Invention Grant
US07704047B2 Cooling of turbine blade suction tip rail 有权
涡轮机叶片抽吸导轨的冷却

Cooling of turbine blade suction tip rail
Abstract:
A turbine blade including an airfoil, the airfoil including an airfoil outer wall having pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges extending radially outwardly from a blade root to a blade tip surface. A continuous squealer tip rail extends radially outwardly from and substantially continuously around the blade tip surface forming a radially outwardly open squealer pocket. The squealer tip rail includes an aft portion adjacent to the trailing edge, where the pressure side tip rail is discontinued in the chordal location of the aft portion. A plurality of chordally spaced film cooling holes are provided in a surface of the suction sidewall and provides a cooling fluid flow along the aft portion of the squealer tip rail surface to define a sub-boundary layer or film of cooling fluid between a hot gas vortex flow and the aft portion of the squealer tip rail at the suction sidewall.
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