The fatigue life of turbine housing is an important index to measure the reliability of a radial turbocharger. The increase in turbine inlet temperatures in the last few years has resulted in a decrease in the fatigue life of turbine housing. A simulation method and experimental verification are required to predict the life of a turbine housing in the early design and development process precisely. The temperature field distribution of the turbine housing is calculated using the steady-state bidirectional coupled conjugate heat transfer method. Next, the temperature field results are considered as the boundary for calculating the turbine housing temperature and thermomechanical strain, and then, the thermomechanical strain of the turbine housing is determined. Infrared and digital image correlations are used to measure the turbine housing surface temperature and total thermomechanical strain. Compared to the numerical solution, the maximum temperature RMS (Root Mean Square) error of the monitoring point in the monitoring area is only 3.5%; the maximum strain RMS error reached 11%. Experimental results of temperature field test and strain measurement test show that the testing temperature and total strain results are approximately equal to the solution of the numerical simulation. Based on the comparison between the numerical calculation and experimental results, the numerical simulation and test results were found to be in good agreement. The experimental and simulation results of this method can be used as the temperature and strain (stress) boundaries for subsequent thermomechanical fatigue (TMF) simulation analysis of the turbine housing.

涡轮壳体的疲劳寿命是衡量径向涡轮增压器可靠性的重要指标。过去几年涡轮进口温度的升高导致涡轮壳体的疲劳寿命下降。在早期的设计和开发过程中，需要一种模拟方法和实验验证来精确预测涡轮机壳体的寿命。采用稳态双向耦合共轭传热法计算涡轮机壳体的温度场分布。接下来，将温度场结果作为计算涡轮壳体温度和热机械应变的边界，然后确定涡轮壳体的热机械应变。红外和数字图像相关性用于测量涡轮机外壳表面温度和总热机械应变。与数值解相比，监测区域内监测点的最大温度RMS（均方根）误差仅为3.5%；最大应变均方根误差达到 11%。温度场试验和应变测量试验结果表明，试验温度和总应变结果与数值模拟解近似相等。通过数值计算与试验结果的对比，发现数值模拟与试验结果吻合较好。