公开(公告)号：US12007114B1

公开(公告)日：2024-06-11

申请号：US18187359

申请日：2023-03-21

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Sibtosh Pal ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Ajoy Patra ,  Michael T. Bucaro ,  Aritra Chakraborty ,  Arijit Sinha Roy ,  Pabitra Badhuk ,  Bhavya Naidu Panduri

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A first fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.