摘要
依据国军标GJB-241A要求开展了某型发动机高压涡轮盘破裂试验研究,按照平均应力法确定了轮盘考核对象,制定了试验参数,应力分析表明本次部件试验能够有效考核发动机状态下涡轮盘的承载能力。设计了高压涡轮盘模拟安装边,经有限元分析强度和刚度可靠,按照发动机状态温度场需求实现了试验器状态下涡轮盘温度场模拟。在分析试验结果基础上,完成了故障定位,为后续的工程试验改进提供依据。
According to the requirements of the national military standards,a HPT disk burst test was conducted on a certain type of engine.The assessment object of the disk was determined using the average stress method,and the test parameters were formulated.The stress analysis showed that the component test can effectively assess the bearing capacity of the turbine disk under aero-engine conditions.The simulated flange of HPT disk was designed.The strength and stiffness were reliable through finite element analysis,and the temperature field simulation of turbine disk under the condition of tester was realized according to the temperature field requirement of engine state.Based on the analysis of the experimental results,the fault location was completed,providing a basis for subsequent engineering test improvements.
作者
王丹
杨修铭
刘明坤
WANG Dan;Yang Xiu-ming;Liu Ming-kun(AECC Shenyang Engine Research Institute,Shenyang 110015)
出处
《航空精密制造技术》
2025年第4期42-46,共5页
Aviation Precision Manufacturing Technology
关键词
航空发动机
高压涡轮盘
破裂试验
断口分析
aero-engine
high pressure turbine disk
burst test
fracture analysis
作者简介
第一作者:王丹(1992-),女,硕士研究生,工程师。
