Safran Aircraft Engines

Yvan Yoann Guezel

Romain Nicolas Lunel

François Xavier Chapelle

Laurent Donatien Behaghel

Erwan Pierre Antoine Perse

Stephane Geyl

Cécile Thiriet

The invention relates to a bottom wall () of a gas turbomachine combustion chamber. This bottom wall comprises openings () for mounting combustion air supply systems and holes () for the passage of cooling air between at least one inlet () and at least one outlet of said holes. The holes () extend inwardly along the bottom wall with the outlet port located closer to the opening () adjacent to it than the inlet hole.

Turbine engine combustion chamber bottom

A combustion chamber for a turbomachine having a bottom wall, at least one mixing bowl for promoting the mixing of air and fuel, mounted in an opening in the bottom wall, at least one annular baffle mounted axially downstream of the bottom wall, with respect to the direction of the gas flow within the combustion chamber, around the opening. The baffle is produced in one piece with the mixing bowl so as to form a one-piece assembly that has at least one channel for the flow of cooling air. The channel has an air inlet located upstream of the bottom wall and an air outlet located downstream of the bottom wall. The air outlet is located radially opposite the baffle.

Combustion chamber for a turbomachine

A turbine engine includes an element (), comprising a wall () and at least one load-bearing member () extending substantially perpendicularly relative to the wall (), with said member () being intended to be attached onto a mounting () used for the attachment thereof onto an aircraft structural part. A thermal protection member () surrounds said member (), with said thermal protection member () including a base flexibly supported on the wall () of the element (), with said base matching the shape of said wall and at least one covering part which surrounds said load-bearing member.

Growing community of inventors

Moissy-Cramayel, France

Yvan Yoann Guezel