高温下发动机涡轮叶片振动疲劳性能测试方法

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摘要针对某型发动机涡轮叶片高温下振动疲劳性能测试方法进行试验研究。搭建了涡轮叶片中值疲劳极限测量试验系统并建立了相应的试验流程，对比分析了涡轮叶片采用振幅和af值（叶片振幅a与第1阶固有频率f的乘积）两种疲劳应力表征方法的离散程度、偏差随温度的变化趋势，并对小子样升降法参数确定过程进行讨论。试验结果显示振幅作为疲劳应力表征方法的离散程度小，而且可通过常温下获得的振幅表征应力的关系去进行高温下的疲劳试验，其表征偏差位于±3%以内。以逐级加载法获得的疲劳极限预估值作为初始应力水平进行小子样升降法，获得该型涡轮叶片某温度下的中值疲劳极限为162.60MPa，试验数据分散性小。该方法可为其它类型航空发动机叶片或零部件的高温下振动疲劳性能测试提供参考。
关键词：涡轮叶片；振动疲劳；中值疲劳极限；高温；发动机叶片

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	张部声1
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	秦秀云3
	张呈波1
	2
	吴光耀3
	潘容3

关键词 ：涡轮叶片, 振动疲劳, 中值疲劳极限, 高温, 发动机叶片

Abstract：The measurement method of vibration fatigue properties for aeroengine turbine blade at high temperature are studied. The test system is estab-lished for measuring the median fatigue limit of aeroengine turbine blade, and the corresponding test process is also builded. The differences of dispersion and deviation varies with temperature between amplitude and af value(product of blade amplitude a and first-order natural frequency f) used as characterization of fatigue stress have been compared and analyzed. And also the parameter determination process of small sample up and down method is discussed. The test results show that the amplitude used as characterization of fatigue stress, not only has a small degree of disper-sion, but also can be used in the fatigue test at high temperature through the relationship between amplitude and stress obtained at room temperature. The amplitude characterization deviation is less than ±3%. The predicted fatigue limit obtained by the step loading method is taken as the initial stress level for the small sample up and down method. The median fatigue limit value of the aeroengine turbine blade with 50% reliability at a high temperature is 162.60MPa, and the dispersion of test data is small. This method also presents a reference to vibration fatigue properties test of other types of aeroengine blades or parts at high temperature.
Key words: aeroengine turbine blade; vibration fatigue; median fatigue limit; high temperature; aeroengine blade

Key words： aeroengine turbine blade vibration fatigue median fatigue limit high temperature aeroengine blade

收稿日期: 2021-10-21 出版日期: 2022-09-15

引用本文:

张部声1,2，秦秀云3，张呈波1,2，吴光耀3，潘容3. 高温下发动机涡轮叶片振动疲劳性能测试方法[J]. 振动与冲击, 2022, 41(17): 117-122.
ZHANG Busheng1,2, QIN Xiuyun3, ZHANG Chengbo1,2, WU Guangyao3, PAN Rong3. Testing method for vibration fatigue performance of engine turbine blades at high temperature. JOURNAL OF VIBRATION AND SHOCK, 2022, 41(17): 117-122.

链接本文:

http://jvs.sjtu.edu.cn/CN/ 或 http://jvs.sjtu.edu.cn/CN/Y2022/V41/I17/117

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