US 11,835,236 B1
Combustor with reverse dilution air introduction
Hiranya Kumar Nath, Bengaluru (IN); Ravindra Shankar Ganiger, Bengaluru (IN); and Steven Clayton Vise, Loveland, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jul. 5, 2022, as Appl. No. 17/857,657.
Int. Cl. F23R 3/54 (2006.01); F23R 3/00 (2006.01); F23R 3/06 (2006.01)
CPC F23R 3/54 (2013.01) [F23R 3/002 (2013.01); F23R 3/06 (2013.01); F05D 2240/35 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A combustor for a gas turbine engine comprising:
a forward liner segment having an aft end portion, wherein the forward liner segment defines a primary combustion chamber; and
an aft liner segment having a forward end portion, wherein the forward end portion is disposed within the aft end portion of the forward liner segment, wherein a channel extends radially from an inner surface of the forward liner segment to an outer surface of the aft liner segment, wherein the channel directs a stream of dilution air in a counter-flow direction with respect to combustion gases flowing from the primary combustion chamber during operation of the combustor,
wherein one of the forward liner segment or the aft liner segment comprises a first damping chamber and a second damping chamber, wherein the first and second damping chambers are disposed downstream from the primary combustion chamber and upstream from a secondary combustion chamber at least partially defined by the aft liner segment, and wherein a wall partially defines the channel and one of the first damping chamber or the second damping chamber and separates the channel from the one of the first damping chamber or the second damping chamber.
 
10. A gas turbine engine, comprising:
a fan, a compressor section, a combustor section, and a turbine section, the combustor section including a combustor, the combustor comprising:
a forward liner segment having an aft end portion, wherein the forward liner segment defines a primary combustion chamber; and
an aft liner segment having a forward end portion, wherein the forward end portion is disposed within the aft end portion of the forward liner segment, wherein the aft liner segment at least partially defines a secondary combustion chamber, wherein a channel is defined radially from an inner surface of the aft end portion of the forward liner segment to an outer surface the forward end portion of the aft liner segment, wherein the channel is oriented to direct a stream of dilution air in a counter-flow direction with respect to combustion gases flowing from the primary combustion chamber towards the secondary combustion chamber during operation of the combustor,
wherein one of the forward liner segment or the aft liner segment comprises a first damping chamber and a second damping chamber, wherein the first and second damping chambers are disposed downstream from the primary combustion chamber and upstream from the secondary combustion chamber, and wherein a wall partially defines the channel and one of the first damping chamber or the second damping chamber and separates the channel from the one of the first damping chamber or the second damping chamber.