I am a student an I am new to this forum but I am very interested in turbomachinery. This thread has more to do with the aerospace side of things but the same principles apply. With lubrication and other complexities aside, would a fully independent 5 stage axial compressor (by independent I mean each compressor disc has its own corresponding power source Eg. turbine) designed to drive each stage at an optimal frequency. The reason I ask this is because the Rolls royce Trent 1000 aircraft engine has 2 compression spools, a IP (intermediate pressure) and HP (high pressure) spool for IP and HP compressors respectively. The IP compressor has 8 stages and the HP compressor has 6 stages and they are contra-rotating which improves efficiency. So if you could have each stage completely independent from all the others and each stage contra-rotating compressor stages, would you even need stator vanes and would there be an efficiency increase over a single spool compressor with the same number of stages all variables held constant?
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