Patent ID: 8376705
Filing Date: 2013-02-19
Classification: F01D,F05D

Abstract:
1. A component in a gas turbine engine comprising: an airfoil extending radially outwardly from an endwall associated with said airfoil, said endwall extending between an upstream edge and a downstream edge and defining a cool side and a gas side; a recess cavity defined in an overhang portion extending from a location adjacent to said downstream edge toward said upstream edge, said recess cavity extending radially into said overhang portion from said cool side toward said gas side and defining a cavity surface located a first distance into said endwall from a peripheral radially inner surface of said endwall; a plurality of grooves extending radially into said cavity surface and having an elongated dimension extending in a direction from said downstream edge toward said upstream edge, said grooves including a groove bottom surface located a second distance radially into said endwall greater than said first distance; and cooling passages extending through said overhang portion and located: