Combustion chamber for a turbine engine

摘要

A combustion chamber (110) for a turbine engine, such as an airplane turboprop or turbojet, the combustion chamber comprising two coaxial annular walls, respectively an inner wall and an outer wall, that are connected together at their upstream ends by a chamber end wall (118) having an annular row of openings (119) for mounting fuel injection devices (120), the combustion chamber being characterized in that an annular metal sheet (130) is mounted upstream from the end wall and includes mounting orifices for receiving the above-mentioned injection devices, the sheet being substantially parallel to the end wall and co-operating therewith to define an annular air flow cavity (140).

主权项

1. A combustion chamber for a turbine engine, the combustion chamber comprising two coaxial annular walls, respectively an inner wall and an outer wall, that are connected together at their upstream ends by a chamber end wall having an annular row of openings for mounting fuel injection devices, the combustion chamber further comprising an annular metal sheet having an upstream portion positioned upstream from the end wall and including mounting orifices for receiving the fuel injection devices, the upstream portion of the annular metal sheet being substantially parallel to the end wall, wherein said upstream portion and said end wall together define an annular air flow cavity, wherein said annular metal sheet also having an inner annular rim and an outer annular rim that bear radially respectively against an inner annular rim and against an outer annular rim of the end wall, said sheet being mounted with radial prestress between the inner annular rim and outer annular rim of the end wall.