A computer code is developed for rapid design ofudprofiles suitable for transonic, highly loaded axialudflow compressors . Analysis of the profiles derived fromudthe procedure using viscous flow codes suggest that theudblades sections should yield efficient performance, characteristic of controlled diffusion aerofoils being introduced in modern gas turbines. Design for stators usingudthe method for validations studies in NAL experimentaludcompressor facility and for a contemporary design areudsuggested.
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