TURBINE ENGINE PART 4

Who establishes mandatory replacement times for critical components of turbine engines?. The FAA. The component manufacturer. The engine manufacturer.

If a turbine engine is unable to reach takeoff EPR before its EGT limit is reached, this is an indication that the. fuel control must be replaced. EGT controller is out of adjustment. compressor may be contaminated or damaged.

How does a dual axial-flow compressor improve the efficiency of a turbojet engine?. More turbine wheels can be used. Higher compression ratios can be obtained. The velocity of the air entering the combustion chamber is increased.

The diffuser section of a jet engine is located between. the burner section and the turbine section. the compressor section and the burner section. station 7 and station 8.

Which of the following statements is true regarding the basic gas turbine engine?. The engine is divided into three sections: cold, neutral, and hot sections. The cold section includes the engine inlet, diffuser, and compressor sections. The hot section includes the combustor, diffuser, and exhaust sections.

An APU is usually rotated during start by. a turbine impingement system. a pneumatic starter. an electric starter.

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

The Brayton cycle is known as the constant. pressure cycle. temperature cycle. mass cycle.

Which of the following acts as a diffuser in a turbine engine and converts velocity to pressure?. Impeller. Manifold. Stators.

What is the primary advantage of an axial-flow compressor over a centrifugal compressor?. High frontal area. Less expensive. Greater pressure ratio.

Which of the following can cause fan blade shingling in a turbofan engine?. Engine overtemperature. Large, rapid throttle movements. Engine overspeed and/or FOD.

An advantage of the axial-flow compressor is its. low starting power requirements. low weight. high peak efficiency.

What should be done initially if a turbine engine catches fire when starting?. Turn off the fuel and continue engine rotation with the starter. Continue engine start rotation and discharge a fire extinguisher into the intake. Continue starting attempt in order to blow out the fire.

A cool-off period prior to shutdown of a turbine engine is accomplished in order to. allow the turbine wheel to cool before the case contracts around it. prevent vapor lock in the fuel control and/or fuel lines. prevent seizure of the engine bearings.

If the RPM of an axial-flow compressor remains constant, the angle of attack of the rotor blades can be changed by. changing the velocity of the airflow. changing the compressor diameter. increasing the pressure ratio.

Which of the following engine variables is the most critical during turbine engine operation?. Compressor inlet air temperature. Compressor RPM. Turbine-inlet temperature.

Usually, most of the load placed on an APU occurs when. an electrical load is placed on the generator(s). the bleed air valve is opened. the bleed air valve is closed.

What term is used to describe a permanent and cumulative deformation of the turbine blades of a turbojet engine?. Stretch. Distortion. Creep.

What is meant by a double-entry centrifugal compressor?. A compressor that has two intakes. A two-stage compressor independently connected to the main shaft. A compressor with vanes on both sides of the impeller.

What is the purpose of the diffuser section in a turbine engine?. To increase pressure and reduce velocity. To convert pressure to velocity. To reduce pressure and increase velocity.

Which of the following is a good indication of a malfunctioning fuel nozzle when inspecting the exhaust section of an aircraft turbine engine?. Buckling of the combustion liner. Hotspots on the tail cone. Carbon build up in the exhaust.

Compressor stall is caused by. a low angle of attack airflow through the first stages of compression. a high angle of attack airflow through the first stages of compression. rapid engine deceleration.

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. Casings. Inlet guide vanes.

A purpose of the shrouds on the turbine blades of an axial-flow engine is to. reduce vibration. increase tip speed. reduce air entrance.

What are the two functional elements in a centrifugal compressor?. Turbine and compressor. Bucket and expander. Impeller and diffuser.

The procedure for removing the accumulation of dirt deposits on compressor blades is called. the soak method. field cleaning. the purging process.

On APU's equipped with a free turbine and load compressor, the primary function of the load compressor is to. provide air for combustion and cooling in the engine gas path. provide bleed air for aircraft pneumatic systems. supply the turning force for operation of the APU generator(s).

A weak fuel to air mixture along with normal airflow through a turbine engine may result in. a rich flameout. a lean die-out. high EGT.

A turbine engine hot section is particularly susceptible to which kind of damage?. Erosion. Cracking. Elongation.

Hot section inspections for many modern turbine engines are required. only at engine overhaul. only when an overtemperature or overspeed has occurred. on a time or cycle basis.

What is the profile of a turbine engine compressor blade?. The leading edge of the blade. A reduced blade tip thickness. The curvature of the blade root.

The fan rotational speed of a dual axial compressor forward fan engine is the same as the. low-pressure compressor. forward turbine wheel. high-pressure compressor.

What type of turbine blade is most commonly used in aircraft jet engines?. Reaction. Impulse. Impulse-reaction.