Patent ID: 8096746

Claim:
A vane assembly for a gas turbine engine, the vane assembly comprising an inner vane support and a vane ring, the vane ring including a plurality of airfoils radially extending between inner and outer vane platforms, the vane assembly being concentric with a longitudinal axis of the gas turbine engine, the vane ring having a plurality of lug members radially protruding therefrom, each lug member being disposed in radial sliding engagement with a corresponding recess of the vane support such as to at least partially support and position the vane ring in place within the gas turbine engine, and wherein a radial loading element is disposed between a remote end of each of the lug members and the vane support, the radial loading elements generating a radial load force against the vane ring such as to radially bias the vane ring relative to the vane support, thereby limiting relative radial movement between the vane ring and the vane support during operation of the gas turbine engine.