Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber

摘要

The component has inner and outer combustion chamber walls (11, 12) shielded from an environment when a fuel flame extends along burner axes (21) during operation of the component. The combustion chamber walls comprise projections in a direction away from the burner axes. The fuel flame is arranged between the combustion chamber walls. The projections of the combustion chamber walls are adapted to a contour of the fuel flame during operation of the component. Length and/or width of the projections correspond to length and/or width of the fuel flame. Independent claims are also included for the following: (1) an annular combustion chamber (2) a method for manufacturing an annular combustion chamber.