高压涡轮叶片缘板阻尼片阻尼效果试验研究

Experiment study on the damping effect of platform damper on high pressure turbine blade

根据试验需求搭建获取缘板阻尼片对叶片阻尼效果的试验系统。通过测量叶片模态阻尼和一弯振动应变最大点的应变响应曲线,获得了阻尼片与缘板之间的压紧力与阻尼效果之间的关系。试验结果表明,采用缘板阻尼结构是降低涡轮叶片振动应力的一种有效方法;叶片模态阻尼和一阶共振频率随阻尼片与缘板间压紧力的增加而增加;叶根位置振动应变随着压紧力的增加呈现出先降低再升高的趋势,最大降幅达69%。该试验研究结果对缘板阻尼片优化设计和高压涡轮叶片断裂故障分析具有重要的指导意义。

A test system had been built to measuring damping effect of platform damper on a real engine high pressure turbine blade(HPTB). Through measuring the blade mode damping and the strain response curve of first order bending vibration, a research had been studied about how the pressure between platform damper and platform affects the damping. The test results show that platform damper structure is an effective method to reduce vibration stress. The mode damping and first order frequency increase as the damper pressure increases. The vibration strain of the blade decreases and then increases as the damper pressure increases, which biggest drop was about 69 percent. The test results were instructive to platform damper optimization design and the fracture malfunction analysis of HPTB.