US 11,747,019 B1
Aerodynamic combustor liner design for emissions reductions
Hiranya Nath, Bengaluru (IN); Ravindra Shankar Ganiger, Bengaluru (IN); Michael A. Benjamin, Cincinnati, OH (US); Steven C. Vise, Loveland, OH (US); Perumallu Vukanti, Bengaluru (IN); Sripathi Mohan, Bengaluru (IN); and Rimple Rangrej, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Sep. 2, 2022, as Appl. No. 17/929,359.
Int. Cl. F23R 3/06 (2006.01); F23R 3/16 (2006.01); F23R 3/50 (2006.01); F23R 3/46 (2006.01)
CPC F23R 3/06 (2013.01) [F23R 3/16 (2013.01); F23R 3/46 (2013.01); F23R 3/50 (2013.01); F23R 2900/03043 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustor liner for a combustor of a gas turbine, the combustor liner comprising:
an annular outer liner extending circumferentially about a combustor centerline of the combustor, and extending in a longitudinal direction, with respect to the combustor centerline, from an outer liner upstream end of the annular outer liner to an outer liner downstream end of the annular outer liner; and
an annular inner liner extending circumferentially about the combustor centerline, and extending in the longitudinal direction, with respect to the combustor centerline, from an inner liner upstream end of the annular inner liner to an inner liner downstream end of the annular inner liner,
the annular outer liner and the annular inner liner defining a combustion chamber therebetween, the combustion chamber having a primary combustion zone defined at an upstream end of the combustion chamber, a secondary combustion zone defined at a downstream end of the combustion chamber, and a dilution zone defined between the primary combustion zone and the secondary combustion zone,
wherein the annular outer liner comprises an outer liner converging-diverging (OLCD) section extending radially inward in the longitudinal direction, with respect to the combustor centerline, into the dilution zone of the combustion chamber, and the annular inner liner comprises an inner liner converging-diverging (ILCD) section extending radially outward in the longitudinal direction, with respect to the combustor centerline, into the dilution zone of the combustion chamber, the OLCD section and the ILCD section being radially opposed to one another across the combustion chamber, and
wherein the OLCD section comprises at least one outer liner dilution opening defined through the OLCD section for providing a flow of an oxidizer through the annular outer liner to the dilution zone of the combustion chamber, and the ILCD section comprises at least one inner liner dilution opening defined through the ILCD section for providing a flow of the oxidizer through the annular inner liner to the dilution zone of the combustion chamber, the at least one outer liner dilution opening comprising an outer liner annular slot and a plurality of outer liner dilution holes longitudinally offset from the outer liner annular slot, and the at least one inner liner dilution opening comprising an inner liner annular slot and a plurality of inner line dilution holes longitudinally offset from the inner liner annular slot, the outer liner annular slot being opposed across the combustion chamber by the plurality of inner liner dilution holes, and the inner liner annular slot being opposed across the combustion chamber by the plurality of outer liner dilution holes.