Patent ID: 8511099

Claim:
A combustor system for a gas turbine engine, the combustor system including: an annular combustion chamber having a forward end receiving at least one fuel injector and a rearward end adjacent a turbine, outer and inner casings housing the combustion chamber, the outer casing being outwardly radially spaced from the combustion chamber and the inner casing being inwardly radially spaced from the combustion chamber, and an attachment arrangement at the rearward end of the combustion chamber for attaching the combustion chamber to the engine, the attachment arrangement axially restraining the rearward end of the combustion chamber from movement relative to the casings; wherein the combustor system further includes a first stop surface formed at the forward end of the combustion chamber adjacent a selected one of the outer and inner casings, and a corresponding first baulking surface axially forward of the first stop surface formed by the selected casing, the first stop surface and the first baulking surface being spaced from each other to allow forward axial movement of the combustion chamber relative to the selected casing, the amount of relative forward axial movement being limited by engagement of the first stop surface with the first baulking surface.