Patent ID: 7293957
Filing Date: 2007-11-13
Classification: F01D,F05D

Abstract:
1. A vane assembly for a gas turbine engine having reduced resistance to thermal deflections, the vane assembly comprising: a first arc-shaped platform having a first thickness, a forward wall, an aft wall, and a first rail extending generally circumferentially along the first arc-shaped platform and located axially between the forward wall and the aft wall, the first rail having a first rail length, a first rail height, a first rail thickness, and a first rail wall; a second arc-shaped platform positioned radially outward of the first arc-shaped platform and having at least one second rail extending generally circumferentially along the second arc-shaped platform, the at least one second rail having a second rail length longer than the first rail length; at least one airfoil extending from the first arc-shaped platform, opposite the first rail, radially outward to the second arc-shaped platform; and at least one substantially cylindrical opening extending through the first rail thickness, the opening having a slot initiating at the first rail wall and extending radially outward to the opening, and wherein the opening is positioned circumferentially along the first rail such that the opening is located radially beneath the at least one airfoil.