Turbo Concepts Flashcards
Chord
The length of a wing or turbomachine blade along the flow direction
Bypass ratio
The ratio of mass flow in the bypass stream to the mass flow through the engine core.
Gross thrust vs. Net thrust
F_G is the thrust created by the exhaust stream without taking into account the drag created by the inlet flow.
For a stationary engine, F_G = F_net.
Calculate the Net Thrust, F_net.
Um…
Why Rolls-Royce?
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Why are you interested in aerospace?
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What are your career aspirations?
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What is your biggest weakness?
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Tell me about a time when you demonstrated leadership skills.
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Can you describe a time when your project didn’t go according to plan and how you dealt with it?
Shit
This is a picture of an aircraft engine. How does it work?
Which order to explain so it makes the most sense? Fan, compressor, combustion chamber, turbine.
Why do we want a high bypass ratio? How high is it currently? Why can’t we make it higher?
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How does a compressor stage work? Why are there so many compressor stages compared to turbine stages? What’s the typical pressure ratio for each?
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Why do we want multiple spools in a jet engine instead of a single shaft? Why 3 spools instead of 2? If we are saving weight with 3 spools, how are we achieving this?
Less stages because they are more efficient??
Off design and part speed performance?
Typically, how fast is the flow through a compressor stage? Does it vary a lot? What about into the combustion chamber? What’s the diffuser design like?
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