航空发动机风扇叶片与机匣刮蹭分析及结构设计

柴象海; 史同承; 王少辉; 张执南

doi:10.13224/j.cnki.jasp.2019.09.004

航空发动机风扇叶片与机匣刮蹭分析及结构设计

doi: 10.13224/j.cnki.jasp.2019.09.004

1.
中国航空发动机集团有限公司商用航空发动机有限责任公司,上海 200241
2.
中国航空研究院上海分院,上海 200241
3.
上海交通大学机械系统与振动国家重点实验室,上海 200240

基金项目: 国家重点研发计划（2018YFB1106400）; 上海科委项目（17DZ1120000）;机械系统与振动国家重点实验室项目(MSVZD201912)

计量
- 文章访问数: 1585
- HTML浏览量: 271
- PDF量: 1327
- 被引次数: 0
出版历程
- 收稿日期: 2019-04-24
- 刊出日期: 2019-09-28

Rubbing analysis and structural design for fan blade and case of aero-engine

摘要

摘要: 针对异常载荷下,航空发动机宽弦风扇叶片的叶尖与机匣刮蹭变形及损伤特征缺乏数据支持,而传统理论计算方法存在较大的误差问题，建立了宽弦风扇叶片叶尖刮蹭显式动力学分析模型,采用宽弦风扇叶片与机匣刮蹭试验数据,对分析模型的计算精度进行了验证。基于分析模型进行了仿真参数的敏感度分析,得到了叶片与机匣刮蹭后叶片变形及机匣损伤规律。研究结果表明：叶尖伸长量对转子转速非常敏感，叶尖径向伸长量增加速率远大于转速增加值，因此在叶片设计中应考虑到风扇叶片极限转速下叶尖伸长量。同时需要选取合理的扭转角度以满足叶片安全性和气动性能的要求。在风扇机匣包容区设计中应主动考虑异常载荷的影响，增大安全性设计域度；设计合理的耐磨层材料参数，减小风扇叶片对其冲击损伤。采用该方法可以提高叶尖间隙控制精度,减小刮蹭对叶片和机匣造成的损伤。
- 涡扇发动机 /
- 宽弦风扇叶片 /
- 风扇机匣 /
- 刮蹭 /
- 结构设计
Abstract: Under abnormal loads, there is often a lack of data to describe the rubbing deformation and damage characteristics between the blade tip and the case of the wide-chord fan blade of aero-engines. The traditional theoretical calculation methods have large errors. To solve this problem, an explicit dynamic analytical model for the blade tip rubbing of a wide-chord fan was established. The calculation accuracy of the analytical model was verified by utilizing the test data of wide-chord fan blades and case. Based on the analytical model, sensitivity analysis of simulation parameters were carried out. The rules of blade deformation and case damage after the rubbing of the blade and case were obtained. The results indicate that the blade tip elongation is sensitive to rotor speed,and the increase rate of blade tip elongation is much bigger than the rotor speed.So the blade tip elongation at limited fan blade speed was considered in design. Suitable twist angle is an important factor of safe and dynamic performance demand.In the case inclusive area design, it is necessary to enlarge the safe margin to eliminate the influence of abnormal load. Choosing wear-resistant material with reasonable parameter is helpful to reduce the impact damage from fan blade. The proposed method can improve the accuracy of tip clearance control, and reduce the risk of rubbing and the damage of blade and case caused by rubbing.
- turbine engine /
- wide-chord fan blade /
- fan case /
- rubbing damage /
- structural design

HTML

参考文献(18)

