
C. To straighten airflow to eliminate turbulence.
Ans : To straighten airflow to eliminate turbulence.
Explanation: Jeppesen A&P Powerplant Textbook 3-17.
14. In a turbine engine with a dual spool compressor, the low speed compressor.
A. always turns at the same speed as the high speed compressor.
B. seeks its own best operating speed.
C. is connected directly to the high speed compressor.
Ans : seeks its own best operating speed.
Explanation: NIL.
15. What units in a gas turbine engine aid in guiding the airflow during low thrust engine operations?.
A. Stator vanes.
B. Bleed air valves.
C. Inlet guide vanes.
Ans : Inlet guide vanes.
Explanation: NIL.
16. What is one purpose of the stator blades in the compressor section?.
A. Increase the velocity of the airflow.
B. Stabilize the pressure of the airflow.
C. Control the direction of the airflow.
Ans : Control the direction of the airflow.
Explanation: Jeppesen A&P Powerplant Textbook 3-17.
17. Compressor stall is caused by.
A. a low angle of attack airflow through the first stages of compression.
B. rapid engine deceleration.
C. a high angle of attack airflow through the first stages of compression.
Ans : a high angle of attack airflow through the first stages of compression.
Explanation: NIL.
18. What is used to aid in stabilization of compressor airflow?.
A. Variable guide vanes and/or compressor bleed valves.
B. Pressurization and dump valves.
C. Stator vanes and rotor vanes.
Ans : Variable guide vanes and/or compressor bleed valves.
Explanation: NIL.
19. What is the primary factor which controls the pressure ratio of an axial flow compressor?.
A. Compressor inlet temperature.
B. Compressor inlet pressure.
C. Number of stages in compressor.
Ans : Number of stages in compressor.
Explanation: NIL.
20. The non-rotating axial-flow compressor airfoils in an aircraft gas turbine are known as.
A. stator vanes.
B. bleed vanes.
C. pressurization vanes.
Ans : stator vanes.
11. The fan speed of a twin spool axial compressor engine is the same as the.
A. low pressure compressor.
B. forward turbine wheel.
C. high pressure compressor.
12. Bleed valves are normally spring loaded to the.
A. closed position.
B. open position.
C. mid-position.
13. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?.
A. To increase air swirling motion into the combustion chambers.
B. To direct the flow of gases into the combustion chambers.
C. To straighten airflow to eliminate turbulence.
14. In a turbine engine with a dual spool compressor, the low speed compressor.
A. always turns at the same speed as the high speed compressor.
B. seeks its own best operating speed.
C. is connected directly to the high speed compressor.
15. What units in a gas turbine engine aid in guiding the airflow during low thrust engine operations?.
A. Stator vanes.
B. Bleed air valves.
C. Inlet guide vanes.
16. What is one purpose of the stator blades in the compressor section?.
A. Increase the velocity of the airflow.
B. Stabilize the pressure of the airflow.
C. Control the direction of the airflow.
17. Compressor stall is caused by.
A. a low angle of attack airflow through the first stages of compression.
B. rapid engine deceleration.
C. a high angle of attack airflow through the first stages of compression.
18. What is used to aid in stabilization of compressor airflow?.
A. Variable guide vanes and/or compressor bleed valves.
B. Pressurization and dump valves.
C. Stator vanes and rotor vanes.
19. What is the primary factor which controls the pressure ratio of an axial flow compressor?.
A. Compressor inlet temperature.
B. Compressor inlet pressure.
C. Number of stages in compressor.
20. The non-rotating axial-flow compressor airfoils in an aircraft gas turbine are known as.
A. stator vanes.
B. bleed vanes.
C. pressurization vanes.
ABOVE QUESTIONS WITH ANSWERS
11. The fan speed of a twin spool axial compressor engine is the same as the.
A. low pressure compressor.
B. forward turbine wheel.
C. high pressure compressor.
Ans : low pressure compressor.
Explanation: Jeppesen A&P Powerplant Textbook 3-18.
12. Bleed valves are normally spring loaded to the.
A. closed position.
B. open position.
C. mid-position.
Ans : open position.
Explanation: Rolls Royce The Jet Engine Page 31 refers.
13. What is the function of the stator vane assembly at the discharge end of a typical axial flow compressor?.
A. To increase air swirling motion into the combustion chambers.
B. To direct the flow of gases into the combustion chambers.
C. To straighten airflow to eliminate turbulence.
Ans : To straighten airflow to eliminate turbulence.
Explanation: Jeppesen A&P Powerplant Textbook 3-17.
14. In a turbine engine with a dual spool compressor, the low speed compressor.
A. always turns at the same speed as the high speed compressor.
B. seeks its own best operating speed.
C. is connected directly to the high speed compressor.
Ans : seeks its own best operating speed.
Explanation: NIL.
15. What units in a gas turbine engine aid in guiding the airflow during low thrust engine operations?.
A. Stator vanes.
B. Bleed air valves.
C. Inlet guide vanes.
Ans : Inlet guide vanes.
Explanation: NIL.
16. What is one purpose of the stator blades in the compressor section?.
A. Increase the velocity of the airflow.
B. Stabilize the pressure of the airflow.
C. Control the direction of the airflow.
Ans : Control the direction of the airflow.
Explanation: Jeppesen A&P Powerplant Textbook 3-17.
17. Compressor stall is caused by.
A. a low angle of attack airflow through the first stages of compression.
B. rapid engine deceleration.
C. a high angle of attack airflow through the first stages of compression.
Ans : a high angle of attack airflow through the first stages of compression.
Explanation: NIL.
18. What is used to aid in stabilization of compressor airflow?.
A. Variable guide vanes and/or compressor bleed valves.
B. Pressurization and dump valves.
C. Stator vanes and rotor vanes.
Ans : Variable guide vanes and/or compressor bleed valves.
Explanation: NIL.
19. What is the primary factor which controls the pressure ratio of an axial flow compressor?.
A. Compressor inlet temperature.
B. Compressor inlet pressure.
C. Number of stages in compressor.
Ans : Number of stages in compressor.
Explanation: NIL.
20. The non-rotating axial-flow compressor airfoils in an aircraft gas turbine are known as.
A. stator vanes.
B. bleed vanes.
C. pressurization vanes.
Ans : stator vanes.
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