Casing for e.g. turbojet engine, of aircraft, has annular combustion chamber delimited by internal and external platforms that are made of metal and formed from single piece with walls of chamber, where platforms are welded onto walls

摘要

The casing (30) has an annular combustion chamber (10) delimited by metallic annular walls e.g. internal and external revolution walls (12, 14) and a high-pressure turbine dispenser (20) including annular internal and external platforms (22, 24) secured to a downstream end of the walls. The platforms are made of metal and are formed from a single piece with the walls. The platforms are welded onto the walls of the combustion chamber. The dispenser has a set of guide blades (26) extending radially between the platforms, where the blades are spaced circumferentially with respect to each other.