US 11,686,473 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. 17/663,103.
Claims priority of application No. 202111051753 (IN), filed on Nov. 11, 2021.
Prior Publication US 2023/0143185 A1, May 11, 2023
Int. Cl. F23R 3/06 (2006.01); F23R 3/04 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/06 (2013.01) [F23R 3/002 (2013.01); F23R 3/045 (2013.01); F23R 2900/03043 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A liner for a combustor in a gas turbine engine, the liner comprising:
a liner body having a cold side and a hot side; and
a dilution array comprising a plurality of dilution passages repeating in a predetermined pattern circumferentially around the liner body, each dilution passage of the plurality of dilution passages having a concatenated geometry comprising:
a discrete hole configured to inject a first dilution air flow therethrough from the cold side to the hot side; and
a discrete slot configured to inject a second dilution air flow therethrough from the cold side to the hot side, wherein the discrete hole is located downstream of the discrete slot such that the discrete hole is configured to inject the first dilution air flow downstream of a location at which the discrete slot is configured to inject the second dilution air flow,
wherein the dilution array is configured (i) to integrate the first dilution air flow and the second dilution air flow into an integrated dilution air flow, and (ii) 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,
wherein the dilution array is repeated along an axial length of the liner body,
wherein the discrete hole has a semi-circular cross section and a centerline extending through a center of a diameter of the semi-circular cross section, and
wherein a forward face of the discrete slot is coextensive with a plane parallel to the forward face and extends through the centerline of the discrete hole.
 
14. A liner for a combustor in a gas turbine engine, the liner comprising:
a liner body having a cold side and a hot side; and
a dilution array comprising a plurality of dilution passages repeating in a predetermined pattern circumferentially around the liner body, each dilution passage of the plurality of dilution passages having a concatenated geometry comprising:
a discrete hole having a semi-circular cross section with a centerline extending through a center of a diameter of the semi-circular cross section, the discrete hole configured to inject a first dilution air flow therethrough from the cold side to the hot side; and
a discrete slot configured to inject a second dilution air flow therethrough from the cold side to the hot side, wherein the discrete slot is located downstream of the discrete hole such that the discrete slot is configured to inject the second dilution air flow downstream of a location at which the discrete hole is configured to inject the first dilution air flow and wherein an aft face of the discrete slot is coextensive with a plane parallel to the aft face and extends through the centerline of the discrete hole,
wherein the dilution array is configured (i) to integrate the first dilution air flow and the second dilution air flow into an integrated dilution air flow, and (ii) 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, and
wherein the dilution array is repeated along an axial length of the liner body.