Design and Verification for Dual⁃mode CDFS and High⁃Load Compressor with a Large Flow Regulation Range  

大流量范围双模式CDFS和高负荷压气机设计研究与验证

作　　者：HUANG Lei ZHANG Jun HAO Yuyang REN Hongkai CHU Wuli 黄磊;张军;郝玉扬;任洪凯;楚武利(西北工业大学动力与能源学院,中国西安710072;中国航发四川燃气涡轮研究院,中国成都610500)

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,P.R.China [2]AECC Sichuan Gas Turbine Establishment,Chengdu 610500,P.R.China

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2024年第5期632-644,共13页南京航空航天大学学报（英文版）

摘　　要：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.介绍了大流量范围双模式核心驱动风扇(Core driven fan stage,CDFS)和高负荷压气机的设计研究与验证。针对其两个模式流量变化范围大、平均级载荷系数高等特点,研究大流量调节范围双模式高效率压缩部件设计技术、平均载荷系数0.504的高负荷压缩部件设计等技术,并在此基础上完成双模式CDFS与四级压气机的设计,开展两种模式的三维流场分析,最终通过试验验证三维数值模拟的结果。试验结果表明:全新的一体化设计技术应用提高了全工况的性能,有效地使CDFS和高压压气机(High⁃pressure compressor,HPC)缩短了长度,减轻了重量,实现了两个部件的完全融合设计,全面研究了单外涵和双外涵模式的级特性匹配机理以及不同调节角度对性能的变化规律,突破了平均载荷系数0.504的高负荷压缩部件设计等关键技术,为下一代发动机的核心压缩部件设计奠定了基础。

关 键 词：fusion design DUAL-MODE high-load compressor large flow regulation range 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]