多动态参数同步测试系统构建及其应用
收稿日期: 2013-04-22
修回日期: 2013-05-24
网络出版日期: 2013-06-03
基金资助
国家级项目
Construction and Application of Synchronized Test System of Multi-dynamic Parameters
Received date: 2013-04-22
Revised date: 2013-05-24
Online published: 2013-06-03
Supported by
National Level Project
压气机试验过程中虽经常需要进行气动、振动、噪声等多种动态信号的测试与分析,但多是孤立进行的,信号的同步测试和统一分析面临困难。因此对一些多物理场耦合现象研究缺乏手段,不能完成细致的描述。本文主要针对这一问题,提出了一种可直接用于工程的多场动态信号统一同步测试分析方案。首先简要描述了动态测试技术在压气机气动非定常现象导致的气动、结构失稳研究方面所起到的作用,说明了针对压气机非定常现象进行多物理场动态信号同步测试分析技术研究的必要性。其次完成了多物理场动态信号同步测试分析方案设计,解决了时间同步、相位修正和同步测试分析等关键问题。最后将其应用于某航空发动机压气机的非定常故障机理研究方面,取得了较好的应用效果,充分展现了该动态测试平台在压气机非定常现象研究方面的广阔应用前景。
武卉 , 杨明绥 , 王德友 , 高飞龙 , 梅繁 . 多动态参数同步测试系统构建及其应用[J]. 航空学报, 2014 , 35(2) : 391 -399 . DOI: 10.7527/S1000-6893.2013.0266
Dynamical signal testing and analysis of multi-physical fields need to be conducted in the process of a compressor test, such as the aerodynamics field, vibration field and noise field. But those are isolatedly conducted tests and there are difficulties in realizing a synchronized test and unified analysis of signals. Many multi-physical field couplings cannot be described in detail because of the lack of a proper research method. In this paper, a new test method of multi-field dynamical signal synchronization is proposed, which provides a way to study coupling and it can be directly applied to engineering projects. The dynamical test technology concerning the study of dynamic and structure instability due to dynamic unsteadiness of a compressor is described briefly, which reveals the necessity of carrying out an investigation on multi-physical field dynamical signal synchronization testing and analysis for compressor unsteady phenomena. A schematic design of multi-physical field dynamical signal synchronization test and analysis is accomplished, and the key issues, such as time synchronism, phase angle modification and synchronization test and analysis are dealt with. This design is applied to the unsteady failure mechanism study of an aero-engine compressor and demonstrates satisfactory effect, which shows there may be a broad prospect for this dynamical test platform to be applied to the research of compressor unsteady performances.
[1] Yang M S, Liu S Y, Wang D Y, et al. Probes into acoustic resonance of aeroengine compressors[J]. Aeroengine, 2012, 38(5): 36-42. (in Chinese) 杨明绥, 刘思远, 王德友, 等. 航空发动机压气机声共振现象初探[J].航空发动机, 2012, 38(5): 36-42.
[2] Qiao W Y, Jing R. Turbine dynamic parameter test technology[M]. Beijing: National Defense Industry Press, 2004. (in Chinese) 乔渭阳, 敬睿. 叶轮机动态参数测试技术[M]. 北京: 国防工业出版社, 2004.
[3] Yu X J, Liu B J, Jiang H K. Three-dimensional flows near the rotor tip in an axial compressor I—experimental and theoretical studies[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(1): 48-57. (in Chinese) 于贤君, 刘宝杰, 蒋浩康.压气机转子尖部三维复杂流动I——实验和理论研究[J]. 航空学报, 2010, 31(1): 48-57.
[4] Liu B J, Yu X J, Liu H X, et al. Application of SPIV in turbomachinery[J]. Experiments in Fluids, 2006, 40(4): 621-642.
[5] Baumgartner M, Kameier F, Hourmouziadis J. Non-engine order blade vibration in a high pressure compressor[C]//20th International Symposium on Airbreathing Engines, 1995: 1-13.
