航空发动机

娄金伟，安中彦，高涵宇，刘海.基于叶尖定时技术的非接触式叶片叶尖扭转角测试及应用[J].航空发动机,2024,50(1):159-163

基于叶尖定时技术的非接触式叶片叶尖扭转角测试及应用

Application of Non-contact Blade Tip Twist Angle Measurement Technique Based on Tip-Timing

DOI：

英文关键词:blade twist blade tip-timing rotor blade non-contact measurement aeroengine

基金项目:航空动力基础研究项目资助

作者	单位
娄金伟，安中彦，高涵宇，刘海	中国航发沈阳发动机研究所，沈阳 110015

摘要点击次数: 283

全文下载次数: 214

中文摘要:

为了验证风扇转子叶片反扭设计的准确性及获取不同气动状态、不同转速条件下叶片扭转变形情况，建立叶片扭转应用理论模型，开发了基于叶尖定时技术的非接触式叶片叶尖扭转角测试技术，在发动机风扇转子叶片上开展了旋转状态下的叶片叶尖扭转角测试和仿真计算。结果表明：叶片叶尖扭转角变形理论计算值为1.5°，实测值为1.4°；采用统计分析方法计算稳态转速风扇转子叶片所有叶片叶尖扭转角最大标准偏差为0.1°，是因加工误差、装配误差、气流扰动和振动因素导致的；单个叶片叶尖扭转角最大标准偏差为0.01°，是因气流扰动和振动因素影响所导致的。该项测试技术成功地验证了叶型反扭设计，稳态转速风扇转子单个叶片叶尖扭转角小于所有叶片叶尖扭转角的离散度。

英文摘要:

In order to verify the accuracy of the blade reverse-twist design of a fan rotor and obtain the blade twist deformation under different aerodynamic conditions and different rotational speeds， a theoretical model for blade twist was established and a non-contact blade tip twist angle measurement technique based on blade tip-timing was developed. Measurement and simulation of the blade tip twist angle of the aeroengine fan rotor under rotating conditions were carried out. The results show that the theoretical twist angle of the blade tip is 1.5°， and the measured twist angle of the blade tip is 1.4°. Through statistical analysis， the maximum standard deviation of the all-blade tip twist angles under steady rotational speeds is 0.1°， which is caused by machining errors， assembly errors， airflow disturbance， and vibration； while the maximum standard deviation of the single-blade twist angles is 0.01°， which is influenced by airflow disturbance and vibration. The measurement technique successfully verified the blade reverse-twist design. The dispersion of the fan rotor single-blade tip twist angles at steady rotational speeds is less than that of the all-blade.

查看全文查看/发表评论下载PDF阅读器