高负荷风扇静叶气动特性的实验与数值研究

推进技术 ›› 2015, Vol. 36 ›› Issue (9): 1331-1338.

高负荷风扇静叶气动特性的实验与数值研究

陶立权¹,孙鹏²,杨坤¹,潘若痴³

中国民航大学天津市民用航空器适航与维修重点实验室，天津 300300,大连海事大学轮机工程学院，辽宁大连 116026,中国民航大学天津市民用航空器适航与维修重点实验室，天津 300300,中国航空工业集团公司沈阳发动机设计研究所，辽宁沈阳 110015

发布日期:2021-08-15
作者简介:陶立权(1978—)，男，硕士，助理研究员，研究领域为发动机性能方面研究。E-mail: cauctao@sina.com 通讯作者:孙鹏(1979—)，男，教授，研究领域为发动机气动热力学方面研究。
基金资助:
国家自然科学基金项目(51576024)，国家自然科学基金重点项目(51436002)。

Experimental and Numerical Investigation on Aerodynamic Performance of a Highly Loaded Fan Stator

Civil Aviation University of China，Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance，Tianjin 300300，China,Marine Engineering College，Dalian Maritime University，Dalian 116026，China,Civil Aviation University of China，Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance，Tianjin 300300，China and Shenyang Aircraft engine design institute，China Aviation Industry Corporation，Shenyang 110015，China

Published:2021-08-15

摘要/Abstract

摘要： 为了掌握高负荷静叶内部流动特征，进而指导静叶改型设计，采用实验和数值模拟相结合的方法，对高负荷风扇末级静子叶栅的气动性能开展研究。为了在级环境下研究静子叶栅的气动性能，在静子叶栅前设计了导叶，提供级中静子叶栅的进口气流参数，分析了不同进口马赫数条件下的静叶气动性能。研究表明:导流叶片可以保证静叶进口气流方向和速度与级内相近，可以用扇形叶栅吹风实验模拟级环境对静叶气动性能开展研究；静叶吸力面存在较大的分离和回流，27%叶高附近分离最大，使该处气流折转最小约42°；静叶3%叶高压力面存在较大的负攻角损失；随着进口马赫数增加，出口气流参数沿径向波动程度明显增加。

关键词: 静叶；扇形叶栅；实验；数值模拟；气动性能

Abstract: In order to understand the flow characteristics in highly loaded stator and guide the stator retrofit design，experimental and numerical methods were adopted for aerodynamic performance analysis of a final stage stator cascade of a highly loaded fan. In order to conduct the sectorial cascade experiment without the existence of moving blades，the adjustable guide vanes (AGV) were designed to simulate the inlet flow velocity and direction of the stator. Aerodynamic performances of the stator cascade under different inlet Mach numbers were analyzed. Results show that the AGV can ensure the stator inlet velocity angle and Mach number are similar to those in stage. Therefore sector cascade experiment can be used to simulate the stage environment to study the stator aerodynamic performance. There is large scale separation on the stator suction surface. The largest scale separation exists at 27% span，which causes the minimum flow turning angle 42° here. The loss of negative attack angle exists at 3% span on the pressure surface. With the increase of inlet Mach number，the fluctuation range of outlet parameters increase significantly along radial direction.

Key words: Stator；Sector cascade；Experiment；Numerical simulation；Aerodynamic performance

陶立权,孙鹏,杨坤,潘若痴. 高负荷风扇静叶气动特性的实验与数值研究[J]. 推进技术, 2015, 36(9): 1331-1338.

TAO Li-quan¹,SUN Peng²,YANG Kun¹,PAN Ruo-chi³. Experimental and Numerical Investigation on Aerodynamic Performance of a Highly Loaded Fan Stator[J]. Journal of Propulsion Technology, 2015, 36(9): 1331-1338.

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