基于主/被动联合控制技术设计的高负荷扩压叶栅内部流场结构研究

推进技术 ›› 2015, Vol. 36 ›› Issue (11): 1662-1668.

基于主/被动联合控制技术设计的高负荷扩压叶栅内部流场结构研究

张龙新¹,杜鑫¹,刘勋²,陈绍文¹,王松涛¹

哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨船舶锅炉涡轮机研究所，黑龙江哈尔滨 150078,哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨 150001,哈尔滨工业大学发动机气体动力研究中心，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:张龙新(1987—)，男，博士生，研究领域为高负荷压气机设计。
基金资助:
国家自然科学基金项目(51206035)；国家自然科学基金创新研究群体项目(51121004)。

Study on Flow Structure of a Highly-Loaded Compressor Cascade Designed with Active and Passive Flow Control Methods

Engine Aerodynamics Research Centre，Harbin Institute of Technology，Harbin 150001,Engine Aerodynamics Research Centre，Harbin Institute of Technology，Harbin 150001,Harbin Boiler & Turbine Institute，Harbin 150078,Engine Aerodynamics Research Centre，Harbin Institute of Technology，Harbin 150001 and Engine Aerodynamics Research Centre，Harbin Institute of Technology，Harbin 150001

Published:2021-08-15

摘要/Abstract

摘要： 为进一步优化设计工作做准备，以基于主/被动联合控制技术设计的高负荷扩压叶栅作为研究对象，在进口为高亚声速的条件下，利用数值模拟的方法，详细研究了冲角变化对扩压叶栅壁面流谱以及气动损失的影响。结果表明，负冲角下，后列叶栅内部存在较大尺度的角区分离流动，构成叶栅损失的主要来源；随着冲角增加，流经串列叶栅近端壁处缝隙流道内流体的相对动量增强，后列叶栅角区分离流动受到抑制，端区二次流动损失降低，+3°冲角下，上、下20%叶展区域内总压损失分别降低了4.4%、6.8%，但前列叶栅叶型分离流动加剧，主流区损失增加；合理协调端壁附面层抽吸技术与串列叶栅技术的应用是提升高负荷扩压叶栅全工况气动性能的关键。

关键词: 高负荷压气机；附面层抽吸；串列叶栅；冲角

Abstract: In order to prepare for the further optimization，numerical simulation is carried out on a highly-loaded compressor cascade designed with active and passive flow control methods at the high subsonic inlet condition，and detail research was performed on the effects of various incidences on the flow pattern and aerodynamic loss of the cascade. As a result，at the negative incidence，a large corner separation exists in the rear blade，which consists of the main source of the loss. With the increased incidence，the jet flow momentum in the flow channel of the tandem near the endwall is enhanced，which suppresses the corner separation and decreases the endwall secondary flow loss，the total pressure loss is reduced by 4.4% and 6.8% in the upper and lower 20% span at +3° incidence，however，blade separation is aggravated on the forward blade and flow loss in the main flow is increased. The key to further improve the full operation aerodynamic performance of the highly-loaded compressor cascade is to utilize tandem cascade and boundary layer suction reasonably.

Key words: Highly-loaded compressor；Boundary layer suction；Tandem cascade；Incidence

张龙新,杜鑫,刘勋,陈绍文,王松涛. 基于主/被动联合控制技术设计的高负荷扩压叶栅内部流场结构研究[J]. 推进技术, 2015, 36(11): 1662-1668.

ZHANG Long-xin¹,DU Xin¹,LIU Xun²,CHEN Shao-wen¹,WANG Song-tao¹. Study on Flow Structure of a Highly-Loaded Compressor Cascade Designed with Active and Passive Flow Control Methods[J]. Journal of Propulsion Technology, 2015, 36(11): 1662-1668.

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