航空发动机高压转子“可容模态”设计及实验验证

Workable Mode Design and Experimental Verification of Aero-Engine High Pressure Rotor

关键词:  航空发动机  高压转子  “可容模态”设计  实验验证  转子动力学

Key words:  Aero-engine  High pressure rotor  Workable mode design  Experimental verification  Rotor dynamics

摘要:

为降低航空发动机高压转子的振动，提高高压转子对复杂工况的可容度，本文建立带双阻尼器的高压转子动力学模型，开展模态分析和响应分析，研究高压转子关键结构参数对“可容模态”的影响规律。构造了可容度评价函数η，建立了“可容模态”设计方法。设计了高压转子模拟实验器，通过模态校核实验验证了计算模型和计算方法的准确性，通过“可容模态”实验验证了设计方法的可行性。研究发现，利用当量临界转速ωˉ估计转子系统前两阶临界转速的方法可行，高压转子实验器的临界转速满足ωcr1≤ωˉ，ωˉ≤ωcr2≤2ωˉ；高压转子实验器在两阶“可容模态”下连续“共振”时长达到7125s，实验器转子关键部位的振动位移峰值不超过79.42μm，振动速度有效值不超过2.33mm/s，最大波动不超过10.59%。结果表明，所建立的发动机高压转子“可容模态”设计方法是行之有效的。

Abstract:

In order to reduce the vibration of aero-engine high pressure rotor， and improve the tolerability to complex working conditions， a dynamical model simulating high pressure rotor with two dampers was established， based on which modal and response analysis were carried out， and effect laws of key structural parameters on workable mode were studied. Tolerability evaluation function η was constructed， and workable mode design method was established. A test rig simulating high pressure rotor was designed. The accuracy of calculation model and method were verified by modal checking experiments， and the feasibility of design method was proved by workable mode experiments. According to research findings， method that using equivalent critical speed ωˉ to estimate the first two critical speeds of high pressure rotor system is feasible， with the critical speeds of test rig satisfying relational expression ωcr1≤ωˉ and ωˉ≤ωcr2≤2ωˉ. The continuous resonance time at the first two order workable modes of test rig are no less than 7125s. The peaks of vibration displacement at key positions are less than 79.42μm， and effective values of vibration velocity are less than 2.33mm/s， with the relative fluctuations less than 10.59%. The results indicate that the workable mode design method of aero-engine high pressure rotor established is effective.