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
61. Allowable damage on the first stage compressor blade is restricted to.
A. middle third of the blade to the outer edge.
B. outer third of the blade to the outer edge.
C. root end of the blade.
62. Tip speed of a centrifugal compressor can reach.
A. Mach 1.3.
B. Mach 1.0.
C. Mach 0.8.
63. What is the profile of a compressor blade?.
A. A cutout that reduces blade tip thickness.
B. The leading edge of the blade.
C. The curvature of the blade root.
64. The resultant velocity of air exiting an axial compressor stage depends upon.
A. aircraft forward speed.
B. compressor RPM.
C. Both of the above.
65. What is a compressor stage?.
A. One compressor rotor and one nozzle guide vane.
B. One rotor plus one stator.
C. One Nozzle Guide Vane and one rotor.
66. If the bypass ratio is 0.7:1, the 0.7 pounds of air is.
A. fed into H.P compressor compared to 1 pound fed around it.
B. fed around the engine to 1 pound fed into H.P. compressor.
C. bypassed for every 1 pound at the intake.
67. Advantage of an axial flow over a centrifugal flow gas turbine engine.
A. power required for starting is less.
B. low weight.
C. high peak efficiencies.
68. Compressor blades reduce in length.
A. from tip to root to maintain uniform velocity in compressor.
B. from L.P to H.P section to maintain uniform velocity in compressor.
C. from root to tip to maintain correct angle of attack.
69. Deposit build-up on compressor blades.
A. airflow is too fast for deposits to build up.
B. will not decrease efficiency but may cause corrosion.
C. can decrease compressor efficiency and cause corrosion.
70. The diffuser after the compressor, before the combustion chamber.
A. increases velocity, decreases pressure.
B. decreases velocity, pressure increases.
C. increases velocity, pressure remains constant.
ABOVE QUESTIONS WITH ANSWERS
61. Allowable damage on the first stage compressor blade is restricted to.
A. middle third of the blade to the outer edge.
B. outer third of the blade to the outer edge.
C. root end of the blade.
62. Tip speed of a centrifugal compressor can reach.
A. Mach 1.3.
B. Mach 1.0.
C. Mach 0.8.
63. What is the profile of a compressor blade?.
A. A cutout that reduces blade tip thickness.
B. The leading edge of the blade.
C. The curvature of the blade root.
64. The resultant velocity of air exiting an axial compressor stage depends upon.
A. aircraft forward speed.
B. compressor RPM.
C. Both of the above.
65. What is a compressor stage?.
A. One compressor rotor and one nozzle guide vane.
B. One rotor plus one stator.
C. One Nozzle Guide Vane and one rotor.
66. If the bypass ratio is 0.7:1, the 0.7 pounds of air is.
A. fed into H.P compressor compared to 1 pound fed around it.
B. fed around the engine to 1 pound fed into H.P. compressor.
C. bypassed for every 1 pound at the intake.
67. Advantage of an axial flow over a centrifugal flow gas turbine engine.
A. power required for starting is less.
B. low weight.
C. high peak efficiencies.
68. Compressor blades reduce in length.
A. from tip to root to maintain uniform velocity in compressor.
B. from L.P to H.P section to maintain uniform velocity in compressor.
C. from root to tip to maintain correct angle of attack.
69. Deposit build-up on compressor blades.
A. airflow is too fast for deposits to build up.
B. will not decrease efficiency but may cause corrosion.
C. can decrease compressor efficiency and cause corrosion.
70. The diffuser after the compressor, before the combustion chamber.
A. increases velocity, decreases pressure.
B. decreases velocity, pressure increases.
C. increases velocity, pressure remains constant.
ABOVE QUESTIONS WITH ANSWERS
61. Allowable damage on the first stage compressor blade is restricted to.
A. middle third of the blade to the outer edge.
B. outer third of the blade to the outer edge.
C. root end of the blade.
Ans : middle third of the blade to the outer edge.
Explanation: Jeppesen Gas Turbine Powerplants Page 5-20 refers.
62. Tip speed of a centrifugal compressor can reach.
A. Mach 1.3.
B. Mach 1.0.
C. Mach 0.8.
Ans : Mach 1.3.
Explanation: Jeppesen Aircraft Gas turbine Powerplant Page 3-11.
63. What is the profile of a compressor blade?.
A. A cutout that reduces blade tip thickness.
B. The leading edge of the blade.
C. The curvature of the blade root.
Ans : A cutout that reduces blade tip thickness.
Explanation: Jeppesen A&P Technician Propulsion Textbook 3-16.
64. The resultant velocity of air exiting an axial compressor stage depends upon.
A. aircraft forward speed.
B. compressor RPM.
C. Both of the above.
Ans : Both of the above.
Explanation: Jeppesen Aircraft Powerplant Page 3-23 Refers.
65. What is a compressor stage?.
A. One compressor rotor and one nozzle guide vane.
B. One rotor plus one stator.
C. One Nozzle Guide Vane and one rotor.
Ans : One rotor plus one stator.
Explanation: Rolls Royce The Jet Engine Page 25 refers.
66. If the bypass ratio is 0.7:1, the 0.7 pounds of air is.
A. fed into H.P compressor compared to 1 pound fed around it.
B. fed around the engine to 1 pound fed into H.P. compressor.
C. bypassed for every 1 pound at the intake.
Ans : fed around the engine to 1 pound fed into H.P. compressor.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 2-9 refers.
67. Advantage of an axial flow over a centrifugal flow gas turbine engine.
A. power required for starting is less.
B. low weight.
C. high peak efficiencies.
Ans : high peak efficiencies.
Explanation: Rolls Royce The Jet engine page 21 shows how higher compression ratios (axial flow compressors) give lower SFC. Which means higher efficiency.
68. Compressor blades reduce in length.
A. from tip to root to maintain uniform velocity in compressor.
B. from L.P to H.P section to maintain uniform velocity in compressor.
C. from root to tip to maintain correct angle of attack.
Ans : from L.P to H.P section to maintain uniform velocity in compressor.
Explanation: Rolls Royce The Jet Engine Page 22 refers.
69. Deposit build-up on compressor blades.
A. airflow is too fast for deposits to build up.
B. will not decrease efficiency but may cause corrosion.
C. can decrease compressor efficiency and cause corrosion.
Ans : can decrease compressor efficiency and cause corrosion.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant page 5-4 refers.
70. The diffuser after the compressor, before the combustion chamber.
A. increases velocity, decreases pressure.
B. decreases velocity, pressure increases.
C. increases velocity, pressure remains constant.
Ans : decreases velocity, pressure increases.
Explanation: Assuming this refers to a centrifugal compressor see figure 3-6 Rolls Royce The Jet Engine.
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