A GAS TURBINE ENGINE COMPONENT, A TURBOJET ENGINE PROVIDED THEREWITH, AND AN AIRCRAFT PROVIDED THEREWITH

摘要

A gas turbine engine component comprising - at least one ring element (114), and - a plurality of circumferentially spaced load carrying vanes (112) extending in a radial direction of the ring element (114), wherein the load carrying vanes (12) 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 the extension direction of the load carrying vane (12), characterized in that the component comprises - a stiffening structure (117) bridging the distance between at least two adjacent load carrying vanes (12) in the circumferential direction of the ring element (114), and that said at least two adjacent load carrying vanes (12) are attached to the stiffening structure (117).