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Gas Turbine Engine Exam Questions and Answers 100% Solved | Graded A+
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Gas Turbine Engine Exam Questions and Answers 100% Solved | Graded A+ On an axial flow, dual compressor forward fan engine, the fan turns the same speed as the. Option A. low pressure turbine. Option B. high pressure compressor. Option C. forward turbine wheel. - c Which statements are true ...

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  • December 8, 2024
  • 86
  • 2024/2025
  • Exam (elaborations)
  • Questions & answers

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  • Gas Turbine
  • Gas Turbine

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Gas Turbine Engine Exam Questions

and Answers 100% Solved | Graded A+


On an axial flow, dual compressor forward fan engine, the fan turns the

same speed as the.

Option A. low pressure turbine.

Option B. high pressure compressor.

Option C. forward turbine wheel. - ✔✔c

Which statements are true regarding aircraft engine propulsion?.

Option A. Turbojet and turbofan engines impart a relatively large amount of

acceleration to a smaller mass of air.

Option B. In modern turboprop engines, nearly 50 percent of the exhaust

gas energy is extracted by turbines to drive the propeller and compressor

with the rest providing exhaust thrust.

Option C. An engine driven propeller imparts a relatively small amount of

acceleration to a large mass of air. - ✔✔c

As subsonic air flows through a convergent nozzle the velocity.

Option A. decreases.


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©JOSHCLAY 2024/2025. YEAR PUBLISHED 2024.

,Option B. increases.

Option C. remains constant. - ✔✔b

In a twin spool compressor system, the first stage turbine drives the.

Option A. N2 compressor.

Option B. N1 and N2 compressors.

Option C. N1 compressor. - ✔✔a

At what point in an axial flow turbojet engine will the highest gas pressures

occur?.

Option A. At the compressor outlet.

Option B. At the turbine entrance.

Option C. Within the burner section. - ✔✔a

The diffuser section is located between.

Option A. the burner section and the turbine section.

Option B. station No. 7 and station No. 8.

Option C. the compressor section and the burner section - ✔✔c

The term Pt7 means.

Option A. pressure and temperature at station No. 7.

Option B. the total pressure at station No. 7.

Option C. the total inlet pressure. - ✔✔b


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,What section provides proper mixing of the fuel and efficient burning of the

gases?.

Option A. Diffuser section and combustion section.

Option B. Combustion section and compressor section.

Option C. Combustion section only. - ✔✔c

The pressure of supersonic air as it flows through a divergent nozzle.

Option A. decreases.

Option B. increases.

Option C. is inversely proportional to the temperature. - ✔✔a

When a volume of air is compressed.

Option A. heat is gained.

Option B. no heat is lost or gained.

Option C. heat is lost. - ✔✔b

The pressure of subsonic air as it flows through a convergent nozzle.

Option A. increases.

Option B. remains constant.

Option C. decreases. - ✔✔c

A divergent duct will cause subsonic flow to decrease in.

Option A. velocity, increase pressure.


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©JOSHCLAY 2024/2025. YEAR PUBLISHED 2024.

, Option B. velocity, pressure remains constant.

Option C. pressure, increase velocity. - ✔✔a

The purpose of a diffuser is to.

Option A. increase the kinetic energy of the air.

Option B. induce a swirl to the air prior to combustion.

Option C. increase the static pressure of the air. - ✔✔c

On a triple spool engine, the first stage of turbines drive.

Option A. the LP compressor.

Option B. the HP compressor.

Option C. the I P compressor. - ✔✔b

Ram effect' due to aircraft forward speed will cause the efficiency of the

engine to.

Option A. remain constant.

Option B. decrease.

Option C. increase. - ✔✔c

The efficiency of a gas turbine engine at altitude.

Option A. decreases.

Option B. remains constant.

Option C. increases. - ✔✔c


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©JOSHCLAY 2024/2025. YEAR PUBLISHED 2024.

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