旋转盘腔盘罩间隙比的敏感性分析

丁水汀; 李烨; 张弓

旋转盘腔盘罩间隙比的敏感性分析

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室适航技术研究中心, 北京 100191

基金项目: 航空发动机复杂系统安全性教育部长江学者创新团队(IRT0905)

计量
- 文章访问数: 1719
- HTML浏览量: 93
- PDF量: 422
- 被引次数: 0
出版历程
- 收稿日期: 2011-05-05
- 修回日期: 2011-12-04
- 刊出日期: 2012-03-28

Sensibility analysis of gap ratio in rotating cavity

Airworthiness Technologies Research Center, National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为保证寿命限制件之一的涡轮盘满足适航性要求,采用单向流固耦合(fluid structure interaction,简称FSI)数值方法,研究转静系旋转盘腔盘罩间隙比的变化对转盘安全性的影响机理.并且,由流阻、换热效果和应力分布三方面构成的工程评价体系对盘罩间隙比的影响进行评价以及敏感性分析.结果表明:盘罩间隙比的变化能够影响旋转盘腔内流动结构的强度,从而改变盘面换热效果和转盘温度分布,导致与温度梯度相关的热应力也发生变化.随着盘罩间隙比的增加,旋转盘腔的流阻损失基本不变,转盘迎风面平均换热效果呈现先增强后减弱的趋势,转盘整体应力水平上升,以及出现在盘心处的最大等效应力值增大.盘罩间隙比的变化能够从材料许用应力和实际使用载荷两方面影响涡轮盘的失效概率,因此,在涡轮盘腔设计阶段,需考虑盘罩间隙比对涡轮盘安全性的影响.
- 适航 /
- 旋转盘腔 /
- 盘罩间隙比 /
- 冷却效果 /
- 敏感性分析
Abstract: The sensibility analysis of the gap ratio was investigated on the cooling effect of the rotating cavity with intent of ensuring safety of a turbine disk,one of the life-limited parts in the propulsion system.The cooling effect was evaluated by fluid-structure-interaction numerical method according to resistance evaluation,heat transfer evaluation and stress distribution evaluation.The results show that the gap ratio has a great effect on heat transfer and temperature distribution of the rotating disk.Furthermore,the thermal stress of the rotating disk related to the temperature gradient can be affected.As the rising of the gap ratio,the frictional windage of the rotating cavity has not changed,heat transfer of the windward of the disk takes on up-down tendency,and the stress level and the maximum value enlarged.Therefore,change of the gap ratio has an effect on the failure probability of the turbine disk from two aspects:the material affordability and the working stress.
- airworthiness /
- rotating cavity /
- gap ratio /
- cooling effect /
- sensibility analysis

HTML

参考文献(16)

[1]	Sehra A K,Whitlow W Jr.Propulsion and power for 21st century aviation[J].Progress in Aerospace Science,2004,40(4-5):199-235.
[2]	International Air Transport Association.Safety report 2008[M].Canada:International Air Transport Association,9049-09,2009.
[3]	U.S.Department of Transportation Federal Aviation Administration.Guidance material for 14 CFR 33.75 safety analysis.America:Federal Aviation Administration,Advisory Circular 33.75-1A,2009.
[4]	U.S.Department of Transportation Federal Aviation Administration.The United Ststates code of federal regulations,title 14,aeronautics and space, Part 33,airworthiness standards:aircraft engines[M].America:Federal Aviation Administration,2009.
[5]	U.S.Department of Transportation Federal Aviation Administration.Guidance material for aircraft engine life-limited parts requirement[M].America:Federal Aviation Administration,Advisory Circular 33.70-1,2009.
[6]	Daily J W,Nece R E.Chamber dimension effects on induced flow and frictional resistance of enclosed rotating disks[J].Journal of Basic Engineering,1960,82(1):217-232.
[7]	Bayley F J,Owen J M.The fluid dynamics of a shrouded disc system with a radial outflow of coolant[J].Trans.ASME,Journal of Engineering for Power,1970,92(3):335-341.
[8]	Howey D A,Holmes A S,Pllen K R.Radially resolved measurement of stator heat transfer in a rotor-stator disc system[J].International Journal of Heat and Mass Transfer,2010,53(1-3):491-501.
[9]	曹玉璋.航空发动机传热学[M].北京:北京航空航天大学出版社,2005.
[10]	徐国强.转静系旋转盘腔内冷气的流动与换热特性研究.北京:北京航空航天大学,1999. XU Guoqiang.Flow and heat transfer characteristics of coolant through a shrouded rotating disk system.Beijing:Beijing University of Aeronautics and Astronautics,1999.(in Chinese)
[11]	陶智,高娟,蔡毅,等.高位垂直进气转静系旋转盘腔流场的实验[J].航空动力学报,2007,22(3):347-351. TAO Zhi,GAO Juan,CAI Yi,et al.Experimental investigation of the flow field between a rotating and a stationary disk at high-positioned air inflow[J].Journal of Aerospace Power,2007,22(3):347-351.(in Chinese)
[12]	丁水汀,陶智,徐国强,等.旋转盘腔冷却问题的工程评价[J].航空动力学报,1999,14(1):83-86. DING Shuiting,TAO Zhi,XU Guoqiang,et al.An engineering evaluation system of turbine disk cooling configuration[J].Journal of Aerospace Power,1999,14(1):83-86.(in Chinese)
[13]	FU Debin,TAO Zhi,ZHANG Gong,et al.Safety evaluation of cooling configuration in a rotor-stator cavity.Beijing:Proceedings,1st Int.Symposium on Aircraft Airworthiness,2009.
[14]	丁水汀,张弓,李烨,等.旋转盘腔进气位置的敏感性分析[J].航空动力学报,2011,26(8):1681-1687. DING Shuiting,ZHANG Gong,LI Ye,et al.Sensibility analysis of the air inlet position in the rotating cavity[J].Journal of Aerospace Power,2011,26(8):1681-1687.(in Chinese)
[15]	Enright M P,Chan K S,Moody J P,et al.Probabilistic fretting fatigue assessment of aircraft engine disks[J].Journal Engineering of Gas Turbines and Power,2010,132(7):072502-1(9 pages).
[16]	Melis M E,Zaretsky E V,August R.Probabilistic analysis of aircraft gas turbine disk life and reliability[J].Journal Propul.Power,1999,15(5):658-666.