摘要
针对部分进气涡轮盘所受气流力在周向分布的严重不均匀易造成动叶片疲劳破坏的问题,从部分进气气流力特征和叶片振动响应两个方面进行了研究。根据已有数值模拟和实验结果给出了部分进气模式下考虑Kick效应的叶片所受气流力的分布曲线,采用快速傅里叶变换方法(FFT)分析了气流力的频谱特征,研究了转速和进气度等因素对气流力的频域特性的影响;采用有限元方法对某火箭发动机部分进气涡轮盘进行了瞬态振动响应分析,对比气流力的频谱特征,研究了叶片振动响应的特性。结果表明:在部分进气模式下,高转速涡轮盘叶片所受气流激励可以视为脉冲激励,存在多阶谐波分量;高转速或小进气度都会使得气流力的高阶谐波分量的幅值较大,使得涡轮盘叶片发生高倍频的共振或幅值较大的强迫振动,区别于全周进气的涡轮盘只需避开前6倍频气流力可能引起的共振,部分进气时还需考虑更高倍频气流力的影响。
The characteristics of airflow force and blade vibration response at partial admission were studied to solve the problem that the severe uneven circumferential distribution of airflow force increases the risk of fatigue failure.According to the existing numerical simulation and experimental results,the airflow force distribution with Kick effect at partial admission was established,and the spectral characteristics of the airflow force were obtained by fast Fourier transform method.The influence of rotational speed and admission on the frequency domain characteristics of airflow force was studied.The transient vibration response of a partial-admission turbine disk of a rocket engine was analyzed by using finite element method,and the spectral characteristics of the vibration response were obtained.The results show that:In partial admission turbines,the airflow force on the turbine disc blade at high rotational speed can be regarded as pulse excitation,and multiorder harmonic components are observed.High rotational speed or small admission will make the amplitude of the high-order harmonic component of the airflow force larger,and cause high-frequency resonance or violent forced vibration of the turbine disc blades,which is different from the full admission turbine disk that only needs to avoid the possible resonance generated by the first six harmonic components of airflow force.As for partial admission,the influence of higher harmonic components should be taken into account.
作者
吴锦涛
王珺
徐自力
闫松
王振
WU Jintao;WANG Jun;XU Zili;YAN Song;WANG Zhen(State Key Laboratory for Strength and Vibration of Mechanical Structures, Xi’an Jiaotong University, Xi’an 710049, China;School of Aerospace Engineering, Xi’an Jiaotong University, Xi’an 710049, China;Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, Xi’an 710100, China)
出处
《西安交通大学学报》
EI
CAS
CSCD
北大核心
2022年第7期108-117,共10页
Journal of Xi'an Jiaotong University
基金
国家自然科学基金资助项目(51675406)
液体火箭发动机技术重点实验室基金资助项目(6142704190404)。
关键词
涡轮盘
部分进气
振动响应
高阶谐波
频谱特征
turbine disk
partial admission
vibration response
higher-order harmonics
spectral characteristic
