Gte Tutorial 2 MCQ
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.
Related Topics
Recent Quizzes
Featured Quizzes
Back to top