US 4,901,522 AGranted

Turbojet engine combustion chamber with a double wall converging zone

AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."

InventorsPatrice Commaret, Michel A. A. Desaulty, Didier H. Hernandez, Jean-Claude Laugeois, Gerard M. F. Mandet, Rodolphe Martinez

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Abstract

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.

In a turbojet engine having a turbine section, the improved annular combustion chamber having a combustion zone, a dilution zone and convergent zone comprising:

(a) a single thickness first outer annular wall defining a radially outer boundary of the combustion zone and the dilution zone;
(b) a single thickness first inner annular wall defining a radially inner boundary of the combustion zone and the dilution zone;
(c) a double thickness, second outer annular wall defining a radially outer boundary of the convergent zone and connected to the single thickness outer annular wall comprising:
(i) a first cold wall having a first flange extending radially from a downstream edge;
and,
(ii) a first hot wall disposed adjacent to but spaced radially inwardly of the first cold wall, and having a second flange extending radially from a downstream edge;
(d) first attaching means to attach the first and second flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section;
(e) a double thickness second inner annular wall defining a radially inner boundary of the convergent zone and connected to the single thickness inner annular wall comprising:
(i) a second cold wall having a third flange extending radially from a downstream edge;
and,
(ii) a second hot wall disposed adjacent to but spaced radially outwardly of the second cold wall, and having a fourth flange extending radially from a downstream edge;
(f) second attaching means to attach the third and fourth flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section;
(g) a plurality of bores defined by the first, second, third and fourth flanges;
and,
(h) a plurality of generally cylindrical studs extending into the bores between the first and second flanges, and between the third and fourth flanges so as to prevent relative circumferential movement between the first and second flanges, and the third and fourth flanges, respectively.

12 more elements

Abstract

Claims8