US 11,940,151 B2
Combustor with baffle
Michael T. Bucaro, Arvada, CO (US); and Clayton S. Cooper, Evendale, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Mar. 15, 2022, as Appl. No. 17/694,978.
Claims priority of provisional application 63/298,749, filed on Jan. 12, 2022.
Prior Publication US 2023/0220998 A1, Jul. 13, 2023
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 comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, the combustion section comprising:
a combustion chamber having a first end and a second end downstream of the first end;
a combustor liner comprising an inner liner and an outer liner together at least partially defining the combustion chamber as having a modified can shape at the first end of the combustion chamber and an annular shape at the second end of the combustion chamber, the modified can shape defining a plurality of fuel cups, the inner liner spaced from the outer liner at the first end to define circumferentially spaced openings located between and fluidly coupling adjacent fuel cups in the plurality of fuel cups;
wherein the circumferentially spaced openings gradually widen as the combustor liner extends from the first end of the combustion chamber to the second end of the combustion chamber,
wherein a first maximum radial distance between the outer liner and the inner liner is larger than the circumferentially spaced openings between the adjacent fuel cups at the first end, and
wherein a second maximum radial distance between the outer liner and the inner liner is same as the circumferentially spaced openings between the adjacent fuel cups at the second end.