TURBINE ENGINE PART 1

Which of the following influences the operation of an automatic fuel control unit on a turbojet engine?. Burner pressure. Mixture control position. Exhaust gas temperature.

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

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

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

The abbreviation Pt7 used in turbine engine terminology means. the total inlet pressure. pressure and temperature at station 7. the total pressure at station 7.

Frequently, an aircraft's auxiliary power unit (APU) generator. is identical to the engine-driven generators. supplements the aircraft's engine-driven generators during peak loads. has a higher load capacity than the engine-driven generators.

The air passing through the combustion chamber of a turbine engine is. used to support combustion and to cool the engine. entirely combined with fuel and burned. speeded up and heated by the action of the turbines.

When starting a turbine engine, a hung start is indicated if the engine. exhaust gas temperature exceeds specified limits. fails to reach idle RPM. N(1) is normal, but N(2) is low.

The function of the exhaust cone assembly of a turbine engine is to. collect the exhaust gases and act as a noise suppressor. swirl and collect the exhaust gases into a single exhaust jet. straighten and collect the exhaust gases into a solid exhaust jet.

In an axial-flow compressor, one purpose of the stator vanes at the discharge end of the compressor is to. straighten the airflow and eliminate turbulence. increase the velocity and prevent swirling and eddying. decrease the velocity, prevent swirling, and decrease pressure.

An exhaust cone placed aft of the turbine in a jet engine will cause the pressure in the first part of the exhaust duct to. increase and the velocity to decrease. increase and the velocity to increase. decrease and the velocity to increase.

The purpose of a bleed valve, located in the beginning stages of the compressor, in an aircraft gas turbine engine is to. vent some of the air overboard to prevent a compressor stall. control excessively high RPM to prevent a compressor stall. vent high ram air pressure overboard to prevent a compressor stall.

Which statement is true regarding jet engines?. At the lower engine speeds, thrust increases rapidly with small increases in RPM. At the higher engine speeds, thrust increases rapidly with small increases in RPM. The thrust delivered per pound of air consumed is less at high altitude than at low altitude.

Between each row of rotating blades in a turbine engine compressor, there is a row of stationary blades which act to diffuse the air. These stationary blades are called. buckets. rotors. stators.

Which of the following statements is true regarding contaminants in the compressor?. Accumulation of contaminants in the compressor of a turbojet engine increases aerodynamic efficiency of the blades. Two common methods for removing dirt deposits from turbojet engine compressor blades are a fluid wash and an abrasive grit blast. The only way to remove dirt deposits is an abrasive grit blast.

In the dual axial-flow or twin spool compressor system, the first stage turbine drives the. N(1) and N(2) compressors. N(2) compressor. N(1) compressor.

A condition known as 'hot streaking' in turbine engines is caused by. a partially clogged fuel nozzle. a misaligned combustion liner. excessive fuel flow.

The exhaust section of a turbine engine is designed to. impart a high exit velocity to the exhaust gases. increase temperature, therefore increasing velocity. decrease temperature, therefore decreasing pressure.

What is the proper starting sequence for a turbojet engine?. Ignition, starter, fuel. Starter, ignition, fuel. Starter, fuel, ignition.

When necessary, APU engine cooling before shutdown may be accomplished by. unloading the generator(s). closing the bleed air valve. opening the bleed air valve.

The stators in the turbine section of a gas turbine engine. increase the velocity of the gas flow. decrease the velocity of the gas flow. increase the pressure of the gas flow.

The blending of blades and vanes in a turbine engine. is usually accomplished only at engine overhaul. should be performed parallel to the length of the blade using smooth contours to minimize stress points. may sometimes be accomplished with the engine installed, ordinarily using power tools.

Fuel scheduling during APU start and under varying pneumatic bleed and electrical loads is maintained. manually through power control lever position. automatically by the APU fuel control system. automatically by an aircraft main engine fuel control unit.

The function of an APU air inlet plenum is to. increase the velocity of the air before entering the compressor. decrease the pressure of the air before entering the compressor. stabilize the pressure of the air before it enters the compressor.

In a turbine engine with a dual-spool compressor, the low speed compressor. always turns at the same speed as the high speed compressor. is connected directly to the high speed compressor. seeks its own best operating speed.

Which two elements make up the axial-flow compressor assembly?. Rotor and stator. Compressor and manifold. Stator and diffuser.

Some engine manufacturers of twin spool gas turbine engines identify turbine discharge pressure in their maintenance manuals as. Pt7. Pt2. Tt7.

A gas turbine engine comprises which three main sections?. Compressor, diffuser, and stator. Turbine, combustion, and stator. Turbine, compressor, and combustion.

At what point in an axial-flow turbojet engine will the highest gas pressures occur?. At the turbine entrance. Within the burner section. At the compressor outlet.

The stator vanes in an axial-flow compressor. convert velocity energy into pressure energy. convert pressure energy into velocity energy. direct air into the first stage rotor vanes at the proper angle.

When the leading edge of a first-stage turbine blade is found to have stress rupture cracks, which of the following should be suspected?. Faulty cooling shield. Overtemperature condition. Overspeed condition.

What is the purpose of the dump valve used on aircraft gas turbine engines?. The fuel is quickly cut off to the nozzles and the manifolds are drained preventing fuel boiling off as a result of residual engine heat. The valve controls compressor stall by dumping compressor bleed air from the compressor discharge port under certain conditions. Maintains minimum fuel pressure to the engine fuel control unit inlet and dumps excessive fuel back to the inlet of the engine-driven fuel pump.

The velocity of subsonic air as it flows through a convergent nozzle. increases. decreases. remains constant.

Generally, when maximum APU shaft output power is being used in conjunction with pneumatic power. pneumatic loading will be automatically modulated to maintain a safe EGT. electrical loading will be automatically modulated to maintain a safe EGT. temperature limits and loads must be carefully monitored by the operator to maintain a safe EGT.