涡轮盘径向变形非线性动态概率分析

赵合阳; 白广忱; 费成巍; 邢伟震

涡轮盘径向变形非线性动态概率分析

1.
北京航空航天大学能源与动力工程学院, 北京 100191
2. 中国人民解放军空军93705部队, 遵化 064200

基金项目: 国家自然科学基金资助项目(51275024,51175017)

详细信息

中图分类号: V 23
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- 被引次数: 0
出版历程
- 收稿日期: 2012-07-23
- 网络出版日期: 2013-07-30

Probabilistic analysis for turbine disc radial displacement

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. 93705 PLA Troops, Zunhua 064200, China

摘要

摘要: 为了合理设计和控制叶尖间隙,对涡轮盘径向变形进行非线性动态概率分析.考虑材料属性的非线性和载荷的动态性进行轮盘径向变形的确定性分析,得出轮盘变形随时间变化规律,找出了涡轮盘变形最大值.通过轮盘变形的概率分析得到:轮盘径向变形的分布特征、不同径向变形设计值δ下的失效数和可靠度、不同可靠度下的各随机参数的极限值,影响涡轮盘径向变形的随机参数的灵敏度.
- 径向变形 /
- 概率分析 /
- 非线性 /
- 动态 /
- 响应面法
Abstract: To reasonably design and control blade-tip clearance, the nonlinear and dynamic probabilistic analysis of disk radial deformation was studied based on finite element model (FEM) and response surface method (RSM). Through deterministic analysis of disk deformation considering material nolinear and loads dynamic, the disk radial deformation change with time and the maximum value of disk deformation were gained. It was available to the distribution feature of disk deformation, the failure number and reliability degrees under different radial deformation preset value δ, the limit values of random parameters under different reliabilities and the sensitivities of random parameters influencing the disk radial deformation.
- radial deformation /
- probabilistic analysis /
- nolinear /
- dynamic /
- response surface method

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参考文献(1)

[1] Hennecke D K,Trappmann K.Turbine tip clearance control in gas turbine engines .NASA N83-29254,1983 [2] Lattime S,Steinetz B.Turbine engine clearance control systems:current practices and future directions .AIAA 2002-3790,2002 [3] 漆文凯,陈伟.某型航空发动机高压涡轮叶尖间隙数值分析[J].南京航空航天大学学报,2003,35(1):63-67 Qi Wenkai,Chen Wei.Tip clearance numerical analysis of an aero-engine HPT[J].Journal of Nanjing University of Aeronautics & Astronautics,2003,35(1):63-67 (in Chinese) [4] Pilidis P,Maccallum N R L.Models for predicting tip clearance changes in gas turbines .NASA N83-29258,1983 [5] NSSA Glenn Research Center.HPT clearance control .NASA/CR-2005-213970,2005 [6] 岂兴明,朴英,祝剑虹.某型航空发动机高压涡轮叶顶间隙三维数值分析[J]．航空动力学报,2008,3(5):904-908 Qi Xingming,Pu Ying,Zhu Jianhong.3-D numerical analysis of the tip clearance of an aero-engine high pressure turbine[J].Journal of Aerospace Power,2008,3(5):904-908 (in Chinese) [7] Eeom Y S,Yoo K S,Park J Y.Reliability-based topology optimization using a standard response surface method for three-dimensional structures [J].Structural and Multidisciplinary Optimization,2011,43(2):287-295 [8] 李昌,韩兴.基于响应面法齿轮啮合传动可靠性灵敏度分析[J].航空动力学报,2011,26(3):711-715 Li Chang,Han Xing.Analysis of reliability sensitivity for gear engagement based on response surface methods[J].Journal of Aerospace Power,2011,26(3):711-715 (in Chinese) [9] Kypuros J A,Melcher K J.A reduced model for prediction of thermal and rotational effects on turbine tip clearance .NASA/TM-2003-212226,2003 [10] Annette E N,Christoph W M,Stehan S.Modeling and validation of the thermal effects on gas turbine transients [J].Journal of Engineering for Gas Turbines and Power,2005,127(3):564-572 [11] Hakan E.Design sensitivity analysis of structures based upon the singular value decomposition [J].Computer Methods in Applied Mechanics and Engineering,2002,191(5):3459-3476

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