Patent ID: 6851924
Filing Date: 2005-02-08
Classification: F01D,F05D

Abstract:
1. A vane segment assembly member for a gas turbine engine comprising: a body portion having a first end region spaced apart from a second end region by a mid region extending therebetween, each of said end regions including a transition zone and a blending zone, said transition zones each being characterized by a first outer contour, and said blending zones each being characterized by a second outer contour; a first shroud portion adjacent said first end region; a second shroud portion adjacent said second end region; a cooling chamber disposed within said body portion, said cooling chamber including a cooling channel entrance adapted for fluid communication with a source of cooling fluid, said chamber being characterized by a first cooling channel having a first number of cooling exits in fluid communication with said first and region and a second cooling channel having a second number of cooling exits in fluid communication with said mid region, wherein the total volume circumscribed by said first number of exits is substantially-equal the total volume circumscribed by said second number of exits, wherein said transition zone and said blending zone cooperatively form a region adapted to facilitate transfer of heat at a rate effective to resist crack propagation within said body portion without storing heat and wherein said cooling exits are adapted and arranged to cool said body portion without inducing local thermal gradients adjacent said shrouds.