[1]	刘大响,金捷,彭友梅,等.大型飞机发动机的发展现状和关键技术分析［J］.航空动力学报,2008,23(6):976-980.LIU Daxiang,JIN Jie,PENG Youmei,et al.Summarization of development status and key technologies for large airplane engines［J］.Journal of Aerospace Power,2008,23(6):976-980.(in Chinese)
[2]	杨雯,杜发荣,郝勇,等.宽弦空心风扇叶片动力响应特性研究［J］.航空动力学报,2007,22(3):444-449.YANG Wen,DU Farong,HAO Yong,et al.Investigation of dynamic response property of wide-chord fan blade［J］.Journal of Aerospace Power,2007,23(3):444-449.(in Chinese)
[3]	梁春华.高性能航空发动机先进的风扇和压气机叶片综述［J］.航空发动机,2006,32(3):49-52.LIANG Chunhua.Overview of advanced fan and compressor blade/vane in high performance aero-engine［J］.Aeroengine,2006,32(3):49-52.(in Chinese)
[4]	SARKAR S,ATLURI S N.Effects of multiple blade interaction on the containment of blade fragments during a rotor failure［J］.Finite Element in Analysis and Design,1996,23(2):211-223.
[5]	侯冠群,尚波生.宽弦风扇叶片技术的发展［J］.国际航空,2002(12):45-47.HOU Guanqun,SHANG Bosheng.Development wide chord fan blades technological［J］.International Aviation,2002(12):45-47.(in Chinese)
[6]	陈巍,杜发荣,李云清.航空发动机转子碰摩故障状态识别［J］.航空动力学报,2009,24(8):1706-1713.CHEN Wei,DU Farong,LI Yunqing.Identification of rotor-rubbing malfunctions in aero-engines［J］.Journal of Aerospace Power,2009,24(8):1706-1713.(in Chinese)
[7]	杨家礼,涂孟罴,张亿力,等.一种涡轮叶尖间隙控制技术［J］.航空动力学报,2014,29(9):2195-2201.YANG Jiali,TU Menggang,ZHANG Yili,et al.A tip clearance control technology for turbine［J］.Journal of Aerospace Power,2014,29(9):2195-2201.(in Chinese)
[8]	TENG X,WIERZBICKI T.Gouging and fracture of engine containment structure under fragment impact［J］.Journal of Aerospace Engineering,2008,21(3):174-179.
[9]	杨剑秋,王延荣.基于正交试验设计的空心叶片结构优化设计［J］.航空动力学报,2011,26(2):376-384.YANG Jianqiu,WANG Yanrong.Structural optimization of hollow fan blade based on orthogonal experimental design［J］.Journal of Aerospace Power,2011,26(2):376-384.(in Chinese)
[10]	蒋向华,王延荣.航空发动机转子级鸟撞损伤及机匣包容数值模拟［R］.北京:中国航空学会第1届航空发动机数值仿真与数字化设计学术交流会,2008.
[11]	SINHA S K.Non-linear dynamic response of a rotating radial Timoshenko beam with periodic pulse loading at the free-end［J］.International Journal of Non-Linear Mechanics,2005,40(1):113-149.
[12]	FORSBERG J,NILSSON L.Evaluation of response surface methodologies used in crashworthiness optimization［J］.International Journal of Impact Engineering,2006,32(5):759-777.
[13]	荣见华,姜节胜,胡德文,等.基于应力及其灵敏度的结构拓扑渐进优化方法［J］.力学学报,2003,35(5):584-591.RONG Jianhua,JIANG Jiesheng,HU Dewen,et al.A structural topology evolutionary optimization method based on stresses and their sensitivity［J］.Acta Mechanica Sinca,2003,35(5):584-591.(in Chinese)
[14]	刚铁.宽弦空心风扇叶片结构设计及强度分析研究［D］.南京:南京航空航天大学,2005.GANG Tie.Research on structural design and stress analysis of hollow fan blades［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese)
[15]	KRISHNAMURTHY T.Response surface approximation with augmented and compactly supported radial basis functions［R］.AIAA-2003-1748,2003.
[16]	JIN R,CHEN W,SIMPSON T W.Comparative studies of meta modelling techniques under multiple modeling criteria［J］.Structural and Multidisciplinary Optimization,2001,23(1):1-13.
[17]	梁武昌,楚武利,朱俊强,等.非轴对称尖部间隙对轴流压气机性能影响的实验研究［J］.航空动力学报,2004,19(2):233-236.LIANG Wuchang,CHU Wuli,ZHU Junqiang,et al.Effects of asymmetric tip clearance on axial flow compressor performance［J］.Journal of Aerospace Power,2004,19(2):233-236.(in Chinese)
[18]	KURTARAN H,ESKANDARIAN A,MARZOUGUI D,et al.Crashworthiness design optimization using successive response surface approximations［J］.Computational Mechanics,2002,29(4/5):409-421.