| 发动机静子尾流激励对叶盘结构高阶共振可激性的研究 |
| |
| 引用本文： | 李琳,郭雅妮. 发动机静子尾流激励对叶盘结构高阶共振可激性的研究[J]. 航空动力学报, 2017, 32(4): 780-790. DOI: 10.13224/j.cnki.jasp.2017.04.002 |
| |
| 作者姓名： | 李琳 郭雅妮 |
| |
| 作者单位： | 北京航空航天大学 能源与动力工程学院，北京 100191 |
| |
| 摘 要： | 针对航空发动机中转静干涉流场诱发的叶盘结构强迫响应问题，分析由导流叶片和动叶构成的转静干涉流场的尾流激励所激起的叶盘结构高阶共振的可能性和危险性.基于非定常转静干涉流场数值模拟结果，通过时域与空间傅里叶分析得到叶盘所受气动压力的频谱和空间波谱，同时定义投影于叶盘结构模态空间的激励（即模态力）为尾流激励的可激性，用于对叶盘结构共振响应强度的评估.研究结果表明:尾流激励对非主要共振点的可激性远远小于其对主要共振点的可激性；在发动机工作转速范围内允许那些模态位移场与激振力场的夹角较大（余角较小）的共振存在，即尾流激励可激性很小的高阶共振的存在是合理的.
|
| 关 键 词： | 尾流激励 叶盘结构 高阶共振 模态力 可激性 |
| 收稿时间： | 2015-09-06 |
Research on excitability of the wake of stator in aero-engine to high order resonance of bladed-disk |
| |
| LI Lin,GUO Ya-ni. Research on excitability of the wake of stator in aero-engine to high order resonance of bladed-disk[J]. Journal of Aerospace Power, 2017, 32(4): 780-790. DOI: 10.13224/j.cnki.jasp.2017.04.002 |
| |
| Authors: | LI Lin GUO Ya-ni |
| |
| Abstract: | Targeting the forced vibration of bladed-disk in aero-engine, the impact of the severity of resonances induced by flow-wake of stator was studied. On the basis of the numerical simulation of unsteady stator-rotor interface flow, both frequency spectrum and spatial spectrum of aerodynamic pressure on the rotor surface were obtained respectively by fast Fourier transformation. Meanwhile, the excitability of wake was defined as the projection of aerodynamic pressure on the modal space, also called modal force, so as to evaluate the strength of resonant response of bladed disk. The analysis shows that the excitability of wake to a non-primary resonance is much less than a primary resonance. As a result, it is reasonable that in the operating speed region of aero-engine, the existence of high-order resonances with small complementary angle between aerodynamic force and modal displacement of bladed disk (small excitability), should be accepted. |
| |
| Keywords: | wake-excitation bladed-disk high-order resonance modal force excitability |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
