主催: 一般社団法人 日本機械学会
会議名: 2020年度 年次大会
開催日: 2020/09/13 - 2020/09/16
The turbine inlet gas temperature has been rising with high efficiency and output power of the gas turbine engine. Turbine blade cooling is necessary to solve the problem of thermal fatigue. Film cooling technique is to protect the turbine blade surface with forming a protective film by cooling flow blown out from cooling holes discretely opened on the surface. It is important to improve film cooling efficiency by using a limited cooling flow rate. In this research, in order to develop high efficiency cooling hole shape, the cooling performance was evaluated by flow visualization, heat transfer experiment and PIV measurement. As a result, it was possible to confirm the high film cooling performance in the new original shape with tilted trailing edge.
