Patent ID: 8672612
Filing Date: 2014-03-18
Classification: F01D,F05D

Abstract:
1. A turbine vane, comprising: a radial outer platform; a radial inner platform; and an airfoil extending between the outer platform and the inner platform, wherein each platform includes a gas washed surface facing towards a respective other platform, a non gas washed surface facing opposite to the gas washed surface and away from the respective other platform, and a peripheral surface extending from the gas washed surface to the non gas washed surface, wherein each peripheral surface includes an upstream section that is designed to be directed towards a gas flow washing the gas washed surface, wherein a plurality of cooling fluid channels, each including an opening in the peripheral surface, are located in a first section of the outer platform and/or in a second section of the inner platform, the respective section directly adjoining the upstream section of the peripheral surface of the respective platform, and wherein the plurality of cooling fluid channels are a plurality of slots located in the non gas washed surface of the outer platform and/or in the non gas washed surface of the inner platform in a third section adjoining the upstream section of the peripheral surface of the respective platform, wherein the non gas washed surface of the inner and/or outer platform, on which the plurality of slots are formed, shows toward and contacts a cooling air supply chamber through which cooling air is supplied to the airfoil and said non gas washed surface, wherein the plurality of slots are in contact with the cooling air supply chamber.