Diffusion chamber for gas turbine engine, combustion chamber and gas turbine engine comprising same

摘要

The fairing (26) has a tapered body i.e. annular disk portion, rotating around a fairing axis (260), and a screw and nut fixed on wall of a converging combustion chamber of a turbo jet engine. The body is extended between planes that are transversal to the fairing axis. Outer and inner edges of the fairing are respectively extended from outer and inner radial ends of the body. Flanged-edge holes (50) are arranged in the body.