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Design of a high-performance centrifugal compressor with new surge margin improvement technique for high speed turbomachinery

引用

Propulsion and Power Research 2018年第1期7卷 19-29页

作者： Sagar Pakle Kyle Jiang School of Engineering University of BirminghamEdgbastonBirmingham B152TTUnited Kingdom

This paper presents the design of a centrifugal compressor for high-speed *** main focus of the research is to develop a centrifugal compressor with improved aerodynamic *** a meridional frame has a significant effect on overall performance of the compressor,special attention has been paid to the end wall *** shroud profile is design with bezier curve and hub profile with circular arc *** blade angle distribution has been arranged in a manner that it merges with single value at impeller *** rake angle is positive at leading edge and negative at trailing edge with identical ***,three-dimensional straight line element approach has been used for this design for better *** verification of the aerodynamic performance has been carried out using CFD software with consideration of a single blade passage and vaneless *** result has been compared with matching size aftermarket compressor stage gas stand *** compressor stage with Trim 55 provides 34%increase in choke flow at 210000 RPM as compared to gas stand data with 87%peak stage efficiency at 110000 *** addition,new surge margin improvement technique has been proposed by means of diffuser *** technique provides an average of 16%improvement in surge margin compared to standard diffuser stage with 55 trim compressor *** mechanical integrity has been validated at maximum RPM with the aluminum alloy 2014-T6 as a fabrication material.

关键词： Centrifugal compressor Aerodynamic performance Surge margin blade angles Stress analysis Computational fluid dynamics

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