The below figure is about rotor and stator blades of compressor . How these are connected to the compressor shaft in jet engines ?
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2$\begingroup$ Welcome to Aviation.SE! Could you edit your question to ask only one specific question per post? If you have multiple question you should ask them separately. It would be a good idea if you took our site tour and checked the help center to see how the site works. $\endgroup$– Notts90Aug 17, 2019 at 13:30
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1$\begingroup$ You’re asking about rotor blades. Why not specify the compressor rotor? People may think you’re enquiring after a helicopter rotor. $\endgroup$– KoyovisAug 17, 2019 at 14:56
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$\begingroup$ I would suggest reversing the terms to read "how are compressor blades connected to the rotor?" I think that is more correct, and might clear up some some confusion. $\endgroup$– Michael HallAug 17, 2019 at 18:06
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1 Answer
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There are three primary ways that blades are connected to the shaft
Circumferential dovetails Here is a nice site demonstrating it. Includes STL files so you can 3D print your own demonstration part. https://cults3d.com/en/3d-model/tool/jet-engine-component-1-1-axial-compressor-circumferential-dovetail-slot-type
Axial dovetails Here is a video demonstrating blades with an axial dovetail being assembled. This particular video is a turbine, not a compressor, but in theory the same method can be used.
Blisk "Blisk" is a contraction of "bladed disk". The blades and the disk are physically welded together (or in some cases machined as one piece out of a solid block of metal). Here's a wikipedia article on blisks https://en.wikipedia.org/wiki/Blisk
Each of these methods has advantages and disadvantages in terms of weight, cost, vibration, etc. Which one is picked depends on the circumstances. It is also common to see multiple different methods within one compressor. For example the LEAP-1A HPC has a 10 stage compressor. The forward stages are blisks, and the aft stages are circumferntial dovetails.
