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

Jean-Claude Laugeois

Michel A Desaulty

Gerard M Mandet

Rodolphe Martinez

Patrice A Commaret

Didier H Hernandez

The combustion chamber according to the present invention utilizes a double-walled structure only in the converging portion of the combustion chamber. A hot wall is retained adjacent to, but spaced from a corresponding cold wall so as to provide a cooling space between them. An upstream portion of the hot wall is retained in a notch defined by the cold wall, while the downstream portions each have generally radially extending flanges. Studs pass through openings in the adjacent flanges to prevent any relative circumferential movement, while a clamp serves to attach the flanges to the inlet of a turbine. The clamp slidably retains the flanges therein so as to permit relative radial movement to accommodate any thermal expansion and contraction of the combustion chamber, solely by the appended claims.

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Palaiseau, France

Jean-Claude Laugeois