TURBINE ROTOR BLADE PLATFORM COOLING
A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
04.07.2013
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Subjects | |
Online Access | Get full text |
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Summary: | A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a suction side of the platform comprises a topside extending circumferentially from the airfoil to a suction side slashface, and wherein the suction side of the platform comprises an aft edge. The platform cooling arrangement may include: a manifold positioned within an aft side of the suction side of the platform; a high-pressure connector that connects the manifold to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the manifold to the low-pressure coolant region of the interior cooling passage; and heat transfer structure positioned within the manifold. |
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Bibliography: | Application Number: US201113341027 |