南京航空航天大学学报（英文版）2024，Vol.41Issue(5)：632-644,13.DOI:10.16356/j.1005-1120.2024.05.008
大流量范围双模式CDFS和高负荷压气机设计研究与验证
Design and Verification for Dual-mode CDFS and High-Load Compressor with a Large Flow Regulation Range
摘要
Abstract
This paper presents the design and verification of the dual-mode core driven fan stage(CDFS)and high-load compressor with a large flow regulation range.In view of the characteristics of large flow regulation range of the two modes and high average stage load coefficient,this paper investigates the design technology of the dual-mode high-efficiency compressor with a large flow regulation range and high-load compressor with an average stage load coefficient of 0.504.Building upon this research,the design of the dual-mode CDFS and four-stage compressor is completed,and three-dimensional numerical simulation of the two modes is carried out.Finally,performance experiment is conducted to verify the result of three-dimensional numerical simulation.The experiment results show that the compressor performance is improved for the whole working conditions by using the new design method,which realizes the complete fusion design of the CDFS and high-pressure compressor(HPC).The matching mechanism of stage characteristics of single and double bypass modes and the variation rule of different adjustment angles on performance are studied comprehensively.Furthermore,it effectively reduces the length and weight of compressor,and breaks through the key technologies such as high-load compressor with the average load factor of 0.504.These findings provide valuable data and a methodological foundation for the development of the next generation aeroengine.关键词
融合设计/双模式/高负荷压气机/大流量范围Key words
fusion design/dual-mode/high-load compressor/large flow regulation range分类
航空航天引用本文复制引用
黄磊,张军,郝玉扬,任洪凯,楚武利..大流量范围双模式CDFS和高负荷压气机设计研究与验证[J].南京航空航天大学学报（英文版）,2024,41(5):632-644,13.基金项目
This work was supported by the Na-tional Major Project. （）
