Gas turbine blade with cooled platform

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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F01D 5/18 (2006.01)

Patent

CA 2198225

A turbine blade (18) has a cooling air flow path specifically directed toward cooling the platform portion (46) of the blade root (44). Two cooling air passages (48, 49) are formed in the blade root platform just below its upper surface. Each passage (48, 49) extends radially outward fron an inlet that receives a flow of cooling air (32) and then extends axially along almost the entire length of the platform (46). Each passage (48, 49) also has an outlet (52, 53) formed in the downstream face (61) of the platform (46) that allows the cooling air (32) to exit the platform (46) and enter the hot gas flow path. The passages (48, 49) are formed in portions of the platform (46) that overhang the shank portion of root.

Ailette (18) de turbine dont les conduits de refroidissement par air sont spécifiquement orientés pour refroidir la partie de plate-forme (46) de l'embase (44) dans laquelle sont formés deux passages (48, 49) d'air de refroidissement, juste sous sa surface supérieure. Chaque passage (48, 49) s'étend radialement vers l'extérieur depuis une arrivée d'air de refroidissement (32), puis axialement sur la quasi totalité de la longueur de la partie de plate-forme (46). Chaque passage (48, 49) présente également une sortie (52, 53) pratiquée dans la face aval (61) de la partie de plate-forme (46) pour permettre à l'air de refroidissement (32) de sortir de ladite plate-forme (46) et de passer dans la voie d'écoulement de gaz chauds. Les passages (48, 49) sont pratiqués dans des parties de la plate-forme (46) qui surplombent la portion en forme de tige de l'embase.

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