Patent ID: 8777568
Filing Date: 2014-07-15
Classification: F01D,F05D,Y02T,Y10T

Abstract:
1. 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 that extends from a connection with a coolant source at the root to at least the approximate radial height of the platform, wherein, in operation, the interior cooling passage comprises at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside along an inboard surface, the platform cooling arrangement comprising: a plate that comprises a plate topside, the plate topside being detachably connected to the platform underside, a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.