13299204
Description
Quiz by Ismael Vázquez, updated more than 1 year ago
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Created by Ismael Vázquez
about 6 years ago
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Question 1
Question
Q1. Which was the first jet-powered aircraft?
Answer
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A. Spitfire
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B. Junkers Ju 87
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C. Bell P-59
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D. Heinkel He-178
Question 2
Question
Q2. Why was the aircraft Gloster Meteor so popular?
Answer
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A. It was the first jet-powered aircraft.
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B. It was the first aircraft to break the sound barrier.
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C. It was the first aircraft with sufficient speed to attack the German V1 flying bomb.
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D. It was the first aircraft that could perform sustained inverted flight.
Question 3
Question
Q3. The engine Jumbo 004B was a milestone in the turbojet engine because…
Answer
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A. It had the first axial compressor in a turbojet engine.
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B. It had the biggest change of pressure in one stage up until then.
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C. It was the most produced engine in the WWII.
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D. All the answers are false.
Question 4
Question
Q4. Mark the right answer:
Answer
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A. A turboprop produces more impulse than a turbojet.
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B. A low-BPR turbofan has a bigger SFC than a high-BPR turbofan in low speeds.
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C. A turboprop has a bigger SFC than a turbojet in low speeds.
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D. A turboprop has the least SFC at any speed.
Question 5
Question
Q5. Which statement is true?
D. None of the above
Answer
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A. Axial compressor is a compressor in which the gas or working fluid principally flows parallel to the axis of rotation
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B. Centrifugal compressor is a compressor in which the gas or working fluid principally flows with a radial component through the compressor.
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C. A and B are correct
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D. None of the above
Question 6
Question
Q6. In jet engines with greater impulse (I):
Answer
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A. Large size.
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B. Smaller size.
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C. The division between thrust (E) and airflow (G) is lower
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D. None of the above
Question 7
Question
Q7. The specific fuel consumption (SFC) is:
Answer
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(E (thrust) )/(G (airflow) )
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(c (consumption) )/(E (thrust) )
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(G (airflow) )/(E (thrust) )
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(G (airflow) )/(c (consumption) )
Question 8
Question
Q8. In turbofan the bypass ratio is:
Answer
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(Secondary flow )/(Primary flow ) ; and primary flows through the combustion chamber.
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(Secondary flow )/(Primary flow ) ; and secondary flows through the combustion chamber.
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(Primary flow )/(Secondary flow ) ; and primary flows through the combustion chamber.
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(Primary flow )/(Secondary flow ) ; and secondary flows through the combustion chamber.
Question 9
Question
Q1. When it is produced stagnation pressure losses in the inlets:
Answer
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A. Increase thrust
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B. Increase Specific Fuel Consumption
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C. Decrease thrust
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D. A and B are correct
Question 10
Question
Q2. Mark the wrong answer:
Answer
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A. Generally, subsonic inlets are named “Pitot”
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B. Typical parameters are NACA Serie 1 profiles
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C. Drag is not due to inlet outer surface
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D. The shape is aerodynamically smooth
Question 11
Question
Q3. Supersonic inlets can be:
Answer
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A. 2D or spike
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B. 3D or wedge
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C. 2D or wedge
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D. A and B are correct
Question 12
Question
Q4. Which are the functions of compressors?
