Abstract
The computer package developed for the preliminary design of multistage axial compressor described in part (I) is applied here for the design of compressor of a typical aeroengine.This compressor is in close proximity to compressor in the CF6-60 turbofan engine. For the same design conditions, the calculated compressor has the same number of stages and layout as that of the CF6 engine. Detailed results concerning both aerodynamic and mechanical designs are presented here.
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Schedule a callMore From: International Conference on Aerospace Sciences and Aviation Technology
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