M15 MCQs Questions
Question Number 1: On an axial-flow dual-compressor forward-fan engine, the fan rotates at the same speed as the:
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Option A: Low-pressure turbine
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Option B: High-pressure compressor
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Option C: Forward turbine wheel
Question Number 2: A turbojet engine produces thrust by giving:
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Option A: More acceleration to a small mass of air
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Option B: Large acceleration to a large mass of air
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Option C: Low acceleration to a large mass of air
Question Number 3: The basic gas turbine engine is divided into cold and hot sections. Which components form the hot section?
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Option A: Engine inlet, compressor, and turbine
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Option B: Combustor, diffuser, and exhaust
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Option C: Combustor, turbine, and exhaust
Correct Answer: Option C – Combustor, turbine, and exhaust
Question Number 4: Gas Turbine jet engine derives its thrust by:
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Option A: Drawing air into the compressor
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Option B: Impingement of propelling gases on outside air
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Option C: Reaction of the propelling gases
Question Number 5: Which symbol may be used to identify turbine discharge pressure?
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Option A: Pt7
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Option B: Pt2
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Option C: Tt7
Question Number 6: In a free-turbine engine:
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Option A: A clutch connects the compressor and output shaft
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Option B: There is direct drive with a free-wheel unit
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Option C: There is no mechanical connection to the compressor
Question Number 7: Bernoulli’s Theorem states that in a flowing gas:
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Option A: Static and dynamic pressures are equal
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Option B: Static pressure is always less than dynamic pressure
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Option C: Total energy remains constant
Question Number 8: The working fluid in a gas turbine engine is:
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Option A: Gasoline
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Option B: Kerosene
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Option C: Air
Question Number 9: Which statement correctly describes aircraft engine propulsion?
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Option A: Turbojets and turbofans accelerate a small mass of air slightly
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Option B: Turboprops convert only half exhaust energy into propeller power
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Option C: Propellers accelerate a large mass of air slightly
Question Number 10: As subsonic airflow passes through a convergent nozzle, its velocity:
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Option A: Decreases
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Option B: Increases
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Option C: Remains constant
Question Number 11: In a twin-spool axial-flow compressor system, the forward (first stage) turbine is mechanically coupled to drive the:
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Option A: N2 compressor
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Option B: N1 and N2 compressors
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Option C: N1 compressor
Question Number 12: Within an axial-flow turbojet engine operating at steady state, the location of the maximum gas pressure is found:
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Option A: At the compressor outlet
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Option B: At the turbine inlet
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Option C: Within the combustion chamber
Question Number 13: Aircraft engine noise certification and assessment are typically expressed using which standardized acoustic measurement unit?
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Option A: Effective Perceived Noise Decibels (EPNdB)
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Option B: Decibels (dB)
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Option C: Sound pressure level
Question Number 14: In a gas turbine engine, the diffuser section is installed between which two major engine components?
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Option A: Combustion section and turbine section
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Option B: Station No. 7 and Station No. 8
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Option C: Compressor section and combustion section
Question Number 15: If the low-pressure (LP) shaft in a multi-spool gas turbine engine fails due to shear, which condition is most likely to occur?
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Option A: Turbine runaway
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Option B: Compressor overspeed
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Option C: Compressor underspeed