US 12,305,861 B2
Combustor with baffle
Michael T. Bucaro, Arvada, CO (US); and Clayton S. Cooper, Evendale, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Mar. 6, 2024, as Appl. No. 18/597,287.
Application 18/597,287 is a division of application No. 17/694,978, filed on Mar. 15, 2022, granted, now 11,940,151.
Claims priority of provisional application 63/298,749, filed on Jan. 12, 2022.
Prior Publication US 2024/0210036 A1, Jun. 27, 2024
Int. Cl. F23R 3/28 (2006.01); F23R 3/00 (2006.01); F23R 3/06 (2006.01); F23R 3/50 (2006.01)
CPC F23R 3/286 (2013.01) [F23R 3/002 (2013.01); F23R 3/06 (2013.01); F23R 3/50 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine having an engine centerline, the gas turbine engine comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, the combustion section comprising:
a combustion chamber having a dome wall at a first end and a combustor outlet at a second end, wherein the second end is spaced from the first end; and
a combustor liner extending axially from the first end to the second end, the combustor liner comprising an inner liner and an outer liner together at least partially defining the combustion chamber as having a can shape at the first end of the combustion chamber and an annular shape at the second end of the combustion chamber, the can shape defining a plurality of discrete, circumferentially-spaced, fuel cups fluidly separate from each other proximate the first end; and
wherein the inner liner and the outer liner meet at the first end to physically separate the plurality of discrete, circumferentially-spaced, fuel cups, and the inner liner and the outer liner gradually radially separate in a downstream axial direction, with respect to the engine centerline, to the second end.