Snecma

Claude Gautier

Denis Jean Maurice Sandelis

Christophe Pieussergues

Alain Rene Cayre

Luc Henri Claude Daguenet

Stephane Henri Guy Touchaud

Romain Biebel

Gerard Edouard Emile Caboche

Denis Sandelis

Gérard Caboche

An annular wall which transversely connects longitudinal walls of an annular combustion chamber of a turbine engine is disclosed. The wall is essentially flat, inclined in relation to a longitudinal axis of the turbine engine, and includes a plurality of deflectors, each formed by an essentially rectangular flat sheet. The deflectors are mounted on the wall and each includes an aperture for the installation of a fuel injection system, a plurality of multi-perforation holes formed in relation to the deflectors around their aperture so as to allow a passage of air intended for the cooling of the deflectors, and a flow forcing unit which forces the flow of air for cooling the deflectors to flow radially around the fuel injection systems.

Transverse wall of a combustion chamber provided with multi-perforation holes

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

A diffuser for a single-head annular combustion chamber of an airplane engine, the diffuser comprising a separator formed by a thin sheet connected by structural arms to inner and outer circularly-symmetrical walls of the diffuser, the diffuser angle for each diffusion stream defined by the separator lying in the range about 12&#xb0; to about 13&#xb0;.

Diffuser for an annular combustion chamber, in particular for an airplane turbine engine

Device for guiding an element in an orifice in a wall of a turbomachine combustion chamber, including a ring and a bush, the ring being traversed axially by the element and including an external annular rim guided transversely in an internal annular channel of the bush, the ring and the bush delimiting around the element a cylindrical annular passage opening into the chamber, air circulation being provided in the ring and/or in the bush and distributed about their axis so as to establish an air circulation in the cylindrical passage from the outside of the combustion chamber toward the inside.

Growing community of inventors

Savigny-Le-Temple, France

Claude Gautier