US 12,435,877 B2
Gas turbine engine combustor with a set of dilution passages
Bhavya Naidu Panduri, Bengaluru (IN); Perumallu Vukanti, Bengaluru (IN); Pradeep Naik, Bengaluru (IN); Michael T. Bucaro, Arvada, CO (US); Sibtosh Pal, Mason, OH (US); Aritra Chakraborty, Bengaluru (IN); Pabitra Badhuk, Bengaluru (IN); Arijit Sinha Roy, Bengaluru (IN); Ajoy Patra, Bengaluru (IN); and R Narasimha Chiranthan, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Apr. 5, 2023, as Appl. No. 18/296,220.
Claims priority of application No. 202311011415 (IN), filed on Feb. 20, 2023.
Prior Publication US 2024/0280264 A1, Aug. 22, 2024
Int. Cl. F23R 3/06 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/06 (2013.01) [F23R 3/002 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A combustor for a gas turbine engine, the combustor defining a combustor centerline and comprising:
a dome wall;
a set of fuel cups located on the dome wall, with each fuel cup of the set of fuel cups having a fuel cup centerline and an outlet;
an inner liner and an outer liner, which, in combination with the dome wall, at least partially define a combustion chamber having a mean centerline for each fuel cup of the set of fuel cups, with the mean centerline being equidistant between the inner liner and the outer liner; and
a set of dilution passages terminating in a plurality of dilution holes arranged in a dilution hole arrangement provided in at least one of the inner liner or the outer liner, with the dilution hole arrangement having at least a first subset of dilution holes arranged along a first leg and a second subset of dilution holes arranged along a second leg, with the first leg and the second leg meeting at an apex that is pointed toward the dome wall, the apex coinciding with a center point of a dilution hole of the plurality of dilution holes, and with the first leg terminating at a center point of an axially downstream most dilution hole of the first subset of dilution holes, and the second leg terminating at a center point of an axially downstream most dilution hole of the second subset of dilution holes;
wherein:
the first leg forms a first angle with respect to a radial plane that is perpendicular to the combustor centerline and passes through the apex, the first angle having an absolute value being greater than or equal to 0 degrees and less than 90 degrees;
the second leg forms a second angle with respect to the radial plane, the second angle having an absolute value being greater than or equal to 0 degrees and less than 90 degrees; and
the first leg and the second leg diverge axially downstream of the apex defining a segment angle therebetween, with an entire circumferential area formed between the apex, the axially downstream most dilution hole of the first subset of dilution holes and the axially downstream most dilution hole of the second subset of dilution holes being devoid of any dilution holes, the area being defined by the segment angle, and the area being located along the at least one of the inner liner or the outer liner.