Abstract
Cooling of hot-section components of a gas turbine, such as combustor liners, combustor transition pieces (TP), and turbine vanes (nozzles) and blades (buckets), is a critical task as its effectiveness determines a turbine's lifespan and reliability. A model of a one-fourth cylinder is designed which could simulate the TP's structure and performance. Furthermore the paper presents the relationship between the angles of the hole, the orientations of the flow injection and the film-cooling effectiveness. Based on the heat-mass transfer analogy, the results of these experiments prove that the distribution of wall temperature and the effectiveness of cooling could be achieved through increasing inclination of coolant holes and coolant flow orientation. The series of experiments demonstrate that the angle of coolant holes and the angle of coolant flow are two of the most significant film-cooling parameters over a concave surface.
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