Snecma

Safran Aircraft Engines

Romain Biebel

Denis Jean Maurice Sandelis

Didier Hippolyte Hernandez

Denis Gabriel Trahot

Luc Henri Claude Daguenet

Claude Gautier

Luc Daguenet

Denis Sandelis

An annular combustion chamber of a turbomachine is provided. The combustion chamber includes an end wall provided at an upstream end of the chamber and side walls extending longitudinally from the end wall to an orifice for discharging a stream of combustion gases provided at a downstream end of the chamber. The side walls includes at least one row of openings for the intake of air for diluting the stream of combustion gases. At least one dilution opening has an upstream edge which projects toward the inside of the chamber and a downstream edge which projects toward the outside of the chamber and is asymmetric to the upstream edge with respect to a plane extending transversely to the wall. An aperture of the opening having an axis oriented in an oblique direction with respect to the wall. This direction being oriented toward the inside and toward the downstream end of the chamber.

Configuration of dilution openings in a turbomachine combustion chamber wall

A combustion chamber having a chamber end wall that presents a plurality of air and fuel injector devices, each of the devices including a bowl and a deflector mounted on a main axis forming a heat shield disposed around the bowl which flares in the gas flow direction and possesses an annular portion, the interface between the bowl and the deflector being situated on this annular portion, at least a portion of the interface being situated towards the end of the annular portion that is downstream in the gas flow direction, such that an annular cavity is defined between the deflector and the downstream annular portion of the interface. First bowl holes are formed in the annular portion to open out facing the edge of the chamber end wall that is in contact with the deflector in order to sustain a flow of air from upstream to downstream in the annular cavity.

Combustion chamber end wall with ventilation

The present invention is concerned with an annular combustion chamber of a gas turbine engine with an external annular wall and an internal annular wall, including an upstream fairing for separating the gas stream at the inlet of the chamber into a combustion stream and a bypass stream which bypasses the inlet of the chamber, the fairing including an annular wall forming a cap, which includes a downstream portion for fastening to a wall of the chamber and an upstream portion forming an edge of the flow cross section for the combustion stream, wherein the upstream portion is continued into at least one additional downstream portion for fastening to the wall of the chamber.

Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber

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Le Coudray Montceau, France

Romain Biebel