MODULE 15 CHAPTER 2 QUIZ 5

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

41. As the air is passed through the turbine, due to the convergent shape formed between adjacent blades.

A. pressure decreases, velocity increases, temperature increases.

B. pressure increases, velocity increases, temperature constant.

C. pressure decreases, velocity increases, temperature decreases.

42. The hottest component in a gas turbine engine is.

A. the nozzle guide vanes.

B. the turbines.

C. the combustion chamber.

43. The basic equation for thrust is.

A. thrust = force * acceleration.

B. thrust = mass * velocity.

C. thrust = mass * acceleration.

44. To maintain the selected RPM of a gas turbine at altitude.

A. the pilot will have to throttle back.

B. more fuel will automatically be added.

C. the fuel will automatically be reduced as the aircraft climbs.

45. The term Pb means.

A. burner pressure measured at the diffuser case.

B. burner pressure measured at the NGV.

C. burner pressure measured at the combustion chamber.

46. Which of the following is not an engine rating?.

A. Maximum Continuous.

B. Idle.

C. Maximum Take Off.

47. At higher then standard day ambient temperatures, compressor speed will be.

A. lower than standard day speed.

B. no different.

C. higher than standard day speed.

48. Ram Recovery is a measure of.

A. intake efficiency.

B. net thrust.

C. forward air speed.

49. most likely parameter limiting the height at which a jet engine powered aircraft can operate would be insufficient.

A. lift to support the aircraft weight.

B. mass airflow to maintain 15:1 air/fuel ratio.

C. oxygen to support combustion.

50. With increasing ram effect.

A. turbine temperatures decreases.

B. propulsive efficiency decreases.

C. propulsive efficiency increases.

ABOVE QUESTIONS WITH ANSWERS 

41. As the air is passed through the turbine, due to the convergent shape formed between adjacent blades.

A. pressure decreases, velocity increases, temperature increases.

B. pressure increases, velocity increases, temperature constant.

C. pressure decreases, velocity increases, temperature decreases.

Ans : pressure decreases, velocity increases, temperature decreases.

Explanation: Rolls Royce The Jet Engine Fig 2-5-1 refers.

42. The hottest component in a gas turbine engine is.

A. the nozzle guide vanes.

B. the turbines.

C. the combustion chamber.

Ans : the combustion chamber.

Explanation: Combustors have to withstand flame temperatures of 2000 degrees C.

43. The basic equation for thrust is.

A. thrust = force * acceleration.

B. thrust = mass * velocity.

C. thrust = mass * acceleration.

Ans : thrust = mass * acceleration.

Explanation: Newtons second Law.

44. To maintain the selected RPM of a gas turbine at altitude.

A. the pilot will have to throttle back.

B. more fuel will automatically be added.

C. the fuel will automatically be reduced as the aircraft climbs.

Ans : the fuel will automatically be reduced as the aircraft climbs.

Explanation: In a hydro mechanical engine the P1 capsule will sense increasing altitude and trim off the fuel.

45. The term Pb means.

A. burner pressure measured at the diffuser case.

B. burner pressure measured at the NGV.

C. burner pressure measured at the combustion chamber.

Ans : burner pressure measured at the combustion chamber.

Explanation: Burner pressure is the static pressure in the combustor can, used in some systems to regulate fuel flow.

46. Which of the following is not an engine rating?.

A. Maximum Continuous.

B. Idle.

C. Maximum Take Off.

Ans : Idle.

Explanation: NIL.

47. At higher then standard day ambient temperatures, compressor speed will be.

A. lower than standard day speed.

B. no different.

C. higher than standard day speed.

Ans : higher than standard day speed.

Explanation: The air is thinner at higher temperatures, therefore the compressor has less load to work against and goes faster. RR Jet Engine Fig 2-18 refers. Note that due to the max allowable EGT the engine will reach a limiting 'corner-point thrust' and fuel will be trimmed off to prevent any over boost or over temperature

48. Ram Recovery is a measure of.

A. intake efficiency.

B. net thrust.

C. forward air speed.

Ans : intake efficiency.

Explanation: Ram Recovery is the ability of an intake to convert kinetic energy into useful pressure energy.

49. most likely parameter limiting the height at which a jet engine powered aircraft can operate would be insufficient.

A. lift to support the aircraft weight.

B. mass airflow to maintain 15:1 air/fuel ratio.

C. oxygen to support combustion.

Ans : oxygen to support combustion.

Explanation: The engine will flame out with insufficient oxygen.

50. With increasing ram effect.

A. turbine temperatures decreases.

B. propulsive efficiency decreases.

C. propulsive efficiency increases.

Ans : propulsive efficiency increases.

Explanation: Increasing Ram Effect increases the overall system pressure ratio, hence increasing propulsive efficiency.