Gas Turbine Engine Assessment 1

Aircraft Powerplant

exposure to high temperatures.

Turbine blades are generally more susceptible to operating damage than compressor blades because of

Compressor outlet

At what stage in a turbine engine is gas pressure the greatest?

pressure rise per stage

An advantage of the centrifugal-flow compressor is its

pressure cycle

The Brayton cycle is known as the constant _____.

ramjet

A pulse jet engine is a modification of the

fan

In a turbofan engine the primary source of thrust is the?

In the P-V diagram of the Brayton Cycle, which parameter is constant?

Pressure

What is the advantage of double face impeller over a single face impeller?

It has a higher volume of air

A Pure Turbo-Jet engine gives:

A small acceleration to a large mass of air.

The purpose of an air inlet is to provide a relatively ________ supply of air to the ________ of the ________ compressor.

turbulent free - face - low pressure

Chemical rockets are further classified into:

Liquid and solid propellant

The compression ratio of an axial-flow compressor is a function of the

number of compressor stages.

What section of a Gas Turbine engine increases the mass of the air

Cold Section

When airflow is at subsonic speeds and goes through a converging duct, the pressure

decreases and velocity increases

When airflow is at supersonic speeds and goes through a diverging duct, the pressure

decreases and velocity increases

Component that supplies compressed air in the combustion chamber

Compressor

What is the major function of the turbine assembly in a turbojet engine?

Supplies the power to turn the compressor.

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.

Reduced blade vibration and improved airflow characteristics in gas turbines are brought about by

shrouded turbine rotor blades.

Turbine blades are generally more susceptible to operating damage than compressor blades because of

exposure to high temperatures.

The two types of centrifugal compressor impellers are

single entry and double entry.

Newton's First Law of Motion, generally termed the Law of Inertia, states:

Everybody persists in its state of rest, or of motion in a straight line, unless acted upon by some outside force.

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

Exhaust.

A purpose of the shrouds on the turbine blades of an axial-flow engine is to

reduce vibration.

At what point in an axial-flow turbojet engine will the highest gas pressures occur?

At the compressor outlet.

What is the function of the stator vane assembly at the discharge end of a typical axial-flow compressor?

To straighten airflow to eliminate turbulence.

What is meant by a double entry centrifugal compressor?

A compressor with vanes on both sides of the impeller.

In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?

Can

Which is not an advantages of Centrifugal Flow Compressor

Large Frontal Area

The non-rotating axial-flow compressor airfoils in an aircraft gas turbine engine, are called

stator vanes.

What type of turbine blade is most commonly used in aircraft jet engines?

Impulse-reaction.

The function of the exhaust cone assembly of a turbine engine is to

straighten and collect the exhaust gases into a solid exhaust jet.

What is the profile of a turbine engine compressor blade?

A reduced blade tip thickness.

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.

The exhaust section of a turbine engine is designed to

impart a high exit velocity to the exhaust gases.

The pressure of subsonic air as it flows through a convergent nozzle

decreases.

Three types of turbine blades are

impulse, reaction, and impulse-reaction.

What is the primary advantage of an axial-flow compressor over a centrifugal compressor?

Greater pressure ratio.

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

stators.

Which of the following variables affect the inlet air density of a turbine engine? 1. Speed of the aircraft. 2. Compression ratio. 3. Turbine inlet temperature. 4. Altitude of the aircraft. 5. Ambient temperature. 6. Turbine and compressor efficiency.

1, 4, 5.