低速轴流压气机周向单槽机匣处理扩稳实验研究

doi:10.7527/S1000-6893.2014.0131

流体力学与飞行力学

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低速轴流压气机周向单槽机匣处理扩稳实验研究

李继超¹, 刘乐^1,2, 杜娟¹, 王偲臣¹, 林峰¹

1. 中国科学院工程热物理研究所先进能源动力重点实验室, 北京 100190;
2. 中国科学院大学, 北京 100190

收稿日期:2014-04-22 修回日期:2014-06-25 出版日期:2015-05-15 发布日期:2014-07-04
通讯作者: 杜娟Tel.: 010-82543094 E-mail: dujuan@iet.cn E-mail:dujuan@iet.cn
作者简介:李继超男, 博士, 助理研究员。主要研究方向: 轴流压气机失稳、扩稳机理及系统建模与控制。 Tel: 010-82543072 E-mail: lijichao@iet.cn;刘乐男, 博士研究生。主要研究方向: 轴流压气机内部周向单槽扩稳机理及实验测量。 Tel: 010-82543084 E-mail: liule@iet.cn;杜娟女, 博士, 副研究员。主要研究方向: 轴流压气机内部流动失稳、扩稳机理。 Tel: 010-82543094 E-mail: dujuan@iet.cn
基金资助:
国家自然科学基金 (51306178, 51106153)

Experimental investigation of stability enhancement with single circumferential groove casing treatment on a low speed axial compressor

LI Jichao¹, LIU Le^1,2, DU Juan¹, WANG Sichen¹, LIN Feng¹

1. Key Laboratory of Advanced Energy and Power, Institute of Engineering Thermophysics, Chineses Academy of Sciences, Beijing 100190, China;
2. University of Chineses Academy of Sciences, Beijing 100190, China

Received:2014-04-22 Revised:2014-06-25 Online:2015-05-15 Published:2014-07-04
Supported by:
National Natural Science Foundation of China (51306178, 51106153)

摘要/Abstract

摘要：

周向槽机匣处理作为一种有效的扩稳措施得到了广泛应用,但是缺乏对其机理的深入理解和认识。为此,在一台低速单转子轴流压气机上考察了周向单槽机匣处理随轴向位置变化的扩稳效果。实验中获得了单槽不同轴向位置的扩稳规律,在该台压气机上得出了扩稳效果最好的槽位于40%~60%轴向弦长,而当单槽位于27%轴向弦长附近时,其扩稳效果最差。在此基础上,选取了最优扩稳槽位和最差扩稳槽位进行详细的壁面非定常流场测量和尾迹测量,对比分析了光壁条件与各单槽处理机匣对叶顶间隙泄漏流和转子尾迹的影响。结果表明,采用扩稳效果最优槽位之后,周向单槽能推迟叶顶间隙泄漏流与主流交界面前移,以及减弱叶顶间隙泄漏流非定常性,且能明显增强尾迹区1BPF(叶片通过频率)的能量,同时减弱0.5BPF的能量,达到扩稳的目的。而对于扩稳效果最差槽位而言,叶顶间隙泄漏流与主流交界面直到失速前也无法跨过单槽从叶片前缘溢出,周向单槽改变了叶顶间隙内部诱发突尖失速先兆的扰动传播方式;另外,其对转子尾迹区0.5BPF和1BPF的影响也比较小,从而使得其扩稳效果减弱。

关键词: 压气机, 周向单槽, 机匣处理, 尾迹, 失速裕度改善

Abstract:

Circumferential casing grooves are known to increase the stable operating range of axial compressors; however, the mechanism by which the stability enhancement occurs is poorly understood. In this paper, experimental investigations are performed on a low speed axial compressor to study the stability enhancement effect of single circumferential casing groove with different axial locations. The complete change rule of stability enmancement improvement is obtained when the groove moves from the leading edge towards trailing edge. It is found that the optimum grooves locate at the location of 40% to 60% of axial chord of the blade tip, and the worst grooves locate near the location of 27% of axial chord of the blade tip. On this basis, dynamic measurements are performed on the casing and at the rotor wake to analyze the effect on the tip leakage flow and rotor wake with different groove locations compared with smooth casing. These results reveal that the optimum groove can delay the forward movement of the interface and it can also enhance the power of frequency band of blade passing frequency (BPF) and weaken the power of 0.5BPF. But for the worst groove, the interface cannot cross the groove to spill out at the leading edge, even until the stall; it will affect the circumferential propagation of the disturbance which induced the stall inception. Its effect on the power of 1BPF and 0.5BPF at the rotor wake is very slightly.

Key words: compressor, single circumferential groove, casing treatment, wake, stall margin improvement

中图分类号:

V231.3

李继超, 刘乐, 杜娟, 王偲臣, 林峰. 低速轴流压气机周向单槽机匣处理扩稳实验研究[J]. 航空学报, 2015, 36(5): 1422-1431.

LI Jichao, LIU Le, DU Juan, WANG Sichen, LIN Feng. Experimental investigation of stability enhancement with single circumferential groove casing treatment on a low speed axial compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(5): 1422-1431.

参考文献

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

低速轴流压气机周向单槽机匣处理扩稳实验研究

Experimental investigation of stability enhancement with single circumferential groove casing treatment on a low speed axial compressor

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