大攻角状态压气机分离流及叶片动力响应特性

doi:10.13700/j.bh.1001-5965.2016.0912

北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (7): 1410-1418.doi: 10.13700/j.bh.1001-5965.2016.0912

大攻角状态压气机分离流及叶片动力响应特性

倪奇峰¹, 侯安平^1,2, 刘若阳¹, 周拜豪³, 张明明⁴

1. 北京航空航天大学能源与动力工程学院, 航空发动机气动热力国家级重点实验室, 北京 100083;
2. 先进航空发动机协同创新中心, 北京 100083;
3. 中国燃气涡轮研究院, 成都 610500;
4. 北京工业大学机械工程与应用电子技术学院, 北京 100074

收稿日期:2016-12-02 修回日期:2017-01-13 出版日期:2017-07-20 发布日期:2017-04-07
通讯作者: 侯安平,E-mail:houap@buaa.edu.cn E-mail:houap@buaa.edu.cn
作者简介:倪奇峰男,博士研究生。主要研究方向:叶轮机气动设计、非定常流动及气动弹性;侯安平男,博士,副教授,博士生导师。主要研究方向:叶轮机气动设计、空气轴承及高速电机设计、非定常流动及气动弹性。
基金资助:
国家自然科学基金（11290140）

Separation flow and blade dynamic response characteristic of compressor at high attack angle

NI Qifeng¹, HOU Anping^1,2, LIU Ruoyang¹, ZHOU Baihao³, ZHANG Mingming⁴

1. National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. Collaborative Innovation Center for Advanced Aero-engine, Beijing 100083;
3. China Gas Turbine Establishment, Chengdu 610500, China;
4. College of Mechanical Engineering and Applied Electronics Technology, Beijing University of Technology, Beijing 100074, China

Received:2016-12-02 Revised:2017-01-13 Online:2017-07-20 Published:2017-04-07
Supported by:
National Natural Science Foundation of China (11290140)

摘要/Abstract

摘要： 为研究大攻角状态压气机转子内部分离区的脱落和传播过程及转子叶片对其动力响应问题，对某跨声速压气机级进行了非定常数值模拟和双向迭代流固耦合数值模拟。研究结果表明，在近失速状态，转子叶片通道内会周期性地发生2次叶背分离区的脱落和传播现象。第1个分离区主要表现出轴向传播特性，其会对下游流场产生影响；第2个分离区主要表现出周向传播特性，其会作用于周向相邻的转子叶片，对转子叶排自身产生激励作用，进而影响叶片表面压力分布，引起叶片较强的动力响应，对叶片结构强度的影响不可忽略。非定常/流固耦合计算手段能够较全面地预测流场中激励源的频率、幅值与位置等，在压气机设计阶段应对此类预测工作予以重视，以期更准确地预测叶片共振及动力响应等问题。

关键词: 分离区脱落和传播, 非定常/流固耦合, 数值模拟, 叶片振动, 动力响应

Abstract: In order to study the shedding and propagation of compressor rotors at high angle of attack, as well as the dynamic response under this transient process, a model with a stage of transonic compressor was simulated with unsteady numerical method and double direction iteration fluid-structure coupled numerical method. The results show that under near-stall condition, the separation regions at suction side move and shed periodically along axial and circumferential directions. The axial separation may influence the flow field and vibration performance of downstream blade rows, while the circumferential separation can impact the adjacent rotor blade, with an excitation brought on rotor row itself and an influence on the pressure distribution of rotor blades. Furthermore, the circumferential separation may cause violent dynamic response which could threaten the structural strength of rotor blades. Unsteady/FSI simulation technology has the ability to forecast frequencies, amplitudes and locations of the excitation sources in flow field. This kind of work should be emphasized during design procedure to assess the resonance and dynamic response of compressor blades.

Key words: separation shedding and propagation, unsteady/FSI, numerical simulation, blade vibration, dynamic response

中图分类号:

V231.3

倪奇峰, 侯安平, 刘若阳, 周拜豪, 张明明. 大攻角状态压气机分离流及叶片动力响应特性[J]. 北京航空航天大学学报, 2017, 43(7): 1410-1418.

NI Qifeng, HOU Anping, LIU Ruoyang, ZHOU Baihao, ZHANG Mingming. Separation flow and blade dynamic response characteristic of compressor at high attack angle[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2017, 43(7): 1410-1418.

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大攻角状态压气机分离流及叶片动力响应特性

Separation flow and blade dynamic response characteristic of compressor at high attack angle

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