# Gte Tutorial 2 MCQ

22 Questions | Total Attempts: 243  Settings  GTE tutorial 2Term test practice

• 1.
The energy required to accelerate a large mass of air to a low final velocity is, in comparison to that required to accelerate a small mass of air to a high velocity is:
• A.

Higher

• B.

The same

• C.

Lower

• 2.
A turbo-jet engine gives:
• A.

A small acceleration to a large mass of air.

• B.

A large acceleration to a large mass of air.

• C.

A large acceleration to a small mass of air.

• 3.
A turbo-prop engine gives:
• A.

A small acceleration to a large mass of air.

• B.

A large acceleration to a large mass of air.

• C.

A large acceleration to a small mass of air.

• 4.
Engine efficiencies may be compared using:
• A.

Thrust : weight ratio

• B.

Specific fuel consumption.

• C.

Overall fuel consumption.

• 5.
A by-pass ratio of 3:1 means the by-pass airflow is:
• A.

Three times higher than the core flow.

• B.

A third of the core flow.

• C.

Twice the core flow.

• 6.
The density of a gas may be expressed as:
• A.

Pressure / Volume

• B.

Volume / mass

• C.

Mass / volume

• 7.
As aircraft forward speed increases, the specific fuel consumption of an engine:
• A.

Increases

• B.

Decreases

• C.

Does not change

• 8.
Which of the following factors affect the thermal efficiency of a turbine engine? 1.Turbine inlet temperature. 2.Compression ratio. 3.Ambient temperature. 4.Speed of the aircraft. 5.Turbine and compressor efficiency. 6.Altitude of the aircraft.
• A.

3, 4 and 6

• B.

1, 2 and 5

• C.

1, 2 and 6

• 9.
In a gas turbine engine, combustion occurs at a constant
• A.

Volume

• B.

Pressure

• C.

Density

• 10.
As aircraft forward speed increases the propulsive efficiency of an engine:
• A.

Increases

• B.

Decreases

• C.

Does not change

• 11.
Bernoulli’s Theorem states that the total amount of energy in a gas flow:
• A.

Remains constant

• B.

Increases

• C.

Decreases

• 12.
Net thrust is:
• A.

Momentum thrust plus pressure thrust

• B.

Gross thrust minus momentum drag

• C.

Gross thrust minus pressure thrust and momentum drag

• 13.
The Brayton cycle is known as the constant
• A.

Pressure cycle.

• B.

Temperature cycle.

• C.

Mass cycle.

• 14.
In a gas turbine engine, combustion occurs at a constant __________.
• A.

Volume.

• B.

Pressure.

• C.

Density.

• 15.
When air intake thermal anti-icing protection is switched ON:
• A.

The engine thrust and EGT are unaffected.

• B.

The engine thrust reduces and the EGT rises.

• C.

The engine thrust increases and the EGT rises.

• 16.
Ram recovery is said to have occurred when the thrust increase it produces:
• A.

Compensates for the thrust lost to momentum drag.

• B.

Reaches the rated sea level thrust value.

• C.

Matches the net thrust.

• 17.
The maximum permissible air velocity entering a gas turbine compressor is:
• A.

Mach 1

• B.

Mach 0.4

• C.

Mach 1.2

• 18.
The vortex dissipators installed on some turbine-powered aircraft to prevent engine FOD utilize
• A.

Variable inlet guide vanes (IGV) and/or variable first stage fan blades.

• B.

Variable geometry inlet ducts.

• C.

A stream of engine bleed air blown toward the ground ahead of the engine.

• 19.
Anti-icing of jet engine air inlets is commonly accomplished by
• A.

Electrical heating elements inside the inlet guide vanes.

• B.

Engine bleed air ducted through the critical areas.

• C.

Electrical heating elements located within the engine air inlet cowling.

• 20.
The purpose of a bellmouth compressor inlet is to
• A.

Provide an increased ram air effect at low airspeeds.

• B.

Maximize the aerodynamic efficiency of the inlet.

• C.

provide an increased pressure drop in the inlet.

• 21.
When an engine with a subsonic divergent type inlet duct is running in place at high speed on the ground, the air pressure within the inlet is
• A.

Positive.

• B.

Negative.

• C.

Ambient.

• 22.
Ram pressure recovery is the slight increase in thrust caused by
• A.

A reduction in air mass flow through the engine at altitude.

• B.

An increase in air temperature due to ram air pressure in the inlet duct.

• C.

An increase in air pressure due to ram recovery by the inlet duct.

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