Patent ID: 7287383

Claim:
A burner ring for a turbofan jet engine, said engine producing both a flow of bypass air and a core flow, said ring having an axis of revolution coinciding with an axis of rotation of the engine, and said ring comprising a plurality of sectors connected together and each sector comprising: an upstream annular envelope sector comprising: a first channel which opens axially in a downstream direction; an upstream surface configured to contact said core flow; and a bypass air inlet to deliver said flow of bypass air through an orifice of said upstream annular envelope sector; a fuel injection manifold arranged in said first channel, said fuel injection manifold being fitted to a fuel inlet; a ventilation duct which extends along said first channel for at least part of a length of said upstream annular envelope sector, said ventilation duct being positioned upstream of said fuel injection manifold, said ventilation duct being configured to emit said flow of bypass air to cool said fuel injection manifold; a first connecting end-piece arranged in said first channel upstream of said fuel injection manifold to receive both said fuel inlet and said ventilation duct; and a downstream annular envelope sector arranged downstream of the fuel injection manifold to protect said fuel injection manifold.