US 12,152,777 B2
Combustor for a gas turbine engine
Ravindra Shankar Ganiger, Bangalore (IN); Hiranya Kumar Nath, Bangalore (IN); Perumallu Vukanti, Bangalore (IN); Daniel J. Kirtley, Blue Ash, OH (US); Karthikeyan Sampath, Bangalore (IN); Shai Birmaher, Cincinnati, OH (US); Pradeep Naik, Bangalore (IN); Rajendra Mahadeorao Wankhade, Bangalore (IN); Michael Anthony Benjamin, Cincinnati, OH (US); Veeraraju Vanapalli, Bangalore (IN); and Deepak Ghiya, Bangalore (IN)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 7, 2021, as Appl. No. 17/340,703.
Prior Publication US 2022/0390112 A1, Dec. 8, 2022
Int. Cl. F23R 3/00 (2006.01); F23R 3/08 (2006.01); F01D 9/02 (2006.01)
CPC F23R 3/002 (2013.01) [F23R 3/08 (2013.01); F01D 9/023 (2013.01); F23R 2900/03043 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
a liner comprising a forward liner segment and an aft liner segment at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber;
one or more guides, wherein at least one guide of the one or more guides defines a scooped surface extending radially outward from an axially forwardmost end of the aft liner segment, the scooped surface formed to redirect cooling medium into the dilution slot; and
a fence extending radially inward from the axially forwardmost end of the aft liner segment into the combustion chamber through the dilution slot, wherein the fence and the scooped surface are axially spaced from an axially aftmost end of the forward liner segment by the dilution slot.