摘要
为进一步研究暖机对发动机压气机叶尖间隙变化的具体影响,对不同暖机时间与不暖机情况下压气机叶片的径向变形进行了试验研究。由于在发动机整机试验中叶片径向变形无法测量,选择模拟件进行温度与离心耦合作用下的变形试验。利用两种叶片材料制作板材试样,以台架测试数据为基础,计算出发动机启动及慢车至最大状态过程中叶片的离心力和截面温度,并据此设计试件的载荷历程,制定试验方案。通过模拟件试验,测得不同暖机时间和不暖机情况对应载荷下模拟件的应变过程和最终应变量,并从模拟件试验结果反推构件。结果表明:相对于离心载荷,温度对叶片径向变形影响更明显,温度与转速共同作用下叶片的径向变形显著大于转速单独作用下变形;正常暖机情况下不同暖机时间对于压气机叶片的最终径向变形没有影响;而暖机与否对压气机叶片的径向变形是存在影响的,其中暖机后与不暖机TC6模拟件变形范围分别为0.468%~0.502%和0.413%~0.466%,GH2150变化分别为0.793%~0.801%和0.765%~0.766%,暖机后的叶片径向变形量稍大于不暖机。
In order to further study the specific influence of heating on the tip clearance of engine compressor,the radial deformation of compressor blade under different heating time and unheating condition is experimentally studied. Because the radial deformation of the blade cannot be measured in the whole engine test,the specimen is selected to conduct the deformation test under the coupling effect of temperature and centrifugal force. Two kinds of blade materials are used to make plate samples. Based on the test data of engine,the centrifugal force and section temperature of the blade in the process of starting and idling to the maximum state are calculated. The load history of the specimen is designed and the experiment plan is formulated based on the calculation results. Through specimen experiment,the strain process and final strain results of the specimen under the load corresponding to different heating time and unheating conditions are measured. Extrapolating the component from the specimen experiment result,it can be proved that compared with centrifugal load temperature has a significant effect on the radial deformation of blade. The radial deformation of blade under the joint action of temperature and speed is significantly greater than that under the action of speed alone. Under normal heating condition,different heating time has no effect on the final radial deformation of compressor blade. But whether the turbine is heating or not has an effect on the radial deformation of compressor blade. Under heating and unheating conditions,the deformation ranges of TC6 specimen are 0.468%~0.502% and 0.413%~0.466%,respectively,and the variation ranges of GH2150 specimen are 0.793%~0.801% and 0.765%~0.766%,respectively. The radial deformation of blade after heating is slightly larger than that without heating.
作者
钱仁军
李本威
宋汉强
张赟
朱飞翔
QIAN Ren-jun;LIBen-wei;SONG Han-qiang;ZHANG Yun;ZHU Fei-xiang(Aviation Foundation College,Naval Aviation University,Yantai 264001,China;Unit 92728,Shanghai 200436,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2022年第3期122-132,共11页
Journal of Propulsion Technology
基金
国家自然科学基金(51505492)
泰山学者建设工程专项经费。
关键词
涡扇发动机
压气机
叶片
径向变形
模拟试验
Turbofan engine
Compressor
Blade
Radial deformation
Specimen test
