Q16. A series of fins grids, placed in a flow, constitutes for the fluid that passes through them:

A series of converging or divergent channels as appropriate

Q17 In a diverging channel, air particles are decelerated and they arestraightened in the engine axis

They say the profiles are straighteners

1 They say the profiles are shock absorbers.

They say the profiles are deviant

Identify the nature of speed V 2

3 The absolute speed located in the outlet of the rotor seen by the stationary part of the engine.

1 The absolute speed located in the outlet of the rotor seen by the rotating grate (rotor).

2 The relative speed located in the outlet of the rotor seen by the rotating grate (rotor).

Question 24.What can you say about a compressor which have a degree of reaction equal zero?

3 The stage gained all pressure in the stator: ΔE rotor = 0

1 The pressure gained in the stage is equal in the stator and in the rotor: so ΔE rotor = ΔE stator

2 The stage gained all pressure in the rotor: ΔE stator = 0

Q26What conclusion can be done about the operation of the last stage of axial compressor when :

3 The AoA of the profile’s fin is too small and the last stage’s rotor works in windmill. A reversal flow of air appears on the last stage of the compressor.

1 The AoA of the profile’s fin is small and an aerodynamic stall appear on the upper surface of the first stage’s rotor

.2 The AoA of the profile’s fin is too large and the first stage’s rotor works in windmil

Q32 In modern turbojet engine the anti-surging systems are four: VBV system, IGV system and VSV system:what is the name of the fourth system?

2 The double compressor assembly: Low Pressure compressor following by a High-Pressure compressor.

1 The double compressor assembly: High-Pressure compressor following by a Low-Pressure compressor.

3 The double flux nozzle: primary flow generated by the gas turbine and the secondary flow generated by the fan

Q33: Low-speed anti surge system VBV, directly improves efficiency:

Of the first stages and of the last stages simultaneously. B

Question 34.High-pressure compressor (N 2 ) deceleration. When the pilot acts on the throttle lever, the N 2 assemblydecelerates immediately because it is controlled by the fuel regulator

Due to the high inertia of N 1 , the aerodynamic link between N1 and N2 does not permit to decelerate N 1 immediately. That imposes on the N2 an air flow greater than what it can evacuate . The compressor can surge

Due to the high inertia of N 1 , the aerodynamic link between N1 and N2 does not permit to decelerate N 1 immediately. That imposes on the N2 an air flow greater than what it can evacuate . The compressor works normally

The aerodynamic link between N1 and N2 permit to decelerate N 1 immediately. That imposes on the N2 an air flow suitable with the condition of operation . The compressor can surge

Question 35.Centrifugal force is the most important mechanical stress in terms ofintensity applied on fan and compressors fins. For these reasons, in theCFM56-3 design

Fan fins and compressor fins are fixed to the disk by a device composed of dovetail foot, dovetail groove and brake pads

Fan fins and compressor fins are welded to the disk

Fan fins and compressor fins are fixed to the disk by using the technic of the “Christmas tree” form

39. Stability of the flame in the chamber: For a good stability of the flame, it is necessary to:

3 Ensure a regular supply of air and fuel and avoid flow turbulence as much as possible in the inlet section of the chamber

1 Avoid flow turbulence as much as possible in the inlet section of the chamber,

2 Ensure a regular supply of air and fuel in the combustion chamber,

40.The ratio between the fuel mass and the air mass(oxidizer) $$d_{th}=\ \frac{Masse_{fuel}}{Masse_{air}}$$ is called

3 Stoechiometric air/fuel ratio.

1 This is the secondary flow and its temperature is around 450 °C

2 This is the primary flow and its temperature is around 450 °C

3 This is the tertiary flow and its temperature is around 450 °C

Q42. Indicate the zone A

3 Zone of combustion – combustion is possible

1 Zone of extinction – no combustion is possible

2 Zone of combustion – no combustion is possible

Q43 For a given value of pressure P”, indicate the name of the limit 1:

2 there is too much air compared to fuel in the mixture and thus the combustion is no possible. This limit is called: the weak limit

1 there is too much fuel compared to air in the mixture and thus the combustion is no possible. This limit is called: the rich limit

