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

作     者：Sagar Pakle Kyle Jiang 

作者机构：School of EngineeringUniversity of BirminghamEdgbastonBirmingham B152TTUnited Kingdom 

基　　金：European Horizon 2020 grant 644971 and Innovate UK grant 104021 

出 版 物：《Propulsion and Power Research》 (推进与动力（英文）)

年 卷 期：2018年第7卷第1期

页      码：19-29页

摘      要：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.

主 题 词：Centrifugal compressor Aerodynamic performance Surge margin Blade angles Stress analysis Computational fluid dynamics 

学科分类：080704[080704] 08[工学] 0807[工学-电子信息类] 

核心收录：

D　O　I：10.1016/j.jppr.2018.02.004

馆 藏 号：203284150...