航空发动机振动应力测量的贴片可靠性及优化分析

推进技术 ›› 2016, Vol. 37 ›› Issue (10): 1964-1969.

航空发动机振动应力测量的贴片可靠性及优化分析

蔡宁泊,侯乃先,张成成

中航商用航空发动机有限责任公司，上海 200241,中航商用航空发动机有限责任公司，上海 200241,中航商用航空发动机有限责任公司，上海 200241

发布日期:2021-08-15
作者简介:蔡宁泊，男，硕士，工程师，研究领域为航空发动机振动。

Reliability and Optimization Analysis of Strain-Gauge

AVIC Commercial Aircraft Engine CO. LTD.，Shanghai 200241，China,AVIC Commercial Aircraft Engine CO. LTD.，Shanghai 200241，China and AVIC Commercial Aircraft Engine CO. LTD.，Shanghai 200241，China

Published:2021-08-15

摘要/Abstract

摘要： 为了评估航空发动机应变片粘贴误差对振动应力测量结果的影响程度，利用有限元计算与蒙特卡洛分析方法对压气机转子叶片的贴片方案进行了研究，并提出基于可靠度的贴片方案优化准则。分析结果表明:当贴片位置由应变梯度较小的B点移动至应变梯度较大的A点时，相对应变误差增加了0.5倍，贴片可靠度降低了0.3倍；当贴片方向与最大主应变方向之间的夹角由0°增加至30°时，相对应变误差增大了0.6倍，贴片可靠度降低了0.4倍；根据可靠度准则，所选贴片方案可同时对两阶模态的振动应力进行有效测量，其可靠度达到限制值0.9以上，表明将该准则用于贴片方案寻优是合适的。

关键词: 航空发动机；振动测量；贴片方案；可靠性；寻优准则

Abstract: The strain-gauge application schemes were investigated through finite element analysis and Monte Carlo simulation methods，so as to evaluate the impact of sensor placement tolerances on vibratory response during aero-engine vibration test. The strain-gauge application scheme optimum criterion was put forward based on reliability theory. The analysis results show that when the strain-gauge was placed from point B to point A，because of the raising of strain gradient，the relative strain error increased by 0.5 times，and the reliability of the scheme was decreased by 0.3 times. When the angle between strain-gauge placement orientation and maximum principle strain orientation was expanded from 0° to 30°，the relative strain error increased by 0.6 times，while the reliability of the scheme was decreased by 0.4 times. According to the reliability criterion，the selected strain-gauge application scheme could effectively measure the vibration stress of two modes simultaneously，and it’s reliability exceeded the limit value of 0.9. The research indicates that it is adequate to use the reliability criterion for the strain-gauge application scheme optimization.

Key words: Aero-engine；Vibration measurements；Strain-gauge application；Reliability；Optimum criterion

蔡宁泊,侯乃先,张成成. 航空发动机振动应力测量的贴片可靠性及优化分析[J]. 推进技术, 2016, 37(10): 1964-1969.

CAI Ning-bo,HOU Nai-xian,ZHANG Cheng-cheng. Reliability and Optimization Analysis of Strain-Gauge[J]. Journal of Propulsion Technology, 2016, 37(10): 1964-1969.

参考文献

[1] 吴大观. 不容忽视发动机叶片动应力测量的作用[J]. 燃气涡轮试验与研究, 1996, 1(1): 58-62.
[2] 吴大观. 发动机叶片动应力测量[J]. 航空科学技术, 1996, 3(1): 3-6.
[3] 王杰, 赵子荣, 姚建尧, 等. 压气机转子叶片高循环疲劳概率寿命研究[J]. 现代振动与噪声技术, 2011, 9(1): 312-321.
[4] 王延荣, 田爱梅. 叶/盘结构振动分析中几个问题的探讨[J]. 推进技术, 2002, 23(3): 233-236. (WANG Yan-rong, TIAN Ai-mei. Several Issues in the Implementation of Vibration Analysis of Bladed Disk[J]. Journal of Propulsion Technology, 2002, 23(3): 233-236.)
[5] GJB 242-1987: 航空涡轮螺桨和涡轮轴发动机通用规范[S]. 北京:中国标准出版社, 1987.
[6] CCAR33-R2:航空发动机适航规定[S]. 北京:中国民用航空局, 2011.
[7] 沈观林. 应变电测与传感器技术的新发展及应用[J].中国测试, 2011, 37(2): 87-96.
[8] 李仙丽, 罗乘川, 安奕忱, 等. 基于遥测技术的发动机涡轮转子叶片动应力测量[J]. 燃气涡轮试验与研究, 2014, 27(6): 53-56.
[9] 彭建, 刘兵. 压气机转子叶片动频动应力测试技术和应用研究[J]. 燃气涡轮试验与研究, 2003, 16(1): 10-13.
[10] 乔俊. 电阻应变片的粘贴方法浅论[J]. 科技创业家, 2013, 21(1).
[11] Nichol K L. Strain-Gage Placement Considerations for Dynamic Data Analysis[C]. Baltimore: 32nd Structures, Structural Dynamics, and Materials Conference, 1991.
[12] 卢艳辉, 梅庆, 雷沫枝, 等. 高转速压气机转子叶片的动应力测试与动力学设计评估[J]. 推进技术, 2014, 35(10): 1398-1403. (LU Yan-hui, MEI Qing, LEI Mo-zhi, et al. Vibration Stress Test and Dynamical Evaluation for High Rotational Speed Compressor Blades Through Numerical and Experimental Method [J]. Journal of Propulsion Technology, 2014, 35(10):10-13.)
[13] 向宏辉, 任铭林, 杜文军. 尾流激振对转子叶片振动应力影响试验研究[J]. 燃气轮机技术, 2010, 23(1):25-29.
[14] Sensmerir M D, Nichol K L. Optimum Placement of Sensors for Vibration Measurements on Turbine Engine Blades[C]. Orlando: 39th Structures, Structural Dynamics, and Materials Conference and Exhibit, 1998.
[15] 李云安. 岩石有限应变测量的莫尔圆图解网法[J]. 地质科技情报, 1993, 12(1):53-58.
[16] 艾书民, 王克明, 翟学, 等. 稳态温度场作用下涡轮叶片的可靠性分析[J]. 沈阳航空航天大学学报, 2012, 29(12): 28-32.
[17] 北京航空材料研究所. 航空发动机设计用材料数据手册[M]. 北京:中国航空发动机总公司, 1990.　　　　　　　　　　　　　*　收稿日期:2015-03-20；修订日期:2015-07-01。作者简介:蔡宁泊,男,硕士,工程师,研究领域为航空发动机振动。E-mail: cainingbo@163.com(编辑:梅瑛)