SLIDING JOINT BETWEEN COMBUSTOR WALL AND NOZZLE PLATFORM

摘要

An assembly for a gas turbine engine (10), the assembly comprising a combustor (16) and a vane assembly (22) downstream from the combustor (16). The vane assembly (22) includes at least one airfoil (24) radially extending between an inner and outer platform (26,28) defining an annular gas path (23) therebetween. At least the outer platform (28) forms a first sliding joint connection (36) with an adjacent outer combustor wall (32) such that radial sealing between the outer platform (28) and the outer combustor wall (32) is provided at engine operating temperature, while permitting relative axial displacement there between.