DZ125带小孔构件低循环/保载疲劳试验与分析

周天朋; 杨晓光; 候贵仓; 石多奇; 丛佩红

DZ125带小孔构件低循环/保载疲劳试验与分析

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2.
中国航空工业第一集团公司沈阳发动机设计研究所, 沈阳 110015

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出版历程
- 收稿日期: 2006-09-07
- 修回日期: 2006-12-13
- 刊出日期: 2007-09-28

Experimental analysis of low-cycle and creep fatigue for directionally solidified DZ125 with a hole

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Shenyang Aeroengine Research Institute, China Aviation Industry Corporation I, Shenyang 110015, China

摘要

摘要: 进行了定向结晶合金DZ125带小孔构件在高温下的低循环/保载疲劳试验.此构件试验用来部分模拟航空发动机气膜冷却的空心涡轮转子叶片, 试验方案根据空心涡轮转子叶片的几何特征和所承受的温度及载荷状况来设计.介绍了试验方案和试验结果分析, 包括寿命分析、试验裂纹扩展规律分析和金相分析.结果表明小孔应力集中和保载是构件破坏的主要原因, 孔边电火花加工特征对裂纹萌生起到决定性影响.
- 航空、航天推进系统 /
- DZ125 /
- 定向结晶 /
- 疲劳 /
- 蠕变 /
- 寿命
Abstract: A low-cycle/creep fatigue test was conducted for directionally solidified DZ125 component with a hole under high temperature conditions.The purpose of this test was to simulate hollow turbine rotor blade for film cooling of aeroengine.The test scheme was planned according to geometric characteristics,temperature and load conditions of hollow turbine rotor blade.The test scheme and test results were described,covering ser-vice life analysis,crack expansion analysis and metallographic analysis.The results show that holes' stress con-centration and creep are major contributing factor to the damage of components,and electric discharge machine(EDM) hole features is decisive to the crack initiation.
- aerospace propulsion system /
- DZ125 /
- directionally solidified /
- fatigue /
- creep /
- life

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参考文献(9)

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