公开(公告)号：US20230296250A1

公开(公告)日：2023-09-21

申请号：US17740443

申请日：2022-05-10

Applicant: General Electric Company

Inventor： Manampathy G. Giridharan ,  Michael T. Bucaro ,  Pradeep Naik ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Ajoy Patra ,  Perumallu Vukanti ,  R Narasimha Chiranthan

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R2900/03044

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.

公开(公告)号：US20230220993A1

公开(公告)日：2023-07-13

申请号：US17686904

申请日：2022-03-04

Applicant: General Electric Company

Inventor： Michael T. Bucaro ,  Clayton S. Cooper

IPC: F23D14/62 ,  F23R3/06 ,  F23R3/28 ,  F23D14/58 ,  F23D14/70

CPC classification number: F23D14/62 ,  F23R3/06 ,  F23R3/286 ,  F23D14/58 ,  F23D14/70

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor liner, a dome assembly coupled to the combustor liner, a fuel nozzle fluidly coupled to the dome assembly, a combustion chamber fluidly coupled to the fuel nozzle, and at least one set of dilution openings located in the dome assembly or combustor liner that fluidly couple to the combustion chamber. A swirler can define at least one passage extending between at least one annular entrance and at least one annular exit, wherein the at least one annular entrance is fluidly coupled to the compressor section. A variable area device is movable relative to the at least one set of dilution openings or at least a portion of the swirler.

公开(公告)号：US20230194095A1

公开(公告)日：2023-06-22

申请号：US17700852

申请日：2022-03-22

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Michael T. Bucaro ,  Ajoy Patra ,  Manampathy G. Giridharan ,  Steven C. Vise ,  R Narasimha Chiranthan ,  Michael A. Benjamin ,  Clayton S. Cooper

IPC: F23R3/38 ,  F02C7/22

CPC classification number: F23R3/38 ,  F02C7/22

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US11092084B2

公开(公告)日：2021-08-17

申请号：US15164946

申请日：2016-05-26

Applicant: General Electric Company

Inventor： Kwanwoo Kim ,  Raymond Floyd Martell ,  Alfred Albert Mancini ,  Clayton S. Cooper

IPC: F02C7/22 ,  F02C9/26 ,  F02C7/228 ,  F23R3/28 ,  F23R3/34

Abstract: A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.