I have a personal project to design a gas turbine engine, the main problem that nags me is how do I determine the pressure rise in each stage of an axial compressor? Say, I'm planning on a 38:1 engine so how do I determine how many stages I might need and how much will be the pressure rise?

If anyone is interested in joining the project feel free to email me, can always use an extra brain!

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    $\begingroup$ Are we super sure this is not class work? Sounds like class work. How did you select 38:1? What is the application? $\endgroup$ – acpilot Jun 24 at 17:42
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    $\begingroup$ Just multiply the compression ratio of each stage. It's not so hard – the hard part is achieving those compression ratios at each stage. $\endgroup$ – Peter Kämpf Jun 24 at 18:11
  • $\begingroup$ @PeterKämpf I think the OP has a total compression ratio and is looking to divide it by the number of compressor in the engine to determine pressure rise/compressor. As a matter of fact, that may just be the answer he's looking for... $\endgroup$ – FreeMan Jun 24 at 18:35
  • $\begingroup$ @FreeMan: I know, and all he needs now is a realistic stage compression ratio. But he should now do a bit research himself. $\endgroup$ – Peter Kämpf Jun 24 at 18:52
  • $\begingroup$ @acpilot: Couldn't agree more. With 38:1 the T4 will be too high for some amateur engine. You need mono crystalline blades with film cooling – impossible to do in a personal project. $\endgroup$ – Peter Kämpf Jun 24 at 18:55

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