Patent ID: 7179049

Claim:
A component for a gas turbine engine, the engine defining a primary gas path including at least two adjacent sections, a first of said sections channelling gases in a first general direction and a second of said sections channelling gases in a second general direction, the second section disposed downstream of the first, the first and second general directions different from one another, the component comprising a primary gas path defining surface having a plurality of spaced-apart airfoils extending therefrom, the surface being a circumferential portion of an annular surface of revolution, the surface defining a peripheral portion of said first section and generally aligned in the first general direction, the surface co-operating with at least a pair of said spaced-apart airfoils extending therefrom to define an aerodynamic throat therebetween, the surface including a lip portion entirely downstream of the throat, the lip portion generally aligned with the second general direction.