考虑棘轮效应的可重复使用火箭发动机涡轮盘损伤分析

孙羽键; 杜大华; 王珺; 李斌潮; 徐自力

doi:10.7652/xjtuxb202608021

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考虑棘轮效应的可重复使用火箭发动机涡轮盘损伤分析

更新时间：2026-07-28

- 考虑棘轮效应的可重复使用火箭发动机涡轮盘损伤分析
- Damage Analysis of a Reusable Rocket Engine Turbine Disk Considering the Ratcheting Effect
- 西安交通大学学报 2026年60卷第8期页码：240-248
- 作者机构：
  
  西安交通大学复杂服役环境重大装备结构强度与寿命全国重点实验室，710049，西安
  西安交通大学航天航空学院，710049，西安
  西安航天动力研究所液体火箭发动机技术重点实验室，710100，西安
- 作者简介：
  
  作者简介：孙羽键（1994-），女，博士生；
  徐自力（通信作者），男，教授，博士生导师。
- 基金信息：
- DOI：10.7652/xjtuxb202608021
  中图分类号： V434.211
- 收稿：2025-10-31，
  
  网络首发：2025-12-09，
  
  纸质出版：2026-08-10
- 稿件说明：
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孙羽键, 杜大华, 王珺, 等. 考虑棘轮效应的可重复使用火箭发动机涡轮盘损伤分析[J]. 西安交通大学学报, 2026,60(8):240-248.

SUN Yujian, DU Dahua, WANG Jun, et al. Damage Analysis of a Reusable Rocket Engine Turbine Disk Considering the Ratcheting Effect[J]. Journal of Xi'an Jiaotong University, 2026, 60(8): 240-248.
孙羽键, 杜大华, 王珺, 等. 考虑棘轮效应的可重复使用火箭发动机涡轮盘损伤分析[J]. 西安交通大学学报, 2026,60(8):240-248. DOI： 10.7652/xjtuxb202608021.

SUN Yujian, DU Dahua, WANG Jun, et al. Damage Analysis of a Reusable Rocket Engine Turbine Disk Considering the Ratcheting Effect[J]. Journal of Xi'an Jiaotong University, 2026, 60(8): 240-248. DOI： 10.7652/xjtuxb202608021.

摘要

针对可重复使用液体火箭发动机涡轮盘在多次启停工况下，由非对称循环应力引起塑性应变累积继而引发棘轮效应，从而严重影响结构寿命的问题，开展了涡轮盘在重复使用工况下的结构损伤分析。基于Chaboche随动强化模型，对涡轮盘在循环载荷下的力学响应进行表征，结合应力-应变演化规律系统分析了结构的棘轮行为。通过量化棘轮效应导致的损伤，结合线性累积损伤理论对结构损伤状态进行了评估。研究结果表明：多次启停工况中，涡轮盘出气侧叶型底部区域失效风险较高；棘轮损伤在初始循环周次最大，随后逐渐减小并趋于稳定；累积棘轮损伤在循环过程中呈非线性演化特征，损伤增量随着循环次数的增加逐渐减小；在10次循环中，随着棘轮应变增量减小，棘轮损伤的占比逐渐降低，疲劳损伤占比随循环次数逐渐提升至96%以上。该研究为可重复使用火箭发动机涡轮盘的结构损伤评估与寿命预测提供了理论分析基础。

Abstract

To address how the ratcheting effect—caused by cumulative plastic strain from asymmetric cyclic stresses under multiple start-stop cycles—seriously affects the structural life of reusable liquid rocket engine turbine disks

a structural damage analysis was conducted on turbine disks under reusable operating conditions. Based on the Chaboche kinematic hardening model

the mechanical response of the turbine disk under cyclic loading was characterized

and the ratcheting behavior of the structure was systematically analyzed in conjunction with the stressstrain evolution law. By quantifying the damage caused by the ratcheting effect

the structural damage state was assessed using the linear cumulative damage theory. The research results show that under multiple start-stop cycles

the trailing-edge blade root region is at a higher risk of failure. Ratcheting damage is greatest in the initial cycles and then gradually decreases before stabilizing. Cumulative ratcheting damage exhibits a nonlinear evolution with cycle number

as the damage increment gradually decreases over cycles. Over the 10 cycles considered

as the ratcheting strain increment decreases

the proportion of ratcheting damage gradually decreases

while the proportion of fatigue damage gradually increases to over 96% with cycle number. This study provides a theoretical basis for the structural damage assessment and life prediction of reusable rocket engine turbine disks.

关键词

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