US 11,808,454 B2
Combustion liner
Pradeep Naik, Bengaluru (IN); Shai Birmaher, Cincinnati, OH (US); Saket Singh, Bengaluru (IN); and Krishnendu Chakraborty, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 12, 2022, as Appl. No. 17/663,095.
Claims priority of application No. 202111051693 (IN), filed on Nov. 11, 2021.
Prior Publication US 2023/0148305 A1, May 11, 2023
Int. Cl. F23R 3/00 (2006.01); F23R 3/04 (2006.01); F23R 3/06 (2006.01); F23R 3/08 (2006.01); F02C 7/00 (2006.01)
CPC F23R 3/002 (2013.01) [F23R 3/04 (2013.01); F23R 3/06 (2013.01); F23R 3/08 (2013.01); F02C 7/00 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A liner for a combustor in a gas turbine engine, the liner comprising:
a liner body having a first surface on a cold side and a second surface on a hot side; and
a dilution passage having a concatenated geometry extending through the liner body, the dilution passage configured (a) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (b) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor, the concatenated geometry having:
(i) a plurality of discrete dilution holes extending from the first surface to the second surface, through which flows the first dilution air flow;
(ii) an annular slot extending from the first surface to the second surface, through which flows the second dilution air flow; and
(iii) a plurality of dilution inserts extending radially inward from the second surface and bordering the annular slot, through which flows the first dilution air flow, each dilution insert of the plurality of dilution inserts concatenated with a respective discrete dilution hole of the plurality of discrete dilution holes, the plurality of dilution inserts configured to assist penetration of the first dilution air flow and the second dilution air flow into the core primary combustion zone of the combustor.