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