Quiz by Ismael Vázquez, created more than 1 year ago

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97. SEMANAS 2018

97. SEMANAS 2018

Question 1 of 32

1

Q1. When it is produced stagnation pressure losses in the inlets:

Select one of the following:

A. Increase thrust
B. Increase Specific Fuel Consumption
C. Decrease thrust
D. A and B are correct

Explanation

Question 2 of 32

1

Q2. Mark the wrong answer:

Select one of the following:

Generally, subsonic inlets are named “Pitot”
Typical parameters are NACA Serie 1 profiles
Drag is not due to inlet outer surface
The shape is aerodynamically smooth

Explanation

Question 3 of 32

1

Q3. Supersonic inlets can be:

Select one of the following:

A. 2D or spike
B. 3D or wedge
C. 2D or wedge
D. A and B are correct

Explanation

Question 4 of 32

1

Q4. Which are the functions of compressors?

Select one of the following:

Increase the pressure of the air mass received
Take the air to the combustion section
Provide bleed air for cabin pressure and other systems
All are correct

Explanation

Question 5 of 32

1

Q5. Which are the types of compressors? Choose the wrong answer:

Select one of the following:

A. Bi-directional
B. Axial
C. Centrifugal
D. B and C are right

Explanation

Question 6 of 32

1

Q6. Which are the elements of centrifugal compressors? Choose the incorrect answer:

Select one of the following:

Diffuser
Stabilizer
Front case
Impeller

Explanation

Question 7 of 32

1

Q7. In centrifugal compressors, leaving the impeller the air passes into the diffuser section where the passages form

Select one of the following:

Divergent nozzles
Convergent nozzles
Divergent and convergent nozzles
None of them

Explanation

Question 8 of 32

1

Q8. Mark the incorrect option:

Select one of the following:

Single-spool is a type of axial compressors
Multi-spool is a type of centrifugal compressors
Generally, in aviation are used single-spool and two spools
Multi-spool is a type of axial compressors

Explanation

Question 9 of 32

1

Q1. If the angle of attack of the rotor blades is too large...

Select one of the following:

Boundary layer can stall
Will cause transonic zones
Can cause heating problem
Nothing can go wrong

Explanation

Question 10 of 32

1

Q2. To ensure the working conditions for the compressor with different velocities via variable incident vanes... (Choose the wrong answer)

Select one of the following:

Variable IGV
Variable stator blades
They close when velocity reduces
None of the above

Explanation

Question 11 of 32

1

Q3. A compression map...

Select one of the following:

A. Provides information of pressure ratio an equivalent flow for a throttle setting (IDLE-100%)
B. Does not give info relative to throttle settings
C. Gives info relative to weather conditions
D. Both A and C are correct

Explanation

Question 12 of 32

1

Q4. Combustion Chambers... (choose the wrong answer)

Select one of the following:

Ensure stable fuel burn with max. Thermal efficiency in large conditions ranges
Are not used for aviation engines
Max temperature (850-1700oC) due to turbine materials
Combustion is initiated by an electric spark from an igniter plug

Explanation

Question 13 of 32

1

Q5. Which is not a cooling method?

Select one of the following:

Corrugated strip cooling
Machined cooling ring
Splash cooling strip
Capsule icing allocation

Explanation

Question 14 of 32

1

Q6. Types of combustion chambers...

Select one of the following:

Tubular
Tubo-annular
Annular
All the above

Explanation

Question 15 of 32

1

Q7. Fuel Nozzle types...

Select one of the following:

Vaporiser
Atomiser
Both A and B are correct
Both A and B are false

Explanation

Question 16 of 32

1

Q8. Both impulse and reaction are energy transfer systems

Select one of the following:

True
False

Explanation

Question 17 of 32

1

Q1. What are the different configuration of turbine?

Select one of the following:

A. Compressor
B. IMPULSE TURBINE
C. REACTION TURBINE
D. B and C

Explanation

Question 18 of 32

1

Q2. What kind of engines are used nowadays in modern fighters?

Select one of the following:

Turbofan of low derivation
Turbofan of high derivation
Piston engines
Stratojet

Explanation

Question 19 of 32

1

Q3. Why the afterburner is an inefficient method to increase the thrust

Select one of the following:

Because it implies more drag inside engine
Indeed, it is a really efficient method, especially in military aviation
Because of increment in thrust, that is proportional to (Tpc)^1/2 / (T noPC)^1/2
Because the increment in thrust follows a linear gradient, so that is not too much.

Explanation

Question 20 of 32

1

Q4. Choose the correct answer

Select one of the following:

A. Afterburning provides the best method of thrust augmentation for short periods.
B. Afterburning provides the worst method of thrust augmentation for short periods.
C. Afterburning provides the best method of thrust augmentation for long periods.
D. Afterburning provides the worst method of thrust augmentation for long periods.

Explanation

Question 21 of 32

1

Q5. Afterburning

Select one of the following:

A. It is a method of augmenting the basic thrust of an engine.
B. For military aircraft improve combat performance
C. It is the worst method of thrust augmentation for short periods.
D. A and B are correct

Explanation

Question 22 of 32

1

Q6. How the use of afterburning affects the nozzle?

Select one of the following:

A. The nozzle expands
B. the nozzle contracts
C. the nozzle stays fixed
D. the nozzle opens and closes periodically

Explanation

Question 23 of 32

1

Q7. What kind of Turbofans exist nowadays?

Select one of the following:

A. low derivation
B. high derivation
C. turboreactors
D. a and b are correct

Explanation

Question 24 of 32

1

Q8. Turbofans of high derivation ratio are used in:

Select one of the following:

Commercial planes
Fighters planes
None of the above
Helicopters

Explanation

Question 25 of 32

1

Q1. Which of these functions doesn ́t belong to the internal air system in engines?

Select one of the following:

Control of bearing axial loads
Cooling the engine
Measure the ground speed of the plane
Engine anti-icing

Explanation

Question 26 of 32

1

Q2. The sealing functions are:

Select one of the following:

Prevent oil leakage from engine bearing chambers
Control cooling airflows
Prevent ingress of the mainstream gas into turbine disc cavities
All of the above

Explanation

Question 27 of 32

1

Q3. Low compression airflow:

Select one of the following:

Avoid the formation of chemtrails
It is used for cooling and pressurization
Is more powerful than high compression air flow
None of them

Explanation

Question 28 of 32

1

Q4. Accesory drives are cooled by:

Select one of the following:

Venturi effect
De-icing systems
Cooling oil
All are wrong

Explanation

Question 29 of 32

1

Q5. Fuel system can be used for:

Select one of the following:

Control of thrust
Hydraulic controls of engine system
Oil cooling
All are right

Explanation

Question 30 of 32

1

Q6. What is the meaning of JP:

Select one of the following:

James Patterson, the inventor of the fuel
Jet Purpose
Jet Propeller
None of above

Explanation

Question 31 of 32

1

Q7. What characteristics makes fuel so important for airlines.

Select one of the following:

It is flamable and dangerous
It isn ́t ecological
Fuel isn ́t so important for aeronautic operators
It represents almost a 40%, of the total cost, of a flight

Explanation

Question 32 of 32

1

Q8. JP-8 is equivalent to:

Select one of the following:

JET A-1
B
AVCAT ( Aviation Carrier Turbine fuel)
GPA (General Purpose Aviation fuel)

Explanation