Patent ID: 8156744

Claim:
A gas turbine engine annular combustion chamber comprising: an outer wall; an inner wall; a chamber-bottom wall connecting the outer wall and the inner wall such that the outer, inner and chamber-bottom walls delimit sources of combustion with axes inclined relative to an axis of the chamber, the chamber-bottom wall, of frustoconical shape, being pierced with orifices for the fuel injection systems, planes of the orifices being perpendicular to the axes of said sources of combustion; and heat-protection baffles centered on each of the orifices comprising a flat shoulder which rest against a flat surface portion of the chamber-bottom wall along a periphery of the orifices, wherein the chamber-bottom wall includes a succession of adjacent flat facets surrounding each of the orifices, each of the flat facets including a radially inner side, a radially outer side, and two rectilinear sides connecting the radially inner side and the radially outer side, the rectilinear sides being continuous with and common to two adjacent facets, are formed of a bended sheet of metal, and are oriented in a radial direction passing through an axis of the engine, and wherein the adjacent flat facets form a V-shape with an apex extending in a downstream direction with respect to gas flow such that the shoulder of the baffles rests against downstream sides of the facets.