航空发动机主轴滚子轴承非典型失效机理

郑金涛; 邓四二; 张文虎; 党晓勇

doi:10.7527/S1000-6893.2019.23347

航空学报 >

2020 , Vol. 41 >Issue 5: 423347 - 423347

DOI: https://doi.org/10.7527/S1000-6893.2019.23347

材料工程与机械制造

航空发动机主轴滚子轴承非典型失效机理

郑金涛 ,
邓四二 ,
张文虎 ,
党晓勇

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1. 河南科技大学机电工程学院, 洛阳 471003;
2. 河南科技大学高端轴承摩擦学技术与应用国家地方联合工程实验室, 洛阳 471003;
3. 辽宁重大装备协同创新中心, 大连 116024;
4. 北京动力机械研究所, 北京 100074

收稿日期: 2019-08-05

修回日期: 2019-08-31

网络出版日期: 2019-09-30

基金资助

国家自然科学基金青年科学基金（51905152）；河南省自然科学基金（162300410086）；河南省科技攻关计划（172102210254）

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Atypical failure mechanism of aero-engine main shaft roller bearing

ZHENG Jintao ,
DENG Sier ,
ZHANG Wenhu ,
DANG Xiaoyong

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1. School of Mechatronics Engineering, Henan University of Science and Technology, Luoyang 471003, China;
2. National United Engineering Laboratory for Advanced Bearing Tribology, Henan University of Science and Technology, Luoyang 471003, China;
3. Collaborative Innovation Center of Major Machine Manufacturing in Liaoning, Dalian 116024, China;
4. Beijing Power Machinery Institute, Beijing 100074, China

Received date: 2019-08-05

Revised date: 2019-08-31

Online published: 2019-09-30

Supported by

Young Scientists Fund of the National Natural Science Foundation of China (51905152); Natural Science Foundation of Henan Province (162300410086); Science and Technology Planning Project of Henan Province (172102210254)

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摘要

针对某航空发动机圆柱滚子轴承的非典型失效问题，基于滚动轴承动力学理论，考虑滚子动不平衡量及滚子与套圈挡边间的碰摩，建立高速圆柱滚子轴承的动力学微分方程组，采用预估-校正GSTIFF（Gear stiff）变步长积分算法进行求解，分析了轴承工况参数和结构参数对动不平衡滚子的最大歪斜角和滚子与挡边最大碰撞力的影响。结果表明：滚子最大歪斜角和滚子与挡边最大碰撞力大小随滚子动不平衡量、轴承内圈转速增加而增大，与径向载荷间未表现出明显的相关性；较小的轴向游隙能够有效抑制滚子歪斜，但会增大滚子与挡边碰撞力，存在合理的轴向游隙范围使得在滚子歪斜角不会过大的情况下滚子与挡边碰撞力较小；较小的保持架兜孔周向游隙与挡边负背角和较大的滚子球端面半径能够减小滚子最大歪斜角和滚子与挡边最大碰撞力。

关键词： 圆柱滚子轴承; 动力学; 动不平衡; 碰撞; 非典型失效

本文引用格式

郑金涛 , 邓四二 , 张文虎 , 党晓勇 . 航空发动机主轴滚子轴承非典型失效机理[J]. 航空学报, 2020 , 41(5) : 423347 -423347 . DOI: 10.7527/S1000-6893.2019.23347

Abstract

Based on the dynamic analysis of rolling bearings, this paper presents dynamics differential equations of high-speed cylindrical roller bearing, considering the roller dynamic unbalance and the collision and friction between the roller and the rib, aiming at the atypical failure of aero-engine cylindrical roller bearing.The problem is solved by the GSTIFF (Gear stiff) integer algorithm with variable step. And the influence of the bearing condition parameters and the structural parameters on the maximum skew angle of the dynamic unbalanced roller and maximum collision force between the roller and the rib are analyzed. The results show that the maximum skew angle of the roller and the maximum collision force between the roller and the rib increase with the roller dynamic unbalance and the inner ring rotation speed, showing no obvious correlation with the radial load. The smaller axial clearance can effectively suppress the roller skew, but it will increase the impact force between the roller and the rib. And a reasonable axial clearance range makes the collision force between the roller and the rib small when the roller skew angle is not excessive. The smaller cage pocket circumferential clearance and the rib negative back angle and the larger roller ball end face radius can reduce the maximum skew angle of the roller and the maximum collision force between the roller and the rib.

Key words： cylindrical roller bearing; dynamics; dynamic unbalance; collision; atypical failure

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