Modulo 15 EASA Turbine Two

The 'core engine' or 'gas generator' is made up of the following components:. Inlet, compressor, combustion chamber, turbine, exhaust. Turbine, combustion chamber, compressor.

The principle of jet propulsion is. the calorific value of fuel burnt is equal to aircraft. every action has a equal and opposite reaction.

Boyle's law states that, at constant temperature, if a gas is compressed. its absolute pressure is proportional to its volume. its absolute pressure is inversely proportional to its volume.

What part of a jet engine has the most potential energy?. Immediately after the combustion chamber. Just before the combustion chamber.

Ram effect' due to aircraft forward speed will cause the efficiency of the engine to. remain constant. increase.

The efficiency of a gas turbine engine at altitude. decreases. increases.

Which statement is true regarding jet engines?. 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.

Some turboprop and turbojet engines are equipped with two spool or split compressors. When these engines are operated at high altitudes, the. low pressure rotor will increase 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.

Ram effect' due to aircraft forward speed will cause the thrust of the engine to. remain constant. decrease.

With a fixed throttle, and with increased massairflow, what happens to EPR?. EPR goes up. EPR goes down.

At what stage in a gas turbine engine are gas pressures the greatest?. Compressor outlet. Turbine outlet.

Increasing ram effect with increased speed. reduces thrust due to reduced compressor efficiency. increases thrust due to increased maximum airflow.

The highest heat to metal contact in a jet engine is the. turbine inlet guide vanes. turbine blades.

Which compressor type gives the greatest advantages for both starting flexibility and improved high altitude performance. Single spool, axial flow. Split spool, axial flow.

Which of the following is the ultimate limiting factor of turbine engine operation?. Burner can pressure. Turbine inlet temperature.

At altitude, idling RPM is. same as at sea level. higher than at sea level.

Thrust. increases with high temperature. increases with low temperature.

Which of the following variables affect the inlet air density of a turbine engine?. Altitude of the aircraft, Ambient temperature. Compression ratio, Turbine inlet temperature, Altitude of the aircraft, Ambient temperature.

The propulsive efficiency is. low, with a low mass flow acceleration. high, with a low mass flow acceleration.

The RPM for maximum power would be. lower on a colder day. lower on a hotter day.

How does engine thrust vary with temperature?. Low temperature gives greater mass flow and therefore greater thrust. Low temperatures give low thrust.

A method of comparing engine efficiencies is by comparing. specific fuel consumption. thrust to weight ratio.

With a fixed throttle in a climb. RPM will increase. RPM will remain constant.

The point of maximum velocity in the engine is in the. exhaust exit nozzle. nozzle guide vanes.

At constant RPM, the pressure ratio of the compressor and the temperature rise across the compressor. remains constant irrespective of height. increases with height.

With the aircraft stationary, propulsive efficiency. depends on RPM. is minimum.

The efficiency of conversion of kinetic energy into propulsive work is a measure of. mechanical efficiency. propulsive efficiency.

What effect does high atmospheric humidity have on the operation of a jet engine?. Decreases compressor and turbine RPM. Has little or no effect.

Power is adjusted in a gas turbine engine by. increasing fuel flow. increasing air and fuel flow.

The engine rating plug. is permanently connected to the E E C. is permanently connected to the Engine casing.

Flat Rated thrust is defined as. thrust at the ambient temperature point above which thrust drops below 100%. that power achieved at maximum EGT.

Thrust rating on an FADEC controlled engine can be changed by. varying the ballast resistor in the EGT system. changing the engine rating plug.

Propeller torque is analogous to. engine RPM. shaft horsepower.

The total power in a turboprop engine is the. SHP. E S HP .

In a dive, with the throttles fixed, the EPR will. not change. decrease.

With an increase in forward speed, the engine thrust. decreases slightly but recover due to ram effect. decreases.

The main factor considered when designing an engine is. maximum turbine temperature. maximum fuel consumption.

To ensure an engine maintains self sustaining speed. idle increases with density decrease. idle remains same for any density.

A factor that limits EGT is the. jet pipe. turbine.

Thrust will. increase at high temperatures. increase at low temperatures.

Across the turbines, there is. a general temperature rise. a general temperature drop.

If the throttle position remains constant. with increasing OAT, RPM and TGT will increase. with increasing OAT, TGT will increase.

If an aircraft climbs with a fixed throttle position. thrust decreases and RPM increases. thrust and RPM remain the same.

Ram pressure recovery will generally take effect at aircraft speeds of. mach 0.1 - 0.2. only when the aircraft is stationary with engines running.

As the air is passed through the turbine, due to the convergent shape formed between adjacent blades. pressure decreases, velocity increases, temperature increases. pressure decreases, velocity increases, temperature decreases.

The hottest component in a gas turbine engine is. the nozzle guide vanes. the combustion chamber.

The basic equation for thrust is. thrust = mass * acceleration. thrust = mass * velocity.

To maintain the selected RPM of a gas turbine at altitude. the pilot will have to throttle back. the fuel will automatically be reduced as the aircraft climbs.

The term Pb means. burner pressure measured at the combustion chamber. burner pressure measured at the diffuser case.

Which of the following is not an engine rating?. Maximum Continuous. Idle.