基于三维激光扫描的涡轮叶片高温模态测试技术

代江波; 罗现强; 符顺国; 王琦; 冯海波

doi:10.13224/j.cnki.jasp.2021.05.002

基于三维激光扫描的涡轮叶片高温模态测试技术

doi: 10.13224/j.cnki.jasp.2021.05.002

中国航空发动机集团有限公司四川燃气涡轮研究院,四川绵阳 621000

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出版历程
- 收稿日期: 2020-08-08
- 刊出日期: 2021-05-28

Hot-modal test technology of turbine blades based on 3D laser scanning

Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China

摘要

摘要: 提出了基于三维激光扫描技术的发动机涡轮叶片高温模态测试技术,实现了在最高900 ℃的高温环境下的涡轮叶片模态测试。设计了一套高温环境模拟装置,实现了不同温度环境的模拟,基于振动台基础激励技术和三维激光扫描技术,建立了不同温度环境下的涡轮叶片三维测试模型,获取了准确的模态振型、模态频率等参数,验证了方法的可行性。分析结果显示:温度升高会导致涡轮叶片固有频率下降,900 ℃较常温环境1阶频率下降约6%,叶尖振型因热应力产生轻微畸变。
- 高温模态 /
- 三维激光扫描 /
- 模态振型 /
- 模态频率 /
- 涡轮叶片
Abstract: The high temperature modal test technology of engine turbine blades based on 3D laser scanning technology was presented, which realized the modal test of turbine blades at high temperature of up to 900 ℃. A set of high temperature environment simulation device was designed to realize the simulation of different temperature environments. Based on the basic excitation technology of the shaking table and 3D laser scanning technology, the 3D test models of turbine blades under different temperature environments were established, the accurate modal shape, modal frequency and other parameters were obtained, by which the feasibility of the method was verified. The analysis results showed that the natural frequency of turbine blades decreased due to the increase of temperature, and the first-order frequency decreased by 6% compared with the ambient temperature at 900 ℃, The modal shape of blade tip was slightly distorted due to thermal stress.
- hot-modal /
- 3D laser scanning /
- modal shape /
- modal frequencies /
- turbine blades

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