Abstract
Abstract
A design method for axial compressor stages is presented which is indicated to reduce the tendency for efficiency to diminish as the design work coefficient increases. Three worked examples with different levels of design work coefficient are used to demonstrate the potential advantages of the procedure. If experimentally confirmed, the results would be of value in situations where the blade speed is restricted, as in the case of core compressor stages attached to the fan shaft of turbofan aero engines. Another potential field of application is the compression of such gases as helium and hydrogen, where the speed of sound is high and mechanical limitations to the blade speed restrict the Mach numbers and therefore the stage pressure ratio achievable with conventional levels of work coefficient.
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