3 there is too much air compared to fuel in the mixture and thus the combustion is possible. This limit is called: the weak limit

Q44 Regarding Module "combustion chamber," what is the exact statement:

3 The higher the combustion pressure, the greater the range of operation. The pressure stabilized the combustion

The higher the combustion pressure, the greater the range of operation. The pressure destabilized the combustion

The lower the combustion pressure, the greater the range of operation. The pressure stabilized the combustion

1 Zone of extinction – no combustion is possible

2 Zone of combustion – no combustion is possible

3 Zone of combustion – combustion is possible

Q46 For a given value of pressure P”, indicate the name of the limit 2

1 there is too much fuel compared to air in the mixture and thus the combustion is no possible. This limit is called: the rich limit

.2 there is too much air compared to fuel in the mixture and thus the combustion is no possible. This limit is called: the weak limit

3 there is too much air compared to fuel in the mixture and thus the combustion is possible. This limit is called: the weak limit

Q49Regarding Module "combustion chamber," what is the exact statement

3 The flow identified “C” is called tertiary flow: it participates to the generation of the parabolic temperature profile in the turbine inlet section

1 The flow identified “C” is called tertiary flow: it participates to the generation of the parabolic temperature profile in the turbine oulet section

2 The flow identified “C” is called tertiary flow: it participates to the cooling of the combustion casing.

Q51 Regarding Module "combustion chamber," what is the exact statemen

1 Generally, the combustion liner is made of Refractory steels,

2 Generally, the combustion liner is made of Maraging steels

3 Generally, the combustion liner is made of Stainless steels

Q52The steel designated by X30 CNS 19 - 10 is composed of:

3 0,3 % of Carbon, 19 % of Chrome and 10 % of Nickel and traces of siliceous.

1 0,3 % of Carbon, 19 % of Chrome and 10 % of Nickel and traces of manganese.

2 0,3 % of Carbon, 19 % of Chrome and 10 % of Nickel.

Question 54.In the separate or individual chamber technology, the chamber is composed of:

1 Several individual chamber housing and individual combustion liner located both around the engine. Each combustion liner is connected to the other by an intercommunication manifold.

2 One chamber housing and one combustion liners goes both around the engine. this type of combustion chamber is widely used in modern engines.

3 Several individual combustion liner located both around the engine and one combustion casing located around the engine.

Question 55.In mixed combustion chamber technology, the chamber is composed of:

3 Several individual combustion liners located around the engine and one combustion casing which goes around the engine.

1 Several individual chamber housing and individual combustion liner located both around the engine. Each combustion liner is connected to the other by an intercommunication manifold

2 One chamber housing and one combustion liners which goes both around the engine. this type of combustion chamber is widely used in modern engines.

Question 56.In conventional mixed combustion chamber technology, the advantages are the following

3 Easy cooling, Easy setting and testing, Easy maintenance, Good control of the combustion and Participate in engine rigidity

1 Participate in engine rigidity, Easy setting and testing, Easy maintenance and Good control of the combustion

2 lightness, weak diametral, Low pressure drop, Good ratio Power/Weight and Participate in engine rigidity.

Question 57.Combustion chamber evolution: Twin head annular combustionchamber is composed of two liners:

3The “idle head zone” which permit to reduce pollutants CO and CH 4 and the “Take-off head” which permit to Reduce pollutant NO.

1The “Take-off head” which permit to reduce pollutants CO and CH 4 and the “idle head zone” which permit to Reduce pollutant NO.

2The “idle head zone” which permit to reduce pollutants NO and CH 4 and the “Take-off head” which permit to Reduce pollutant CO.

Question 58.Injector evolution: The injector must work optimally such that take-off/cruise fuel mass flow rate is 30time greater that idle fuel mass flow rate

2In the same time, between idle and take-off/cruise the fuel pressure ratio is 900.

1 In the same time, between idle and take-off/cruise the fuel pressure ratio is 600.

3 In the same time, between idle and take-off/cruise the fuel pressure ratio is the same.

Question 59.Injector evolution: Regarding the figure presented above what is the exact statement:

1The pressure on the control valve piston is not sufficient to counterbalance the force exerted by the spring. The control valve remains closed and only the primary circuit is supplied:idle condition.

