Q1. When it is produced stagnation pressure losses in the inlets:
A. Increase thrust
B. Increase Specific Fuel Consumption
C. Decrease thrust
D. A and B are correct
Q2. Mark the wrong answer:
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
Q3. Supersonic inlets can be:
A. 2D or spike
B. 3D or wedge
C. 2D or wedge
Q4. Which are the functions of compressors?
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
Q5. Which are the types of compressors? Choose the wrong answer:
A. Bi-directional
B. Axial
C. Centrifugal
D. B and C are right
Q6. Which are the elements of centrifugal compressors? Choose the incorrect answer:
Diffuser
Stabilizer
Front case
Impeller
Q7. In centrifugal compressors, leaving the impeller the air passes into the diffuser section where the passages form
Divergent nozzles
Convergent nozzles
Divergent and convergent nozzles
None of them
Q8. Mark the incorrect option:
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
Q1. If the angle of attack of the rotor blades is too large...
Boundary layer can stall
Will cause transonic zones
Can cause heating problem
Nothing can go wrong
Q2. To ensure the working conditions for the compressor with different velocities via variable incident vanes... (Choose the wrong answer)
Variable IGV
Variable stator blades
They close when velocity reduces
None of the above
Q3. A compression map...
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
Q4. Combustion Chambers... (choose the wrong answer)
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
Q5. Which is not a cooling method?
Corrugated strip cooling
Machined cooling ring
Splash cooling strip
Capsule icing allocation
Q6. Types of combustion chambers...
Tubular
Tubo-annular
Annular
All the above
Q7. Fuel Nozzle types...
Vaporiser
Atomiser
Both A and B are correct
Both A and B are false
Q8. Both impulse and reaction are energy transfer systems
Q1. What are the different configuration of turbine?
A. Compressor
B. IMPULSE TURBINE
C. REACTION TURBINE
D. B and C
Q2. What kind of engines are used nowadays in modern fighters?
Turbofan of low derivation
Turbofan of high derivation
Piston engines
Stratojet
Q3. Why the afterburner is an inefficient method to increase the thrust
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.
Q4. Choose the correct answer
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.
Q5. Afterburning
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.
Q6. How the use of afterburning affects the nozzle?
A. The nozzle expands
B. the nozzle contracts
C. the nozzle stays fixed
D. the nozzle opens and closes periodically
Q7. What kind of Turbofans exist nowadays?
A. low derivation
B. high derivation
C. turboreactors
D. a and b are correct
Q8. Turbofans of high derivation ratio are used in:
Commercial planes
Fighters planes
Helicopters
Q1. Which of these functions doesn ́t belong to the internal air system in engines?
Control of bearing axial loads
Cooling the engine
Measure the ground speed of the plane
Engine anti-icing
Q2. The sealing functions are:
Prevent oil leakage from engine bearing chambers
Control cooling airflows
Prevent ingress of the mainstream gas into turbine disc cavities
All of the above
Q3. Low compression airflow:
Avoid the formation of chemtrails
It is used for cooling and pressurization
Is more powerful than high compression air flow
Q4. Accesory drives are cooled by:
Venturi effect
De-icing systems
Cooling oil
All are wrong
Q5. Fuel system can be used for:
Control of thrust
Hydraulic controls of engine system
Oil cooling
All are right
Q6. What is the meaning of JP:
James Patterson, the inventor of the fuel
Jet Purpose
Jet Propeller
None of above
Q7. What characteristics makes fuel so important for airlines.
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
Q8. JP-8 is equivalent to:
JET A-1
B
AVCAT ( Aviation Carrier Turbine fuel)
GPA (General Purpose Aviation fuel)
