This paper presents the design of a centrifugal compressor for high-speed turbomachinery.The main focus of the research is to develop a centrifugal compressor with improved aerodynamic performance.As a meridional fram...This paper presents the design of a centrifugal compressor for high-speed turbomachinery.The main focus of the research is to develop a centrifugal compressor with improved aerodynamic performance.As a meridional frame has a significant effect on overall performance of the compressor,special attention has been paid to the end wall contours.The shroud profile is design with bezier curve and hub profile with circular arc contour.The blade angle distribution has been arranged in a manner that it merges with single value at impeller exit.The rake angle is positive at leading edge and negative at trailing edge with identical magnitude.Furthermore,three-dimensional straight line element approach has been used for this design for better manufacturability.The verification of the aerodynamic performance has been carried out using CFD software with consideration of a single blade passage and vaneless diffuser.The result has been compared with matching size aftermarket compressor stage gas stand data.The 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 RPM.In addition,new surge margin improvement technique has been proposed by means of diffuser enhancement.This technique provides an average of 16%improvement in surge margin compared to standard diffuser stage with 55 trim compressor impeller.The mechanical integrity has been validated at maximum RPM with the aluminum alloy 2014-T6 as a fabrication material.展开更多
基金European Horizon 2020 grant 644971 and Innovate UK grant 104021.
文摘This paper presents the design of a centrifugal compressor for high-speed turbomachinery.The main focus of the research is to develop a centrifugal compressor with improved aerodynamic performance.As a meridional frame has a significant effect on overall performance of the compressor,special attention has been paid to the end wall contours.The shroud profile is design with bezier curve and hub profile with circular arc contour.The blade angle distribution has been arranged in a manner that it merges with single value at impeller exit.The rake angle is positive at leading edge and negative at trailing edge with identical magnitude.Furthermore,three-dimensional straight line element approach has been used for this design for better manufacturability.The verification of the aerodynamic performance has been carried out using CFD software with consideration of a single blade passage and vaneless diffuser.The result has been compared with matching size aftermarket compressor stage gas stand data.The 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 RPM.In addition,new surge margin improvement technique has been proposed by means of diffuser enhancement.This technique provides an average of 16%improvement in surge margin compared to standard diffuser stage with 55 trim compressor impeller.The mechanical integrity has been validated at maximum RPM with the aluminum alloy 2014-T6 as a fabrication material.
