1) The efficiency of a gas turbine engine at high altitudes Report

Decreases

Increases

Remains constant

2) Which statement is true regarding jet engines? Report

At the higher engine speeds, thrust increases rapidly with small increases in RPM

At the lower engine speeds, thrust increases rapidly with small increases in RPM

The thrust delivered per pound of air consumed is less at high altitude

3) Some turboprop and turbojet engines are equipped with two spool or split compressors. When these engines are operated at high altitudes, the Report

low pressure rotor will increase in speed as the compressor load decreases in the lower density air

low pressure rotor will decrease in speed as the compressor load decreases in the lower density air

throttle must be retarded to prevent overspeeding of the high pressure rotor due to the lower density air

4) Ram effect' due to aircraft forward speed will cause the thrust of the engine to Report

decrease

increase

remain constant

5) With a fixed throttle, and with increased massairflow, what happens to EPR? Report

EPR goes up

EPR goes down

EPR remains constant

6) At what stage in a gas turbine engine are gas pressures the greatest? Report

Turbine outlet

Compressor outlet

Compressor inlet

7) Increasing ram effect with increased speed Report

reduces thrust due to reduced compressor efficiency

increases thrust due to increased maximum airflow

reduces thrust due to reduced turbine temperature

8) The highest heat to metal contact in a jet engine is the Report

burner cans

turbine blades

turbine inlet guide vanes

9) Which compressor type gives the greatest advantages for both starting flexibility and improved high altitude performance?. Report

Single spool, axial flow

Split spool, axial flow

Dual stage, centrifugal flow

10) Which of the following is the ultimate limiting factor of turbine engine operation?. Report

Burner can pressure

Compressor inlet air temperature

Turbine inlet temperature

11) At altitude, idling RPM is Report

lower than at sea level

higher than at sea level

same as at sea level

12) Thrust Report

increases with high temperature

increases with low temperature

decreases with low temperature

13) Which of the following variables affect the inlet air density of a turbine engine? Report

Altitude of the aircraft, Ambient temperature

Compression ratio, Turbine inlet temperature, Altitude of the aircraft, Ambient temperature

Speed of the aircraft, Compression ratio, Turbine inlet temperature,Altitude of the aircraft

14) The propulsive efficiency is Report

low, with a low mass flow acceleration

high, with a low mass flow acceleration

high, with a high mass flow acceleration

15) The RPM for maximum power would be Report

lower on a colder day

lower on a hotter day

greater on a colder day

16) How does engine thrust vary with temperature? Report

Increase in temperature gives greater thrust because of low friction in compressors

Low temperatures give low thrust

Low temperature gives greater mass flow and therefore greater thrust

17) A method of comparing engine efficiencies is by comparing Report

fuel consumption

thrust to weight ratio

specific fuel consumption

18) With a fixed throttle in a climb Report

RPM will increase

RPM will decrease

RPM will remain constant

19) The point of maximum velocity in the engine is in the Report

exhaust exit nozzle

combustion chamber

nozzle guide vanes

20) At constant RPM, the pressure ratio of the compressor and the temperature rise across the compressor Report

increases with height

decrease with height

remains constant irrespective of height

EASA Questions Mod 15: Gas Turbine Engine Set 2: Engine Performance

Set 1: Fundamentals

Set 2: Engine Performance

Set 3: Engine Inlet

Set 4: Eng. compressors

Set 5: Combustion Section

Set 6: Turbine Section

Set 7: Engine Exhaust

Set 8: Bearing and Seals

Set 9: Lubricants and Fuel

Set 10: Lubrication system

Set 11: Fuel Systems

Set 12: Air Systems

Set 13: Ignition Systems

Set 14: Engine Indication

Set 15: Power Augmentation

Set 16:Turboprop engines

Set 17: Turboshaft

Set 18: APU

Set 19:Powerplant Installation

Set 20: Fire Protection

Set 21:Engine Monitoring

Set 22: Engine Storage