Abstract: For the design of modern gas turbine, cooling sources such as middle passage gap leakage flow, upstream slot leakage flow, and discrete film holes are designed to protect the blade. This research included middle passage ...

Abstract: Due to the complex flow field and the considerable heat load on the turbine blade tip, film cooling is essential to protect the tip from being overheated. In this paper, an experimental work was conducted to compare the ...

Abstract: A comprehensive understanding of the tip heat transfer characteristics is important to the blade tip design. In this work, the heat transfer coefficient (h) data of several multicavity tips was measured using a steady-state ...