Jet Turbine Engine Fundamentals Quiz
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Question 1 of 10
1. Question
1. What is the compressor pressure ratio?
Hint
The compressor pressure ratio. This ratio is the outlet pressure divided by the inlet pressure.
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Question 2 of 10
2. Question
2. Which of the following are basic elements of the accessory section?
Hint
The basic elements of the accessory section are:
- The accessory case, which has machined mounting pads for the engine-driven accessories, and
- The gear train, which is housed within the accessory case.
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Question 3 of 10
3. Question
3. What is the approximate compression ratio of a single stage in an axial-flow compressor?
Hint
From inlet to exit, the air flows along an axial path and is compressed at a ratio of approximately 1.25:1 per stage.
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Question 4 of 10
4. Question
4. What is the purpose of the diffuser?
Hint
This prepares the air for entry into the flame burning area of the combustion section at a lower velocity so that the flame of combustion can burn continuously.
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Question 5 of 10
5. Question
5. What is the purpose of having fuel spray in a swirling motion?
Hint
All of the above
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Question 6 of 10
6. Question
6. What type of combustion chamber is typically used on modern engines?
Hint
Modern turbine engines usually have an annular combustion chamber.
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Question 7 of 10
7. Question
7. Which engine part must be constructed to allow for thermal expansion?
Hint
The thermal expansion of turbine nozzles is accomplished by one of several methods.
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Question 8 of 10
8. Question
8. What does “fir-tree design” in reference too?
Hint
There are various ways of attaching turbine blades, some similar to compressor blade attachment. The most satisfactory method utilizes the fir-tree design.
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Question 9 of 10
9. Question
9. A turbine stage consists of __________ followed by __________.
Hint
A turbine stage consists of a row of stationary vanes or nozzles, followed by a row of rotating blades.
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Question 10 of 10
10. Question
10. What type of exhaust nozzle design is used for subsonic gas velocities?
Hint
There are two types of exhaust nozzle designs: the converging design for subsonic gas velocities and the converging- diverging design for supersonic gas velocities.