The cyclic stress produced by rapidly alternate heating and cooling and strong noise on the combustion chamber of aero-engineer will seriously affect its fatigue performance. In order to explore the influence of the load on the first-order thermal modal frequencies and fatigue resistance, the high temperature and strongly acoustic excitation response test and fatigue test for Haynes alloy 188 thin-walled structure with the rapidly alternate heating and cooling were firstly carried out for various work conditions. Based on the coupled finite element and boundary element methods to calculate the dynamic response, the comparison is discussed about the modal frequencies and strain values between the simulation and test. A fatigue life model included the improved rain flow counting method and miner linear damage accumulation theory was proposed to predict the fatigue life of the thin-walled structure. The prediction results are verified by comparing the fatigue damage and fatigue life with the tests. The simulation reveals that in higher temperature the nonlinear response of the structure is expanded significantly, and the rapidly alternate heating and cooling load aggravates the vibration behavior, reducing the fatigue life and making the valley position of the fatigue life shift to the right in the heating process.

快速交替的加热和冷却产生的循环应力以及航空发动机燃烧室上的强烈噪音将严重影响其疲劳性能。为了探索载荷对一阶热模态频率和抗疲劳性的影响，首先对快速交替加热和冷却的Haynes 188薄壁结构进行了高温和强声激发响应测试以及疲劳测试。针对各种工作条件进行。基于有限元和边界元耦合方法计算动力响应，讨论了模拟与试验之间的模态频率和应变值的比较。疲劳寿命模型包括改进的雨流计算方法和矿工线性损伤累积理论，以预测薄壁结构的疲劳寿命。通过将疲劳损伤和疲劳寿命与试验进行比较，验证了预测结果。仿真表明，在较高的温度下，结构的非线性响应会显着扩展，快速交替的加热和冷却负荷会加剧振动行为，缩短疲劳寿命，并使疲劳寿命的谷值位置在加热时向右移动过程。