Patent ID: 9097425
Filing Date: 2015-08-04
Classification: F23R,Y02T

Abstract:
1. A fuel mixing device for an annular combustion chamber of an aircraft turbine engine, comprising from an upstream side of the fuel mixing device towards a downstream side of the fuel mixing device with respect to a fuel flow general direction, centered on a longitudinal axis of the fuel mixing device parallel to the fuel flow general direction: a centering member for centering a turbine engine injector head; at least one air intake ring comprising a plurality of blades swirling air around the longitudinal axis, the at least one air intake ring connected to the centering member; a bowl formed of a first annular wall flared radially outward from the longitudinal axis towards downstream, the bowl arranged downstream from the air intake ring, the bowl including an annular row of air intake orifices located in the first annular wall, an upstream part of the first annular wall sealingly joined to a second annular wall of the air intake ring, a downstream part of the first annular wall connected to an annular part located radially outside the annular row of air intake orifices, the annular part connected with an annular supporting wall, the annular supporting wall extending upstream from the downstream part of the first annular wall, the annular supporting wall sealingly joined to the second annular wall to enclose an annular cavity between the second annular wall, the bowl, and the annular supporting wall, the annular cavity communicating with the air intake orifices; and a channel arranged through each one of the plurality of blades, the channel feeding air to the annular cavity.