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基于英军标Defence Standard 00971对盘类零件的安全性要求,采用安全寿命法对某型发动机高压涡轮盘的低循环疲劳寿命试验进行了研究.通过有限元法对发动机工作条件下的高压涡轮盘进行了应力分析,考虑了温度场对应力分布的影响,按照Defence Standard 00971的要求确定了高压涡轮盘的关键部位及其标准循环,制定了高压涡轮盘低循环疲劳寿命试验方案,给出了基于试验结果确定高压涡轮盘安全寿命的方法.分析表明:中心孔和螺栓孔的应力系数分别为1.0和1.017,均在合理范围内;提高高压涡轮盘转速同时截短涡轮叶片的试验方法能有效模拟热应力对寿命的影响,对高压涡轮盘低循环疲劳寿命试验具有重要指导意义.
Based on the requirements of British Standard Standard 00971 for the safety of disk-type components, a safety-life method was used to study the low-cycle fatigue life of a high-pressure turbine disk of a certain type of engine.According to the finite element method, The stress analysis was taken into account and the influence of temperature field on the stress distribution was considered. According to the requirements of Defense Standard 00971, the key parts of high-pressure turbine disk and its standard circulation were determined and the low-cycle fatigue life test program of high pressure turbine disk was established. The results show that the stress coefficients of center hole and bolt hole are 1.0 and 1.017, respectively, which are within a reasonable range. The test method of increasing turbine speed while cutting turbine blades can effectively simulate The influence of thermal stress on the life of the high pressure turbine disk low cycle fatigue life test has important guiding significance.