Patent ID: 8479524

Claim:
A combustion chamber arrangement for a gas turbine comprising: a combustion chamber wall, which encloses a combustion chamber space for hot gases which develop inside the combustion chamber; the combustion chamber wall having an aft combustion chamber which freely terminates in an axial flow direction of the hot gases, the combustion chamber wall axially overlapping and radially spaced within a hot gas housing with a radial clearance between the combustion chamber wall and the hot gas housing; an annular seal, wherein the combustion chamber wall is completely encompassed in the circumferential direction by the annular seal which comprises a plurality of individual sealing segments which on an end face side are joined to each other in each case via connecting structures, on one side axially indirectly or directly adjoining the hot gas housing and with the outer-side combustion chamber wall delimited by axially oriented flow passages which on one side lead into an annular spatial area radially delimited by the axially mutually overlapping combustion chamber wall and hot gas housing; a plurality of collar-like fasteners indirectly or directly attached to the hot gas housing, the collar-like fasteners projecting upstream over the hot gas housing, arranged in a distributed manner in the circumferential direction of the hot gas housing, and attached to the annular seal on an outer side on the combustion chamber wall upstream to the aft combustion chamber wall edge; and the aft combustion chamber wall edge formed with a profile which blocks or at least inhibits the hot gases in the combustion chamber space from flowing radially outward into the annular spatial area, the profiling of the combustion chamber wall edge is a bevel with a bevel surface which faces the hot gas housing, the bevel angled at an angle α, where α=40°±10°.