发动机飞行载荷测量应变计布置方案分析
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摘要
针对发动机风扇机匣飞行载荷的测量需求,开展了机匣应变计布置方案研究。利用应力摩尔圆得出了通过若干半桥叠加不能获取主应变的结论。根据应变和载荷的线性叠加原理,通过分析典型飞行条件下发动机受力情况,将机匣承受的静载荷归为拉压力、扭矩、剪切力、弯矩载荷、压差载荷五种载荷类型,采用合理的组桥方式可消除其他载荷对目标载荷应变的影响,确定了前四种载荷类型的应变布置方案。给出了后续载荷的测量分析方法:以地面试车、稳定平飞时的载荷数据为基准点,根据受力分析结论,建立不同状态发动机参数与应变之间的关系。这些分析和结论可为应变改装提供指导,也可为其他应变测试提供了参考和借鉴。
Aiming at the flight load measurement requirements of engine fan casing,the placement scheme of casing strain gauge is studied. The conclusion that the principal strain can't be obtained by superposition of several half-bridges is obtained by using the stress Mohr circle. According to the linear superposition principle of strain and load,the static loads on the casing is classified into five load types: tension,torque,shear force,bending moment load and differential pressure load by analyzing the stress of the engine under typical flight conditions,the influence of other loads on the target load strain can be eliminated by using the reasonable combination bridge way,and the strain placement scheme of the first four load types are determined. The measurement and analysis method of the subsequent load is given: based on the load data of ground test and stable level flight,the relationship between engine parameters and strain in different states is established according to the conclusion of force analysis. These analysis and conclusions can provide guidance for strain refitting,and also provide reference for other strain testing.
Aiming at the flight load measurement requirements of engine fan casing,the placement scheme of casing strain gauge is studied. The conclusion that the principal strain can't be obtained by superposition of several half-bridges is obtained by using the stress Mohr circle. According to the linear superposition principle of strain and load,the static loads on the casing is classified into five load types: tension,torque,shear force,bending moment load and differential pressure load by analyzing the stress of the engine under typical flight conditions,the influence of other loads on the target load strain can be eliminated by using the reasonable combination bridge way,and the strain placement scheme of the first four load types are determined. The measurement and analysis method of the subsequent load is given: based on the load data of ground test and stable level flight,the relationship between engine parameters and strain in different states is established according to the conclusion of force analysis. These analysis and conclusions can provide guidance for strain refitting,and also provide reference for other strain testing.
引文
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[2]雷晓波,张强,张永峰.基于剪力桥路建立不同载荷与应变力学方程[J].现代机械,2015(1):54-57.
[3]王俨剀,王理,廖明夫,等.双转子发动机—机匣碰摩振动特征研究[J].机械科学与技术,2014,33(4):614-620.
[4]王四季,廖明夫,蒋云帆,等.对转双转子局部碰摩故障实验[J].推进技术,2013,34(1):31-36.
[5]汤阿妮,周占廷,曹景涛.起落架载荷实测应变校准技术[C].第27届ICAS国际航空技术大会,2010.
[6]雷晓波,张强,张永峰.航空发动机推力销载荷计算及应变分析[J].机械研究与应用,2014,27(4):32-34.
[7]杜鹤龄.航空发动机推力的测量和确定方法[J].航空动力学报,1997,12(4):389-392.
[8]雷晓波,张强,文敏,等.航空发动机安装节推力测量技术与试验研究[J].航空学报,2017,38(12):16-23.
[9]李其汉,胡璧刚.航空发动机强度振动测试技术[M].北京:北京航空航天大学出版社,1986.
[10]郑秀瑗,谢大吉.应力应变电测技术[M].北京:国防工业出版社,1985.