Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Claude A Genet

Pierre A Bouillot

A method of manufacturing a cooling film device for the combustion chamber of a turbomachine is described in which a blank is machined to provide a substantially cylindrical upstream wall and an enlarged downstream part of generally frusto-conical shape, an inner recess open at the downstream end is machined in the downstream part to constitute an inner wing and an outer wing, the wings are machined and deformed to define a settling chamber which converges in the downstream direction to an annular outlet slit, and the radial upstream end wall of the settling chamber is drilled to provide a plurality of small air inlet holes.

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Vigneux, France

Claude A Genet