PP 20

The stators in the turbine section of a gas turbine engine. ncrease the velocity of the air. Increase the pressure of the air.

The compressor stators in a gas turbine engine act as diffusers to. Decrease the velocity of the gas flow. Increase the velocity of the gas flow.

In-flight turbine engine flameouts are usually caused by. Interruption of the inlet airflow. Fuel-nozzle clogging.

In a turbine engine with a dual-spool compressor, the low speed compressor. Seeks its own best operating speed. Always turns at the same speed as the high speed compressor.

What is the function of the inlet guide vane assembly on an axial-flow compressor?. Directs the air into the first stage rotor blades at the proper angle. Converts velocity energy into pressure energy.

Which statement is true regarding jet engines?. At the lower engine speeds, thrust increases rapidly with small increases of RPM. At the higher engine speeds, thrust increases rapidly with small increases in RPM.

Some high-volume 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 over speeding of the two compressor rotors due to the lower density air.

The function of the exhaust cone assembly of a turbine engine is to. Straighten and collect the exhaust gases into a solid exhaust jet. Pipe the exhaust gases away from the aircraft.

What must be done after the fuel control unit has been replaced on a turbine engine?. Re Trim the engine. Retime the engine.

A turbine engine compressor which contains vanes on both sides of the impeller is a. Double entry centrifugal compressor. Single entry centrifugal compressor.

Turbine discharge pressure is identified in service manuals and by engine instruments as. Pt7. Tt2.

Main bearing oil seals used with turbine engines are usually what type(s)?. Labyrinth and/or carbon rubbing. Teflon and synthetic rubber.

Three types of turbine blades are. Impulse, reaction, and impulse-reaction. Reaction, converging, and diverging.

Damage to turbine vanes is apt to be greater than damage to compressor vanes because turbine vanes are subjected to much greater. Heat stress. Stress in the combustor.

Reduced blade vibration and Improved airflow characteristics In gas turbines are brought about by. Profile blade. Fir-tree blade attachment.

Which turbine engine compressor offers the greatest advantages for both starting flexibility and improved high-altitude performance?. Split-spool, axial-flow. Dual-stage, centrifugal-flow.

Jet engine turbine blades removed for detailed inspection must be re-installed in. In its original /same slot. A slot 180° away.

An advantage of the centrifugal-flow compressor. Pressure rise per stage. Frontal area.

The highest heat-to-metal contact In a jet engine is the. Turbine blades. Exhaust cone.

When aircraft turbine blades are subjected to excessive temperatures, what type of failures would you expect?. Stress rupture. Bending and torsion.

A purpose of the shrouds on the turbine blades of an axial-flow engine Is to. Reduce vibration. Shorten run-in time.

In a dual axial-flow compressor, the first stage turbine drives. Low pressure compressor. N2 compressor.

Which of the following is NOT a factor in the operation of an automatic fuel control unit used on turbojet engines?. Mixture control position. Compressor inlet air density.

Newton’s Third Law of Motion states: To every action there is an equal and opposite reaction. Force is proportional to the product of mass and acceleration.

Dirt particles in the air being introduced into the compressor of a turbine engine will form a coating on all but which of the following?. Turbine blades. Compressor blades.

Severe rubbing of turbine engine compressor blades will usually cause. Galling. Bowing.

What is meant by a shrouded turbine?. The turbine blades are shaped so that their ends form a band or shroud. The turbine wheel is enclosed by a protective shroud to contain the blades in case of failure.

What is the purpose of the pressurization and dump valve used on turbojet engines?. Allows fuel pressurization of the engine when starting and operating and dumps fuel pressure at engine shutdown. Controls the pressure of the compressor outlet by dumping air when pressure reaches an established level.

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

In what section of a turbojet engine is the jet nozzle located?. Exhaust. Turbine.