US 12,422,143 B1
Fuel-air mixer for turbine engine combustion section
Gregory Boardman, Owens Cross Roads, AL (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Mar. 5, 2024, as Appl. No. 18/596,056.
Int. Cl. F23R 3/28 (2006.01); F23R 3/14 (2006.01)
CPC F23R 3/286 (2013.01) [F23R 3/14 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An apparatus for a turbine engine, comprising:
a fuel-air mixer including a mixer outlet, an annular inner passage, an air swirler, an annular fuel passage, a center body and a fuel swirler;
the annular inner passage extending axially along an axis within the fuel-air mixer, the annular inner passage extending axially along and circumscribing the center body, the annular inner passage including an inner passage downstream section and an inner passage upstream section fluidly coupled with the mixer outlet through the inner passage downstream section, and the inner passage downstream section radially tapering and diverging radially outward away from the axis as the annular inner passage extends axially towards the mixer outlet;
the air swirler disposed with the inner passage upstream section;
the annular fuel passage circumscribing the annular inner passage and extending axially within the fuel-air mixer to the inner passage downstream section, wherein a centerline of a half of the annular fuel passage, at an annular outlet from the annular fuel passage into the inner passage downstream section, is parallel with the axis;
the center body including an air inlet, a plurality of air outlets and an internal cavity, the internal cavity fluidly coupled with and between the air inlet and the plurality of air outlets, the internal cavity fluidly coupled with the mixer outlet through the plurality of air outlets, and the internal cavity extending within the axis; and
the fuel swirler disposed with the annular fuel passage.