Patent ID: 8459942
Filing Date: 2013-06-11
Classification: F01D,Y02T

Abstract:
1. A gas turbine engine component comprising at least one ring element, a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element, wherein the load carrying vanes have an internal structure with an anisotropic load carrying property, and wherein the internal structure is configured so that a main load carrying direction is in parallel with an extension direction of a load carrying vane of the load carrying vanes, and a stiffening structure having an internal structure with an isotropic load carrying property and comprising a plurality of interconnected brackets, each bracket bridging a distance between at least two adjacent ones of the load carrying vanes in a circumferential direction of the ring element, and the at least two adjacent load carrying vanes being attached to attachment portions of the bracket by bolts, the attachment portions being spaced in the circumferential direction and each attachment portion extending in the radial direction.