轴流压气机大小叶片气动弹性稳定性分析

黄钟山; 王延荣; 付志忠

doi:10.13224/j.cnki.jasp.2016.08.023

轴流压气机大小叶片气动弹性稳定性分析

doi: 10.13224/j.cnki.jasp.2016.08.023

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金（51475022）

详细信息

作者简介:
黄钟山(1990-),男,江西瑞昌人,硕士生,主要从事航空发动机结构强度振动及气动弹性稳定性的研究.

中图分类号: V215.3
计量
- 文章访问数: 845
- HTML浏览量: 4
- PDF量: 572
- 被引次数: 0
出版历程
- 收稿日期: 2014-11-13
- 刊出日期: 2016-08-28

Aero-elastic stability analysis of an axial compressor with splitter rotor

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 分别采用能量法和时域法对轴流压气机大小叶片进行了气动弹性稳定性分析，获得了叶片的气动模态阻尼比和叶片表面的非定常气动功分布.对叶片的振动位移响应进行了频域分析，并与常规设计转子作了对比.结果表明：大小叶片存在的结构失谐和气动失谐对气动弹性稳定性有明显的影响.气动失谐改善了叶片表面的非定常气动功分布，结构失谐改变了叶间相位角的影响.大小叶片对应的1阶模态振型的气动模态阻尼比为0.000791，而常规设计转子的值为0.000217，大小叶片相对于常规设计转子，不仅改善了气动性能，同时还提高了气动弹性稳定性.
- 轴流压气机 /
- 大小叶片 /
- 失谐 /
- 气动弹性 /
- 颤振
Abstract: The aero-elasticity of an axial compressor with splitter rotor was investigated by employing energy method and time-domain method. The aerodynamic modal damping ratio of blade and unsteady aerodynamic work distribution on the blade surface were obtained while the frequency domain analysis of blade vibration displacement were made; the conventionally designed rotors and the splitter rotor were also compared. The results show that the structural mistuning and aerodynamic mistuning had significant positive effects on the aero-elastic stability of the system. Aerodynamic mistuning improved the unsteady aerodynamic work distribution on the blade surface and the structural mistuning weakened the effect of interblade phase angles. For the first vibration mode, aerodynamic modal damping ratio (AMDR) of the splitter rotor has the value of 0.000791, and that of conventionally designed rotors have the value of 0.000217.Therefore,the structure of the splitter rotor not only has a better aerodynamic performance, but also enhanced the aero-elastic stability.
- axial compressor /
- splitter rotor /
- mistuning /
- aero-elasticity /
- flutter

HTML

参考文献(18)

[1]	陈懋章.风扇/压气机技术发展和对今后工作的建议[J].航空动力学报,2002,17(1):1-15. CHEN Maozhang.Development of fan/compressor techniques and suggestions on further researches[J].Journal of Aerospace Power,2002,17(1):1-15.(in Chinese)
[2]	Wennerstrom A J,Forst G R.Design of a rotor incorporating splitter vanes for a high pressure ratio supersonic axial compressor stage[R].ARL-TR-1974-0110,1974.
[3]	Wennerstrom A J,Buzzell W A,de Rose R D,et al.Test of a supersonic axial compressor stage incorporating splitter vanes in the rotor[R].ARL-TR-1975-0165,1975.
[4]	杨小贺,单鹏.大小叶片轴流级反问题设计及数值模拟[J].航空学报,2011,32(10):1786-1795. YANG Xiaohe,SHAN Peng.Inverse problem and numerical simulation of axial stage with splitter rotor[J].Acta Aeronautica et Astronautica Sinica,2011,32(10):1786-1795.(in Chinese)
[5]	严明,陈懋章.大小叶片轴流压气机转子流动特性分析[J].推进技术,2002,23(4):280-282. YAN Ming,CHEN Maozhang.Flow performance analysis in an axial compressor rotor with splitter[J]. Journal of Propulsion Technology,2002,23(4):280-282.(in Chinese)
[6]	张永新,邹正平,严明,等.单级大小叶片轴流压气机流动分析[J].航空动力学报,2004,19(1):89-93. ZHANG Yongxin,ZOU Zhengping,YAN Ming,et al.Flow analysis of a single-stage axial flow compressor with splitter rotor[J].Journal of Aerospace Power,2004,19(1):89-93.(in Chinese)
[7]	陈懋章,刘宝杰.中国压气机基础研究及工程研制的一些进展[J].航空发动机,2007,33(1):1-9. CHEN Maozhang,LIU Baojie.Progress on fundamental study and engineering development for compressor in China[J].Aeroengine,2007,33(1):1-9.(in Chinese)
[8]	Marshall J,Imregun M.A review of aeroelasticity methods with emphasis on turbomachinery applications[J].Journal of Fluids and Structures,1996,10(3):237-267.
[9]	Whitehead D.Effect of mistuning on the vibration of turbomachine blades induced by wakes[J].Journal of Mechanical Engineering Science,1966,8(1):15-21.
[10]	张小伟.叶轮机械叶片气弹稳定性数值预测方法研究[D].北京:北京航空航天大学,2010. ZHANG Xiaowei.Numerical prediction method for aeroelastic stability of blades in turbomachines[D].Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)
[11]	Chiang H W,Fleeter S.Flutter control of incompressible flow turbomachine blade rows by splitter blades[R].AIAA 91-1900,1991.
[12]	Fleeter S,Topp D A,Hoyniak D.Control of rotor aerodynamically forced vibrations by splitters[J].Journal of Propulsion and Power,1988,4(5):445-451.
[13]	Sadeghi M,Liu F.Computation of mistuning effects on cascade flutter[J].AIAA Journal,2001,39(1):22-28.
[14]	Sadeghi M,Liu F.Investigation of mistuning effects on cascade flutter using a coupled method[J].Journal of Propulsion and Power,2007,23(2):266-272.
[15]	付志忠,王延荣.前后掠风扇叶片颤振特性对比分析[J].航空动力学报,2013,28(8):1803-1807. FU Zhizhong,WANG Yanrong.Comparison of flutter characteristics of forward/backward swept fan blades[J].Journal of Aerospace Power,2013,28(8):1803-1807.(in Chinese)
[16]	Moffatt S,Ning W,Li Y,et al.Blade forced response prediction for industrial gas turbines[J].Journal of Propulsion and Power,2005,21(4):707-714.
[17]	NUMECA Incorporation.FINE/Turbo theoretical manual[M].Brussels,Belgium:NUMECA International,2013.
[18]	Debrabandere F,Tartinville B,Hirsch C,et al.Fluid-structure interaction using a modal approach[J].Journal of Turbomachinery,2012,134(5):597-626.