US 12,007,114 B1
Gas turbine engine combustor with openings
Perumallu Vukanti, Bengaluru (IN); Sibtosh Pal, Mason, OH (US); Pradeep Naik, Bengaluru (IN); R Narasimha Chiranthan, Bengaluru (IN); Ajoy Patra, Bengaluru (IN); Michael T. Bucaro, Arvada, CO (US); Aritra Chakraborty, Bengaluru (IN); Arijit Sinha Roy, Bengaluru (IN); Pabitra Badhuk, Bengaluru (IN); and Bhavya Naidu Panduri, Bengaluru (IN)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 21, 2023, as Appl. No. 18/187,359.
Int. Cl. F23R 3/06 (2006.01)
CPC F23R 3/06 (2013.01) 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:
a combustor liner at least partially defining a combustor chamber;
a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;
a first fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;
a first set of openings comprising a first opening emitting air into the combustion chamber along a first flow path streamline; and
a second set of openings comprising a second opening emitting air into the combustion chamber along a second flow path streamline;
wherein the first flow path streamline intersects the second flow path streamline at an intersection point to form a sheet of air; and
wherein each opening of the first set of openings is radially aligned with another opening of the first set of openings relative to the engine rotational axis, and wherein each opening of the second set of openings is radially aligned with another opening of the second set of openings relative to the engine rotational axis.