Forced Response Prediction of Gas Turbine Rotor Blades

Gary Hilbert, R. Ni, Ronald K. Takahashi
{"title":"Forced Response Prediction of Gas Turbine Rotor Blades","authors":"Gary Hilbert, R. Ni, Ronald K. Takahashi","doi":"10.1115/imece1997-0750","DOIUrl":null,"url":null,"abstract":"\n An analytical forced response prediction system is used to predict turbomachinery airfoil vibratory stress amplitudes. The forced airfoil vibration can be caused by time dependent (unsteady) aerodynamic loads due to interaction with the flow field from neighboring airfoils rows, such as shocks, wakes, or pressure waves, or due to self induced unsteady aerodynamics such as vortex shedding and unsteady tip vortices. The amplitude of the forced response is of particular interest when the frequency of the time dependent unsteadiness is close to the natural frequency of the forced airfoil. At this condition, the airfoil is at or near resonance and vibratory stress can exceed the material capability causing high cycle fatigue (HCF) failures.\n The airfoil forced response prediction system presented here combines structural static and dynamic analysis with steady and unsteady computational fluid dynamic analysis in an iterative coupled solution to the aeroelastic problem. The system includes three dimensional viscous multistage steady and unsteady computational fluid dynamics and three dimensional geometric nonlinear structural static, linear free vibration and modal forced response analysis to predict the airfoil amplitude in the resonance modes during engine operation.\n This analysis system is being used to help identify the cause of HCF failure and determine corrective action. The analysis system is demonstrated using a compressor rotor excited by upstream and downstream vanes. Results are then compared with engine test data.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"8 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"7","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Analysis and Design Issues for Modern Aerospace Vehicles","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1115/imece1997-0750","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
引用次数: 7

Abstract

An analytical forced response prediction system is used to predict turbomachinery airfoil vibratory stress amplitudes. The forced airfoil vibration can be caused by time dependent (unsteady) aerodynamic loads due to interaction with the flow field from neighboring airfoils rows, such as shocks, wakes, or pressure waves, or due to self induced unsteady aerodynamics such as vortex shedding and unsteady tip vortices. The amplitude of the forced response is of particular interest when the frequency of the time dependent unsteadiness is close to the natural frequency of the forced airfoil. At this condition, the airfoil is at or near resonance and vibratory stress can exceed the material capability causing high cycle fatigue (HCF) failures. The airfoil forced response prediction system presented here combines structural static and dynamic analysis with steady and unsteady computational fluid dynamic analysis in an iterative coupled solution to the aeroelastic problem. The system includes three dimensional viscous multistage steady and unsteady computational fluid dynamics and three dimensional geometric nonlinear structural static, linear free vibration and modal forced response analysis to predict the airfoil amplitude in the resonance modes during engine operation. This analysis system is being used to help identify the cause of HCF failure and determine corrective action. The analysis system is demonstrated using a compressor rotor excited by upstream and downstream vanes. Results are then compared with engine test data.
燃气轮机转子叶片强迫响应预测
采用解析式强迫响应预测系统对涡轮机械翼型振动应力幅值进行了预测。强迫翼型振动可以由时间依赖(非定常)气动载荷引起,由于与邻近翼型排的流场相互作用,如冲击、尾迹或压力波,或由于自诱导的非定常空气动力学,如旋涡脱落和非定常叶尖涡。强迫响应的幅度是特别感兴趣的时候,时间依赖的不稳定的频率接近于强迫翼型的固有频率。在这种情况下,翼型处于或接近共振和振动应力可以超过材料的能力,导致高循环疲劳(HCF)失效。本文提出的翼型强迫响应预测系统将结构静力与动力分析与定常与非定常计算流体动力学分析相结合,采用迭代耦合方法求解气动弹性问题。该系统包括三维粘性多级定、非定常计算流体动力学和三维几何非线性结构静力、线性自由振动和模态强迫响应分析,用于预测发动机运行过程中共振模态下翼型幅值。该分析系统用于帮助确定HCF故障的原因并确定纠正措施。以压气机转子为例,对该分析系统进行了验证。然后将结果与发动机试验数据进行比较。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
求助全文
约1分钟内获得全文 求助全文
来源期刊
自引率
0.00%
发文量
0
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
确定
请完成安全验证×
copy
已复制链接
快去分享给好友吧!
我知道了
右上角分享
点击右上角分享
0
联系我们:info@booksci.cn Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。 Copyright © 2023 布克学术 All rights reserved.
京ICP备2023020795号-1
ghs 京公网安备 11010802042870号
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术官方微信