DGCA & EASA Module 15 : Part-12 Engine Air Systems Question

DGCA & EASA Module 15 : Part-12 Engine Air Systems Question-Answer


1. Engine anti-ice is taken from the.
A. turbine.
B. H.P compressor.
C. LP compressor.
Ans : H.P compressor.
Explanation: Jepperson Gas Turbine Powerplants Page 9-2 refers.



2. In an axial flow turbine engine, compressor bleed air is sometimes used to aid in cooling the.
A. inlet guide vanes.
B. turbine, vanes, blades, and bearings.
C. fuel.
Ans : turbine, vanes, blades, and bearings.
Explanation: NIL.

3. If air is taken from the compressor for air conditioning or anti-icing.
A. thrust will increase EGT will increase.
B. thrust will decrease EGT will increase.
C. thrust will decrease EGT will decrease.
Ans : thrust will decrease EGT will increase.
Explanation: Air is taken from the H.P compressor hence there is less mass flow.

4. Turbine case cooling utilizes.
A. LP compressor air.
B. fan air.
C. H.P compressor air.
Ans : fan air.
Explanation: Fan air is the coldest in the engine.

5. Air for anti-icing is taken from the.
A. accessory Gearbox.
B. LP compressor.
C. H.P compressor.
Ans : H.P compressor.
Explanation: LP air would not be hot enough.

6. As air is bled off the engine, EGT will.
A. remain constant.
B. decrease.
C. increase.
Ans : increase.
Explanation: Less air, but same fuel equals higher EGT.

7. The heat absorbed by internal components can be detrimental to thrust and is prevented by.
A. reducing fuel flow to reduce internal temperature.
B. bleeding air off the compressor to heat the components.
C. bleeding air off the compressor to cool the components.
Ans : bleeding air off the compressor to cool the components.
Explanation: Jeppesen Aircraft Gas Turbine Powerplant Page 4-53 refers.

8. On a gas turbine engine, thermal wing de-icing system derives air.
A. via air from the H.P turbine.
B. through a pressure regulating shut-off valve (P.R.S.O.V).
C. through a pressure relief system.
Ans : through a pressure regulating shut-off valve (P.R.S.O.V).
Explanation: Rolls Royce The Jet Engine Page 150 Refers.

9. Inlet for cooling air for the first stage turbine blades is fed via the.
A. blade root.
B. grill holes.
C. leading edge of the blade.
Ans : blade root.
Explanation: The cooling air is ducted through the turbine disc to the blade root then out into the airstream through holes in the leading and trailing edges.

10. Air bleed for an anti-ice system is.
A. tapped directly off the compressor.
B. sent through a pressure regulator.
C. sent through the air conditioning.
Ans : tapped directly off the compressor.
Explanation: With this method if the engine is running then anti-ice air is always available.

11. With bleed valves open for anti-ice.
A. thrust is unaffected.
B. thrust decreases, fuel consumption decreases.
C. thrust decreases, fuel consumption increases.
Ans : thrust decreases, fuel consumption decreases.

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