2The pressure on the control valve piston is sufficient to counterbalance the force exerted by the spring. The control valve is open and both circuit are supplied: take-off and cruise conditions.

3 The pressure on the control valve piston is sufficient to counterbalance the force exerted by the spring. The control valve is open and both circuit are supplied: idle conditions.

Question 60.Injector evolution: To obtain a good diffusion of the fuel in the air:

1it is necessary to impart a high rotational speed to the fuel and in a direction opposite to that given to the air by swirling grate.

2it is necessary to impart a low rotational speed to the fuel and in a direction opposite to that given to the air by swirling grate

3 it is necessary to impart a high rotational speed to the fuel and in the same direction to that given to the air by swirling grate.

Question 61.In turbojet engine:

2 The number of turbine stages is always lower than the number of stages of the compressor.

1 The number of turbine stages is always greater than the number of stages of the compressor.

3 The number of turbine stages is equal to the number of stages of the compressor.

Question 66.Limitation in deceleration. TC = turbine/compressor

2In deceleration, TC assembly leaves the stabilized regime point A on the adaptive line in the right direction in order to reach the stabilized regime point C by a succession of transient regime points.

1In acceleration, TC assembly leaves the stabilized regime point A on the adaptive line in order to reach the stabilized regime point C by following the adaptative line

3In deceleration, TC assembly leaves the stabilized regime point A on the adaptive line in the left direction in order to reach the stabilized regime point C by a succession of transient regime points

Question 67.Shape of the deceleration transient. In deceleration the fuel flow is reduced:

1 the deceleration transient move strongly on the right side and can reach the weak extinction zone

2 the deceleration transient move on the left side and may pass through the surging area.

3 the deceleration transient move strongly on the left side, may pass through the surging area and reach the rich extinction zone

Question 68.The proximity of the adaptive line to the surging line,

3 This carries the risk of the compressor stalling with each acceleration.

1 Does not cause any major engine malfunctions.

2 This carries the risk of engine extinction with each acceleration.

Gas Turbine Final USTH

Authored by Duc Nguyen

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MULTIPLE CHOICE QUESTION

10 mins • 5 pts

Fuction of air intake

Connect the infinite upstream flow to the flow in the compressor inlet.

Connect the infinite upstream flow to the flow in the turbine inlet with maximum efficiency.

Connect the infinite upstream flow to the flow in the compressor inlet with maximum efficiency.

Question 2. - The air intakes suitable for supersonic flight are:

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

- The air intakes suitable for supersonic flight are:

"PITOT" air intake: they are convergent in shape.

3 Converging-divergent type with variable section.

2 "PITOT" air intake: they are divergent in shape.

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

Air intake type?

Subsonic Pitot

Supersonic Pitot

Conver-Diver

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

flight regime for the engine

Subsonic

Sonic

Supersonic

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

Q13. Buzz is

A thermal phenomenon – interaction chock wave / boundary layer

A vibratory phenomenon – interaction chock wave / boundary layer 2

A vibratory phenomenon – interaction normal shock / oblique shock. 3

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

Question 14.The axial compressor is a dynamic machine that ensures a speed of air flow at the entrance to thecombustion chamber:

1 Independent of flight speed.

2 Proportionate to flight speed.

3 Inversely proportional to the temperature of the flame.

MULTIPLE CHOICE QUESTION

10 mins • 5 pts

q15/ Grates of stationary blades are

Rotor

Generator

Stator

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Gas Turbine Final USTH

Fuction of air intake

- The air intakes suitable for supersonic flight are:

Air intake type?

flight regime for the engine

Q13. Buzz is

Question 14.The axial compressor is a dynamic machine that ensures a speed of air flow at the entrance to thecombustion chamber:

q15/ Grates of stationary blades are

Q16. A series of fins grids, placed in a flow, constitutes for the fluid that passes through them:

Q17 In a diverging channel, air particles are decelerated and they arestraightened in the engine axis

Q18 In the Newton’s composition of speed where U, V and W aremathematical vector, we can write the following relationship

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