[6] Kameier F, Neise W. Rotating blade flow instability as a source of noise in axial turbomachines[J]. Journal of Sound and Vibration, 1997, 203(5): 833-853.
[7] Wang T Q, Wu H Y, Peng F. The study on the acoustic measurement technology of instable flow in the high speed compressor[J]. Journal of Engineering Thermophysics, 2004, 25(1): 56-58. (in Chinese) 王同庆, 吴怀宇, 彭锋. 高速压气机不稳定流动声测量技术研究. 工程热物理学报, 2004, 25(1): 56-58.
[8] März J, Hah C, Neise W, et al. An experimental and numerical investigation into the mechanisms of rotating instability[J]. Journal of Turbomachinery, 2002, 124(3): 367-375.
[9] Yu X J, Liu B J. Stereoscopic PIV measurement of unsteady flows in an axial compressor stage[J]. Experimental Thermal and Fluid Science, 2007, 31(8): 1049-1060.
[10] Drolet M, Thomassin J, Vo H D, et al. Numerical investigation into non-synchronous vibrations of axial flow compressors by the resonant tip clearance flow[C]//Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air, 2009: 487-498.
[11] Kameier F, Neise W. Rotating blade flow instability as a source of noise in axial turbomachines[J]. Journal of Sound and Vibration, 1997, 203(5): 722-742.
[12] Vignau-Tuquet F, Girardeau D. Aerodynamic rotating vortex instability in a multi-stage axial compressor[C]//17th International Symposium on Airbreathing Engines, 2005: 1-8.
[13] Kikuta H, Iwakir K, Furukawa M, et al. Unsteady and three-dimensional flow mechanism of spike-type stall inception in an axial flow compressor rotor[C]//ASME-JSME-KSME 2011 Joint Fluids Engineering Conference, 2011: 817-829.
[14] Hellmich B, Seum J R. Causes of acoustic resonance in a high-speed axial compressor[J]. Journal of Turbomachinery, 2008, 130(3): 031003.1-031003.9.
[15] Jiang H K, Li Y C, Zhang H, et al. A large-scale axial flow compressor facility and dynamic measurement techniques for rotor flow study[J]. Journal of Aerospace Power, 1992, 7(1): 1-8. (in Chinese) 蒋浩康, 李雨春, 张洪, 等. 研究转子内流动的大尺寸轴流压气机实验装置和动态测量技术[J]. 航空动力学报, 1992, 7(1): 1-8.
[16] Ma H W, Jiang H K, Li Y C. Dynamic flow measurement and diagnosis software of flow in turbomachinery[J]. Wind Turbine Technology, 1996, 6(1): 3-5.(in Chinese) 马宏伟, 蒋浩康, 李雨春.叶轮机械内流动动态测量及流场诊断系统软件[J]. 风机技术, 1996, 6(1): 3-5.
[17] Yuan W, Lu Y J, Zhou S, et al. An application of data acquisition technique to turbomachinery experiments[J]. Journal of Aerospace Power, 2004, 19(3): 402-407. (in Chinese) 袁巍, 陆亚钧, 周盛, 等. 数据采集技术在叶轮机械实验中的应用[J]. 航空动力学报, 2004, 19(3): 402-407.
[18] Wang Y H, Jiang K Y, Huang S. Design and realization of an axial compressor parameter collecting system[J]. Gas Turbine Technology, 2009, 22(4): 24-26. (in Chinese) 王永华, 蒋科艺, 黄帅. 轴流式压气机参数采集系统的设计与实现[J]. 燃气轮机技术, 2009, 22(4): 24-26.
[19] Wang Z Q, Yuan W, Song X Z, et al. Experimental investigation on the stall process of a transonic compressor rotor[J]. Journal of Aerospace Power, 2012, 27(7): 1456-1463.(in Chinese) 王卓奇, 袁巍, 宋西镇, 等. 跨声速压气机转子失速过程的实验[J]. 航空动力学报, 2012, 27(7): 1456-1463.
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