对转压气机轮缘端壁抽吸流场特性数值分析及实验研究

doi:10.7527/S1000-6893.2014.0340

流体力学与飞行力学

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对转压气机轮缘端壁抽吸流场特性数值分析及实验研究

史磊, 刘波, 巫骁雄, 那振喆, 张鹏

西北工业大学动力与能源学院, 西安 710072

收稿日期:2014-09-29 修回日期:2014-12-09 出版日期:2015-09-15 发布日期:2015-01-27
通讯作者: 刘波男, 博士, 教授, 博士生导师。主要研究方向: 轴流叶轮机械气动设计及其热力学。 Tel: 029-88488029 E-mail: liubo704@nwpu.edu.cn E-mail:liubo704@nwpu.edu.cn
作者简介:史磊男, 博士研究生。主要研究方向: 轴流叶轮机械流动控制技术。 Tel: 029-88488029 E-mail: star704nwpu@gmail.com;巫骁雄男, 硕士研究生。主要研究方向: 轴流叶轮机械气动热力学。 Tel: 029-88488029 E-mail: xxwu1990@126.com;那振喆男, 博士研究生。主要研究方向: 轴流叶轮机械气动热力学。 Tel: 029-88488029 E-mail: na_wuli@163.com;张鹏男, 博士研究生。主要研究方向: 轴流叶轮机械气动热力学。 Tel: 029-88488029 E-mail: zhengpeng257@163.com
基金资助:
国家自然科学基金 (51236006)

Numerical analysis and experimental research of shroud casing boundary layer removal on a counter-rotating compressor

SHI Lei, LIU Bo, WU Xiaoxiong, NA Zhenzhe, ZHANG Peng

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

Received:2014-09-29 Revised:2014-12-09 Online:2015-09-15 Published:2015-01-27
Supported by:
National Natural Science Foundation of China (51236006)

摘要/Abstract

摘要：

以某双排对转轴流压气机为研究对象,通过区域缩放法开展非定常数值研究。数值结果显示近喘点附近转子2(R2)叶尖泄漏流动造成了高叶展范围内的流动阻塞以及高熵流动区域的产生,下游出口导流叶片承受着非常不利的来流条件。通过在转子叶尖近高熵流动核心区轮缘端壁处设置抽吸孔进行低能流体的移除能够明显改善叶尖区域的流场品质,提高压气机工作特性。根据数值研究结果,重新设计并加工了用于端壁抽吸的轮缘机匣,搭建了附面层抽吸系统及测控系统。在80%设计转速下,针对转子2叶尖进行端壁附面层抽吸,相对抽吸流量为1.0%。实验结果显示,端壁附面层抽吸应工作在低于原始特性最高效率点所在流量的小流量范围内。在此流量范围内端壁抽吸会大幅提高工作效率,改善压气机负荷水平。而在高于此流量的范围内,端壁附面层抽吸会带来负面影响。

关键词: 对转压气机, 非定常计算, 区域缩放法, 端壁附面层抽吸, 工作特性

Abstract:

Domain scaling method is used in the unsteady numerical simulation of a dual-stage axial counter-rotating compressor. Numerical results show that tip leakage vortex over Rotor 2(R2) is the main source of flow blockage in high spanwise and high entropy zone in the tip region, which makes outlet guide vanes in the downstream endure a serious flow condition. Shroud casing boundary layer removal in the high entropy core over rotor tip can make the flow field better and improve the characteristic of compressor. Based on the results of numerical calculation, we redesign and machine the aspirated shroud casing, meanwhile set up boundary layer suction and control system. Experiment is carried out at 1.0% suction rate through R2 tip region shroud casing at 80% corrected rotating speed. Results indicate that boundary layer suction through shroud casing should be used under the massflow with the highest efficiency in original characteristic. Boundary layer suction can better the efficiency and improve the loading level in this flow area. Else it has a negative influence.

Key words: counter-rotating compressor, unsteady calculation, domain scaling method, shroud casing boundary layer removal, operating performance

中图分类号:

V231.3

史磊, 刘波, 巫骁雄, 那振喆, 张鹏. 对转压气机轮缘端壁抽吸流场特性数值分析及实验研究[J]. 航空学报, 2015, 36(9): 2968-2980.

SHI Lei, LIU Bo, WU Xiaoxiong, NA Zhenzhe, ZHANG Peng. Numerical analysis and experimental research of shroud casing boundary layer removal on a counter-rotating compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2968-2980.

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对转压气机轮缘端壁抽吸流场特性数值分析及实验研究

Numerical analysis and experimental research of shroud casing boundary layer removal on a counter-rotating compressor

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