公开(公告)号：US20230194094A1

公开(公告)日：2023-06-22

申请号：US17677165

申请日：2022-02-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Fei Han ,  Ramal Janith Samarasinghe ,  Pradeep Naik ,  Krishnakumar Venkatesan ,  Michael T. Bucaro ,  Ajoy Patra ,  Manampathy G. Giridharan

IPC: F23R3/16 ,  F02C3/00 ,  F02C7/22 ,  F23R3/36

CPC classification number: F23R3/16 ,  F02C3/00 ,  F02C7/22 ,  F23R3/36

Abstract: A turbine engine having a compressor section, a combustion section and a turbine section in serial flow arrangement. The turbine engine further having a combustor, provided within the combustion section, defining a combustion chamber and having at least one fuel injector. The fuel injector having a fuel channel, a first set of fuel orifices, and a flow restrictor located within the fuel channel and having a second set of fuel orifices.

公开(公告)号：US20230194088A1

公开(公告)日：2023-06-22

申请号：US17686800

申请日：2022-03-04

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/06 ,  F23R3/28

CPC classification number: F23R3/06 ,  F23R3/286 ,  F23R2900/03044

Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.

公开(公告)号：US11649966B1

公开(公告)日：2023-05-16

申请号：US17689070

申请日：2022-03-08

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/28 ,  F02C7/264 ,  F23R3/04 ,  F23R3/50 ,  F23D14/64

CPC classification number: F23R3/286 ,  F02C7/264 ,  F23D14/64 ,  F23R3/045 ,  F23R3/50 ,  F05D2240/35 ,  F05D2260/99 ,  F23D2207/00

Abstract: A turbine engine having a combustion section. The combustion section can have a combustor, at least one fuel cup, and at least one ignition tube. The combustor can include a combustor liner and a dome wall, which together at least partially define a combustion chamber. The at least one fuel cup can include a swirler and a fuel injector. The at least one ignition tube can include an outlet directly fluidly coupled to the combustion chamber.

公开(公告)号：US20220357038A1

公开(公告)日：2022-11-10

申请号：US17315016

申请日：2021-05-07

Applicant: General Electric Company

Inventor： Gregory A. Boardman ,  Pradeep Naik ,  Bassam Sabry Mohammad Abdelnabi ,  Manampathy G. Giridharan ,  Vishal Sanjay Kediya ,  Narasimhan S. Sahana

IPC: F23R3/28 ,  F23R3/34 ,  F23D14/58

Abstract: A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.

公开(公告)号：US20220349342A1

公开(公告)日：2022-11-03

申请号：US17244729

申请日：2021-04-29

Applicant: General Electric Company

Inventor： Manampathy G. Giridharan ,  Pradeep Naik ,  Narendra D. Joshi ,  Harris D. Abramson

IPC: F02C7/14 ,  F02C3/22

Abstract: A fuel mixer configured to provide a fuel-air mixture to a combustor of an engine. The fuel mixer may include a mixer body having a mixer outer wall, a center body, an annular passageway defined between the mixer outer wall and the center body, and a fuel tube assembly placed circumferentially about the mixer body. The fuel tube assembly may include at least one fuel channel for injecting a fuel flow into the annular passageway. The fuel tube assembly may be configured to cool a boundary layer flow present in the annular passageway. The fuel tube assembly may be configured to cool the mixer outer wall, the center body, or both the mixer outer wall and the center body. Heat from the mixer outer wall, the center body, or both the mixer outer wall and the center body, may pass to the fuel flow in the fuel tube assembly.