Patent ID: 8790073
Filing Date: 2014-07-29
Classification: F01D,F05D

Abstract:
1. A gas turbine engine, comprising: a stator vane for directing hot combustion gases onto a plurality of rotor blades; and a support and cooling arrangement, wherein the stator vane includes a platform disposed at a radial inner first side of the vane with respect to an axis of rotation of the engine, wherein the platform includes a trailing edge portion downstream with respect to a flow of the hot combustion gases past the stator vane, wherein the support and cooling arrangement directs a cooling fluid to an upstream end of a second side of the trailing edge portion of the platform, which second side facing radially inward with respect to the axis of rotation of the engine, wherein the support and cooling arrangement also directs the cooling fluid to flow over the second side in a generally axial direction to a downstream end of the second side, the cooling fluid cooling the trailing edge portion as it flows over the second side, and wherein a plurality of turbulators are included on the second side to increase heat transfer from the trailing edge portion as the cooling fluid flows over the second side, the plurality of turbulators extending so as to traverse the axial direction of the axis of rotation of the engine, and wherein the radially inwardly facing second side incorporates a plurality of axially extending wall partitions that divide the second side into a number of discrete axially extending cooling channels the plurality of turbulators included on the second side being located in the cooling channels.