基于台架试验的涡轴发动机喘振发生位置规律

闫思齐; 李本威; 王永华; 张赟; 周鹏宇

doi:10.13224/j.cnki.jasp.20210085

基于台架试验的涡轴发动机喘振发生位置规律

doi: 10.13224/j.cnki.jasp.20210085

1.
海军航空大学航空基础学院，山东烟台 264001
2.
中国人民解放军 92326部队，广东湛江 524005

基金项目: 国家自然科学基金（51505492）；山东省自然科学基金（ZR2020ME125）

详细信息

作者简介:
闫思齐（1993-），男，博士生，主要从事航空发动机状态监控与健康评估方面的研究。E-mail：q525943734@163.com

中图分类号: V231.3
计量
- 文章访问数: 132
- HTML浏览量: 8
- PDF量: 100
- 被引次数: 0
出版历程
- 收稿日期: 2021-02-25
- 刊出日期: 2022-02-28

Position rule of turboshaft engine surge based on bench test

1.
Aeronautical Foundation Institute，Naval Aviation University，Yantai Shandong 264001，China
2.
Unit 92326，People's Liberation Army，Zhanjiang Guangdong 524005，China

摘要

摘要: 为了探究某型涡轴发动机喘振发生位置规律，采集并分析了台架喘振试验时进气道、轴流压气机叶尖、轴流压气机出口和离心压气机出口的压力信号。采用连续小波时频变换对压力信号进行特征提取，以小波系数作为喘振信号特征，阈值为小波系数最大值的10%，结果表明：某型涡轴发动机的轴流压气机总是比离心压气机先发生喘振，喘振在轴向上由进气道向离心压气机传递的同时，在周向上也沿着压气机转子叶片旋转方向传递。对某型号发动机进行实时喘振监测时，监测轴流压气机能比监测离心压气机更早发现喘振，在后续某型涡轴发动机改型设计时，可增加轴流压气机的喘振裕度来提升整机防喘能力。
- 涡轴发动机 /
- 压气机 /
- 喘振试验 /
- 特征提取 /
- 小波变换
Abstract: In order to investigate the surge position of turboshaft engine，the pressure signals of air inlet，axial compressor tip，axial compressor outlet and centrifugal compressor outlet were collected and analyzed during the bench surge test.Continuous wavelet time-frequency transform was used to extract the characteristics of the pressure signal.The wavelet coefficients were used as the characteristics of the surge signal，and the threshold value was 10% of the maximum value of the wavelet coefficients.The results showed that the axial flow compressor of a turboshaft engine surged earlier than the centrifugal compressor，and the surge was transmitted from the inlet to the centrifugal compressor in the axial direction，and also along the rotor blade rotation in the circumferential direction.When the real-time surge monitoring was carried out for a certain type of engine，the surge can be detected earlier by monitoring the axial compressor than by monitoring the centrifugal compressor.In the subsequent modification design of a certain type of turboshaft engine，the surge margin of the axial compressor can be increased to improve the anti-surge ability of the whole engine.
- turboshaft engine /
- compressor /
- surge test /
- feature extraction /
- wavelet transform

HTML

参考文献(23)

[1]	潘天宇,孙太璐,李志平,等.局部喘振的发生机理[J].航空动力学报,2016,31（4）:877-885.
[2]	代坷,郭峰,失剑锋,等.基于DMD方法的超声速进气道喘振特性分析[J].航空动力学报,2019,34（5）:1076-1084.
[3]	孙晓峰,何晨,刘小华,等.航空压气机流动稳定性预测研究进展[J].推进技术,2017,38（10）:2172-2185.
[4]	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.
[5]	旷桂兰,姚峥嵘,王道波,等.某涡轴发动机整机逼喘试验研究[J].航空动力学报,2009,24（3）:588-595.
[6]	MAILACH R,LEHMANN I,VOGELER K.Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex[J].Journal of Turbomachinery,2001,123（3）:453-460.
[7]	PETER J,PARDOWITZ B,ECK M,et al.Advanced stereo high-speed PIV in an annular cascade without clearance:evidences of rotating instability[R].Stockholm,Swede:European Conference on Turbomachinery Fluid Dynamics and Thermodynamics,2017.
[8]	ECK M,RüCKERT R,PEITSCH D.Advanced application of a sublayer fence probe in highly instationary turbomachinery flows:observations on prestall instabilities[J].Experiments in Fluids,2019,60（3）:47.1-47.17.
[9]	桂幸民,滕金芳,刘宝杰,等.航空压气机气动热力学理论与应用[M].上海:上海交通大学出版社,2014.
[10]	贺象,马宏伟,银越千,等.小尺寸多级轴流压气机喘振现象试验[J].航空动力学报,2016,31（8）:1957-1963.
[11]	潘天宇,贺雷,王正鹤,等.局部喘振频率特性及估算方法[J].航空动力学报,2015,30（11）:2666-2672.
[12]	王玉东.基于压气机出口静压变化率的喘振检测方法[J].航空动力学报,2020,35（6）:1131-1139.
[13]	李小彪,余海生,孙建国,等.一种涡扇发动机喘振信号判定方法[J].推进技术,2009,30（6）:727-729，739.
[14]	LI J C.Self-adaptive stability enhancing technology with tip air injection in an axial flow compressor[J].Journal of Turbomachinery,2017,139（1）:1-9.
[15]	LI J C,LIU Y,DU J,et al.Automatic stability control using tip air injection in a multi-stage axial compressor[J].Aerospace Science and Technology,2020,98（2）:1-12.
[16]	LI J C,DU J,GENG S J,et al.Tip air injection to extend stall margin of multi-stage axial flow compresso with inlet radial distortion[J].Aerospace Science and Technology,2020,96（1）:1-13.
[17]	吴学辉,伍友利,李志刚,等.轴流压缩系统的 Lyapunov指数谱分析及应用[J].推进技术,2006,27（1）:37-39.
[18]	王占学,王鹏,乔渭阳.畸变进气时涡扇发动机整机环境下压缩部件气动稳定性评定[J].推进技术,2007,28（1）:20-25.
[19]	HAGINO N,KASHIWABARA Y.Experimental study of surge and rotating stall occurring in small centrifugal compressor[R].Denver,USA:the 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,2009.
[20]	LIN F,CHEN J Y,LI M L.Wavelet analysis of rotor-tip disturbances in an axial-flow compressor[J].Journal of Propulsion and Power,2004,20（2）:319-334.
[21]	LIN F,LI M L,CHEN J Y.Long-to-short length-scale transition:a stall inception phenomenon in an axial compressor with inlet distortion[J].Journal of Turbomachinery,2006,128（1）:130-140.
[22]	LIU Y,LI J C,DU J,et al.Application of fast wavelet analysis on early stall warning in axial compressors[J].Journal of Thermal Science,2019,28（5）:837-849.
[23]	刘洋,李继超,杜娟,等.周向畸变下轴流压气机的失速预警方法研究及应用[J].推进技术,2020,41（9）:1967-1974.