Research on online detection of test status for heavy gas turbine compressors
-
摘要:
针对重型燃气轮机压气机部件质量重、空气流量大、转速高、试验风险高等特点,开展重型燃气轮机压气机部件试验状态双余度模式在线检测技术研究。通过分析压气机试验不稳定工作状态参数特征,设计基于时频-小波辨识算法,研制出具有国内自主知识产权的重型燃气轮机压气机部件试验状态双余度模式在线检测系统,解决试验过程缺乏有效安全自动检测的技术难题。该系统相对于国内同类产品,能够更可靠、准确、及时地检测到压气机试验不稳定工作状态动态特征信号,辨识系统响应时间优于50 ms,具备对重型燃气轮机压气机部件试验状态在线预警能力。
Abstract:Based on the characteristics of heavy gas turbine compressor components, such as heavy weight, large air flow, high rotating speed, and high test risk, research on the online detection technology of double-redundancy-model for heavy gas turbine compressor components’ test status was carried out. By analyzing parameter characteristics of unstable operating status in compressors test, designing identification algorithm based on time-frequency and wavelet analysis, a double-redundancy-model online detection system for heavy gas turbine compressors’ test status was developed with domestic independent intellectual property rights, then the technological problem of effective safety automatic detection in the test process was solved. Compared with similar domestic products, the system can detect the dynamic characteristic signal of unstable operating status for compressors test more reliably, accurately and timely, and identify response time of the system within 50 ms. The research can provide the ability of on-line pre-warning of the test status for heavy gas turbine compressor components.
-
Key words:
- double redundancy model /
- unstable operating status /
- signal extract /
- wavelet analysis /
- response time
-
-
[1] 刘大响, 叶培梁, 胡骏, 等. 航空燃气涡轮发动机稳定性设计与评定技术[M]. 北京: 航空工业出版社, 2004. [2] 国防科学技术工业委员会. 航空燃气涡轮发动机稳定性设计与评定方法: GJB/Z224-2005[S]. 北京: 中国航空工业第一集团公司, 2005: 15-20. [3] MOORE F K,GREITZER E M. A theory of post-stall transients in axial compression systems: Part Ⅰ development of equations[J]. Journal of Engineering for Gas Turbines and Power,1986,108(1): 68-76. doi: 10.1115/1.3239887 [4] GREITZER E M,MOORE F K. A theory of post-stall transients in axial compression systems: Part Ⅱ application[J]. Journal of Engineering for Gas Turbines and Power,1986,108(2): 231-239. doi: 10.1115/1.3239893 [5] HYNES T P,GREITZER E M. A method for assessing effects of circumferential flow distortion on compressor stability[J]. Journal of Turbomachinery,1987,109(3): 371-379. doi: 10.1115/1.3262116 [6] HAYNES J M,HENDRICKS G J,EPSTEIN A H. Active stabilization of rotating stall in a three-stage axial compressor[J]. Journal of Turbomachinery,1994,116(2): 226-239. doi: 10.1115/1.2928357 [7] TRYFONIDIS M,ETCHEVERS O,PADUANO J D,et al. Prestall behavior of several high-speed compressors[J]. Journal of Turbomachinery,1995,117(1): 62-80. doi: 10.1115/1.2835644 [8] BROWN C, SAWYER S, OAKES W. Wavelet based analysis of rotating stall and surge in a high speed centrifugal compressor[R]. AIAA 2002-4080, 2002. [9] LIAO Shengfang, CHEN Jingyi. Time-frequency analysis of compressor rotating stall by means of wavelet transform[R]. ASME Paper GT-1996-57, 1996. [10] SALUNKHE P B,JOSEPH J,PRADEEP A M. Active feedback control of stall in an axial flow fan under dynamic inflow distortion[J]. Experimental Thermal and Fluid Science,2011,35(6): 1135-1142. doi: 10.1016/j.expthermflusci.2011.03.008 [11] 李长征,熊兵,韩伟. 基于时间序列分析的压气机喘振检测[J]. 测控技术,2011,30(1): 100-104. doi: 10.3969/j.issn.1000-8829.2011.01.028LI Changzheng,XIONG Bing,HAN Wei. Compressor surge detecting based on time series analysis[J]. Measurement and Control Technology,2011,30(1): 100-104. (in Chinese) doi: 10.3969/j.issn.1000-8829.2011.01.028 [12] 李长征,韩伟,熊兵. 压气机喘振模式识别与在线检测[J]. 推进技术,2011,32(3): 318-322.LI Changzheng,HAN Wei,XIONG Bing. Pattern recognition and on-line detection for compressor surge[J]. Journal of Propulsion Technology,2011,32(3): 318-322. (in Chinese) [13] 张朴,祝雪平,李应红. 失速起始检测的平均数值差分方法[J]. 航空动力学报,2003,18(4): 546-548.ZHANG Pu,ZHU Xueping,LI Yinghong. An averaged numerical difference method for detection of stall inception[J]. Journal of Aerospace Power,2003,18(4): 546-548. (in Chinese) [14] 吴云,李应红,张朴. 某涡喷发动机压气机气动失稳过程的非线性分析[J]. 航空动力学报,2005,20(5): 890-894.WU Yun,LI Yinghong,ZHANG Pu. Nonlinear analysis of the process of loosing compressor aerodynamic stability in a turbojet engine[J]. Journal of Aerospace Power,2005,20(5): 890-894. (in Chinese) [15] 张浩,蒲秋洪. 基于小波分析的压气机气动失稳检测[J]. 燃气涡轮试验与研究,2005,18(1): 38-40.ZHANG Hao,PU Qiuhong. Aerodynamic unsteadiness detection in compressor based on wavelet analysis[J]. Gas Turbine Experiment and Research,2005,18(1): 38-40. (in Chinese) [16] 田金虎,乔渭阳,彭生红. 航空发动机高空压力畸变试验[J]. 航空动力学报,2014,29(4): 817-823.TIAN Jinhu,QIAO Weiyang,PENG Shenghong. Experiment on aero-engine altitude simulated pressure distortion[J]. Journal of Aerospace Power,2014,29(4): 817-823. (in Chinese) [17] 李继超,童志庭,聂超群,等. 基于互相关分析的前失速先兆检测分析[J]. 航空学报,2013,34(1): 28-36.LI Jichao,TONG Zhiting,NIE Chaoqun,et al. Detection and analysis of early stall warning based on cross-correlation[J]. Acta Aeronautica et Astronautica Sinica,2013,34(1): 28-36. (in Chinese) [18] 钟明,陈洪敏,熊兵,等. 风扇/压气机失稳辨识系统设计与验证[J]. 燃气涡轮试验与研究,2016,29(6): 51-55.ZHONG Ming,CHEN Hongmin,XIONG Bing,et al. Design and experimental investigation of instability identification system for fan and compressor[J]. Gas Turbine Experiment and Research,2016,29(6): 51-55. (in Chinese) [19] 彭生红,钟华贵,吴锋,等. 移动插板容腔对发动机压力畸变流场的影响[J]. 航空动力学报,2018,33(9): 2242-2247.PENG Shenghong,ZHONG Huagui,WU Feng,et al. Effect of movable flat baffle’s plenum volume on pressure distortion flow field of engine[J]. Journal of Aerospace Power,2018,33(9): 2242-2247. (in Chinese) [20] 彭生红,田金虎,刘冬根,等. 中等涵道比涡扇发动机高空压力畸变试验[J]. 航空动力学报,2019,34(6): 1273-1281.PENG Shenghong,TIAN Jinhu,LIU Donggen,et al. Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal of Aerospace Power,2019,34(6): 1273-1281. (in Chinese)