Patent ID: 7836702

Claim:
An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor, the vane assembly including a plurality of airfoils radially extending between annular inner and outer platforms defining an annular gas path therebetween, at least the outer platform forming a first sliding joint connection with an adjacent outer combustor wall such that relative axial displacement therebetween is permitted, a radial clearance gap being defined between the outer platform and the outer combustor wall, said radial clearance gap being minimized at engine operating temperature such that radial sealing between the outer platform and the outer combustor wall is substantially provided, and wherein the outer platform includes a plurality of radial depressions located in an outer circumferential surface thereof opposite said outer combustor wall, said radial depressions being solely disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the outer platform is substantially uniform circumferentially therearound and thus said minimized radial clearance gap is maintained during engine operation to prevent binding contact between the outer platform and the outer combustor wall, each depression providing a reduced thickness of the outer platform over the entirety of the surface of an associated one of the regions of expected higher thermal growth.