Answer
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A. Increase the pressure of the air mass received
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B. Take the air to the combustion section
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C. Provide bleed air for cabin pressure and other systems
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D. All are correct
Question 13
Question
Q5. Which are the types of compressors? Choose the wrong answer:
Answer
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A. Bi-directional
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B. Axial
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C. Centrifugal
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D. B and C are right
Question 14
Question
Q6. Which are the elements of centrifugal compressors? Choose the incorrect answer:
Answer
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A. Diffuser
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B. Stabilizer
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C. Front case
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D. Impeller
Question 15
Question
Q7. In centrifugal compressors, leaving the impeller the air passes into the diffuser section where the passages form
Answer
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A. Divergent nozzles
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B. Convergent nozzles
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C. Divergent and convergent nozzles
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D. None of them
Question 16
Question
Q8. Mark the incorrect option:
Answer
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A. Single-spool is a type of axial compressors
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B. Multi-spool is a type of centrifugal compressors
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C. Generally, in aviation are used single-spool and two spools
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D. Multi-spool is a type of axial compressors
Question 17
Question
Q1. If the angle of attack of the rotor blades is too large…
Answer
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A. Boundary layer can stall
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B. Will cause transonic zones
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C. Can cause heating problem
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D. Nothing can go wrong
Question 18
Question
Q2. To ensure the working conditions for the compressor with different velocities via variable incident vanes… (Choose the wrong answer)
Answer
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A. Variable IGV
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B. Variable stator blades
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C. They close when velocity reduces
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D. None of the above
Question 19
Question
Q3. A compression map…
Answer
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A. Provides information of pressure ratio an equivalent flow for a throttle setting (IDLE-100%)
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B. Does not give info relative to throttle settings
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C. Gives info relative to weather conditions
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Both A and C are correct
Question 20
Question
Q4. Combustion Chambers… (choose the wrong answer)
Answer
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A. Ensure stable fuel burn with max. Thermal efficiency in large conditions ranges
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B. Are not used for aviation engines
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C. Max temperature (850-1700ºC) due to turbine materials
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D. Combustion is initiated by an electric spark from an igniter plug
Question 21
Question
Q5. Which is not a cooling method?
Answer
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A. Corrugated strip cooling
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B. Machined cooling ring
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C. Splash cooling strip
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D. Capsule icing allocation
Question 22
Question
Q6. Types of combustion chambers…
Answer
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A. Tubular
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C. Annular
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B. Tubo-annular
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All the above
Question 23
Question
Q7. Fuel Nozzle types…
Answer
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A. Vaporiser
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B. Atomiser
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C. Both A and B are correct
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D. Both A and B are false
Question 24
Question
Q8. Both impulse and reaction are energy transfer systems
Answer
- True
- False
Question 25
Question
Q1. What are the different configuration of turbine?
A. Compressor
B. IMPULSE TURBINE
C. REACTIONTURBINE
D. B and C
Answer
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A. compressor
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B. Impulse Turbine
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C. Reaction Turbine
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B and C
Question 26
Question
Q2. What kind of engines are used nowadays in modern fighters?
Answer
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A. Turbofan of low derivation
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B. Turbofan of high derivation
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C. Piston engines
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D. Stratojet
Question 27
Question
Q3. Why the afterburner is an inefficient method to increase the thrust
Answer
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A. Because it implies more drag inside engine
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B. Indeed, it is a really efficient method, especially in military aviation
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Because of increment in thrust, that is proportional to (√T_PC)/(√T_NoPC )
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D. Because the increment in thrust follows a linear gradient, so that is not too much.
Question 28
Question
Q4. Choose the correct answer
Answer
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A. Afterburning provides the best method of thrust augmentation for short periods.
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B. Afterburning provides the worst method of thrust augmentation for short periods.
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C. Afterburning provides the best method of thrust augmentation for long periods.
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D. Afterburning provides the worst method of thrust augmentation for long periods.
Question 29
Question
Q5. Afterburning
Answer
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A. It is a method of augmenting the basic thrust of an engine.
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B. For military aircraft improve combat performance
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C. It is the worst method of thrust augmentation for short periods.
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D. A and B are correct
Question 30
Question
Q6. how the use of afterburning affects the nozzle?
Answer
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A. The nozzle expands
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B. the nozzle contracts
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C. the nozzle stays fixed
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D. the nozzle opens and closes periodically
Question 31
Question
Q7. What kind of Turbofans exist nowadays?
Answer
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A. low derivation
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B. high derivation
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C. turboreactors
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D. a and b are correct
Question 32
Question
Q8. Turbofans of high derivation ratio are used in
Answer
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A. Commercial planes
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B. Fighters planes
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C. None of the above
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D. Helicopters
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