文献类型：会议论文

英文题名：Film cooling performance on the trailing edge cutback of turbine blade with various slot inner angles

作者：Chen, Mingfeng[1]; Ling, Changming[1]; Zhang, Yuwen[2]

机构：[1] College of Mechanical and Power Engineering, Guangdong Ocean University, No.40 East Jiefang Road, Zhanjiang, Guangdong, 524025, China; [2] Department of Mechanical and Aerospace Engineering, University of Missouri, E2412A Lafferre Hall, Columbia, MO, 65211, United States

会议论文集：Proceedings of the 10th International Conference on Computer Modeling and Simulation, ICCMS 2018

会议日期：January 8, 2018 - January 10, 2018

会议地点：Sydney, NSW, Australia

语种：英文

外文关键词：Numerical methods - Numerical models - Turbine components - Thermal insulation - Film cooling

外文摘要：In order to study the impact of the slot inner angle on the film cooling performance of the trailing edge cutback for turbine blade, physical model and the three-dimensional mathematical model were established. The temperature distribution on the pressure side close to the wall was obtained through numerical simulation method, and the adiabatic temperature difference ratio and actual temperature difference ratio on the trailing edge cutback with various slot inner angles were analyzed. The results showed that, as slot inner angle increases, the average adiabatic temperature difference ratio on the trailing edge cutback and the effect of thermal insulation of gas film are increased. The impact of actual temperature difference ratio on the trailing edge cutback suffers slot inner angle is small, and it is conducive to lower the wall temperature of trailing edge when reduces the slot inner angle. For the study of film cooling performance on the trailing edge cutback of turbine blade, in addition to evaluate the adiabatic temperature difference ratio, it should also assess the actual temperature difference ratio. ? 2018 Association for Computing Machinery.