Patent ID: 7000406
Filing Date: 2006-02-21
Classification: F01D,F05D,F23R,Y02T

Abstract:
1. An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor, the vane assembly including at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween, wherein a portion of at least the outer platform mates with an adjacent outer combustor wall to form a first sliding joint connection therebetween such that both relative radial and axial displacement between the outer platform and the outer combustor wall is permitted, said first sliding joint defining a radial gap between facing surfaces of said portion of the outer platform and the outer combustor wall at a first temperature less than engine operating temperature, said facing surfaces being mutually disposed in radial sealing engagement at said engine operating temperature, wherein the inner platform forms a second sliding joint connection with an adjacent inner combustor wall, the second sliding joint connection permitting at least relative axial displacement between the inner platform and the inner combustor wall while maintaining a radial seal therebetween.