GTE Question and answer

b

Turbine blades are generally more susceptible to operating damage than compressor blades because of
a. higher centrifugal loading
b. expose to high temperatures
c. high pressure and high velocity gas flow
d. exposure to high pressure

b

At what stage in a turbine engine is gas pressure the greatest?
a. Compressor inlet
b. Compressor outlet
c. Turbine outlet
d. Exhaust Cone

a

An advantage of the centrifugal-flow compressor is its
a. pressure rise per stage
b. ram efficiency
c. peak efficiency
d. steady temperature

a

The Brayton cycle is known as the constant
a. pressure cycle
b. mass cycle
c. temperature cycle
d. polytrophic cycle

a

A pulse jet engine is a modification of the
a. ramjet
b. rocket
c. pure jet
d. turbine

c

In a turbofan engine, the primary source of thrust is the?
a. exhaust
b. high velocity jet
c. fan
d. afterburner

a

In the P-V diagram of the Brayton Cycle, which parameter is constant?
a. Pressure
b. Volume
c. Temperature
d. Entropy

d

In the T-S diagram of the Brayton Cycle, which parameter is constant?
a. Pressure
b. Volume
c. Temperature
d. Entropy

a

What is the advantage of a double-face impeller over a single-face impeller?
a. It has a higher volume of air
b. It has a higher-pressure ratio
c. It is lighter in weight
d. It has higher strength

d

A Pure Turbo-Jet engne gives:
a. A small acceleration to a large mass of air
b. A large acceleration to a large mass of air
c. A small acceleration to a small mass of air
d. A large acceleration to a small mass of air

a

A purpose of an air inlet is to provide a relatively _____ supply of air to the ____ of the _____ compressor
a. turbulent free- face - low pressure
b. turbulent - face - low pressure
c. turbulent free - rear - low pressure
d. turbulent free - face - high pressure

c

Chemical rockets are further classified into:
a. Breathing and air-breathing
b. Impulse and reaction
c. Liquid and solid propellant
d. Single and multi-stages

a

The compression ratio of an axial-flow compressor is a function of the
a. the number of compressor stages
b. rotor diameter
c. air inlet velocity
d. number of stator vanes

d

What section of a Gas turbine engine increases the mass of the air
a. Hot section
b. Warm section
c. Freezing section
d. Cold section

a

What section of a Gas turbine engine increases the velocity of the air
a. Hot section
b. Warm section
c. Freezing section
d. Cold section

b

When airflow is at subsonic speeds and goes through a converging duct, the pressure
a. decreases and velocity decreases
b. decreases and velocity increases
c. increases and velocity increases
d. and velocity remains the same

b

When airflow is at supersonic speeds and goes through a diverging duct, the pressure
a. decreases and velocity decreases
b. decreases and velocity increases
c. increases and velocity increases
d. and velocity remains the same

c

Component that supplies compressed air in the combustion chamber
a. Exhaust Cone
b. Turbine
c. Compressor
d. Stator

b

What is the major function of the turbine assembly in a turbojet engine?
a. Directs the gases in the proper direction to the tailpipe
b. Supplies the power to turn the compressor
c. Increases the temperature of the exhaust gases
d. Supplies the power to the accessory parts

b

In an axial flow compressor, one purpose of the stator vanes at the discharge end of the compressor is to
a. promotes turbulent flow
b. straightens the airflow and eliminate turbulence
c. increases the velocity and prevent swirling and eddying
d. decreases the velocity, prevent swirling, and decrease pressure

c

Reduced blade vibration and improved airflow characteristics in gas turbines are brought about by
a. fir-tree blade attachment
b. impulse type blades
c. shrouded turbine rotor blades
d. shorter blade chord

b

Turbine blades are generally more susceptible to operating damage than compressor blades because of
a. higher centrifugal loading
b. expose to high temperatures
c. high pressure and high velocity gas flow
d. exposure to ram air

a

The two types of centrifugal compressor impellers are:
a single entry and double entry
b. rotor and stator
c. impeller and diffuser
d. bypass and no bypass

c

In what section of a turbojet engine is the jet nozzle located?
a. Combustion
b. Turbine
c. Exhaust
d. Air inlet

a

The purpose of the shrouds on the turbine blades of an axial flow engine is to
a. reduce vibration
b. increase tip speed
c. reduce air entrance
d. reduce operating temperatres

c

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

b

What is the function of the stator vane assembly at the discharge end of a typical axial-flow compressor?
a. To harness the energy and drive the turbine
b. To straighten airflow to eliminate turbulence
c. To direct the flow of gases into the combustion chambers
d. To increase air swirling motion into the combustion chambers

c

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

a

In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?
a. Can
b. Can annular
c. Annular
d. Can less

c

Which is not an advantage of Centrifugal flow compressor
a. Simplicity in Manufacture
b. low weight
c. Large Frontal Area
d. Low starting Power Requirements

b

The non rotating axial flow compressor airfoils in an aircraft gas turbine engine are called
a. Pressurization vanes
b. stator vanes
c. bleed vanes
d. Rotor vanes

c

What type of turbine blade is most commonly used in aircraft jet engines?
a. Reaction
b. impulse
c. Impulse-reaction
d. Direct

c

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

b

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

b

Some high volume turboprop and turbojet engines are equipped with two-spool or split compressors. When these engines are operated at high altitudes, the
a. low-pressure rotor will decrease in speed as the compressor load increases in the lower-density air
b. low- pressure rotor will increase in speed as the compressor load decreases in the lower-density
c. throttle must be retarded to prevent over speeding of the high pressure rotor due to the lower density
d. low-pressure rotor will decrease in speed as the compressor load decreases in the lower-density air

b

The exhaust section of a turbine engine is designed to
a. remove a much heat in the combustion chamber
b. impart a high exit velocity to the exhaust gases
c. increase temperature, therefore increasing velocity
d. decrease the temperature, therefore decreasing pressure

b

The pressure of a subsonic air as it flows through a convergent nozzle
a. increases
b. decreases
c. remains constant
d. fluctuates

c

Three types of turbine blades
a. octivius, scorpio, venom
b. reaction, converging, and diverging
c. impulse, reaction, and impulse reacton
d. impulse, vector, and impulse-vector

c

What is the primary advantage of an axial flow compressor over a centrifugal compressor?
a. high frontal area
b. less expensive
c. greater pressure ratio
d. axial arrangement of blades

c

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

b

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

a. 1,3,6
b. 1,4,5
c. 4,5,6
d. 1,2,3