公开(公告)号：US20220333781A1

公开(公告)日：2022-10-20

申请号：US17232433

申请日：2021-04-16

Applicant: General Electric Company

Inventor： Hari Ravi Chandra ,  Jayanth Sekar ,  Gurunath Gandikota ,  Michael A. Benjamin

IPC: F23R3/28 ,  F23D14/64 ,  F23R3/34 ,  F02C7/232

Abstract: A mixing assembly for a combustor includes: a pilot mixer including a pilot housing extending along a mixer centerline and a pilot fuel nozzle; a main mixer surrounding the pilot mixer; a fuel manifold between the pilot and main mixers; a mixer foot extending from a main housing of the main mixer; a main swirler body surrounding the main housing defining a mixing channel between the main housing and the main swirler body; and a main fuel ring in the mixing channel connected to the main housing by main fuel vanes, at least one of the main fuel ring and main fuel vanes including fuel injection ports for discharging fuel into the mixing channel, wherein the fuel injection ports are disposed non-uniformly relative to the mixer centerline, so as to produce a static pressure difference therebetween in response to mixer air flow passing around the main fuel ring.

公开(公告)号：US11421884B2

公开(公告)日：2022-08-23

申请号：US17231750

申请日：2021-04-15

Applicant: General Electric Company

Inventor： Nayan Vinodbhai Patel ,  Duane Douglas Thomsen ,  Michael A. Benjamin

IPC: F23R3/28 ,  F23R3/14

Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.

公开(公告)号：US12085281B2

公开(公告)日：2024-09-10

申请号：US18350205

申请日：2023-07-11

Applicant: General Electric Company

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US12078100B2

公开(公告)日：2024-09-03

申请号：US17457559

申请日：2021-12-03

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F02C3/22 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  F02C6/20

CPC classification number: F02C3/22 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  F02C6/20 ,  F05D2240/35

Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.

公开(公告)号：US20240288167A1

公开(公告)日：2024-08-29

申请号：US18660463

申请日：2024-05-10

Applicant: General Electric Company

Inventor： Michael A. Benjamin ,  Manampathy G. Giridharan

IPC: F23R3/28 ,  F02C3/22 ,  F23R3/42

CPC classification number: F23R3/28 ,  F02C3/22 ,  F23R3/42

Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.

公开(公告)号：US12072099B2

公开(公告)日：2024-08-27

申请号：US17682510

申请日：2022-02-28

Applicant: General Electric Company

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

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 meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US20240230091A9

公开(公告)日：2024-07-11

申请号：US17969913

申请日：2022-10-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  Sibtosh Pal ,  Michael A. Benjamin ,  Bhavya Naidu Panduri ,  Aritra Chakraborty ,  Pabitra Badhuk

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/00

CPC classification number: F23R3/28 ,  F02C7/22 ,  F23R3/002 ,  F05D2220/32 ,  F05D2240/35

Abstract: A combustor including an annular liner, a dome wall, a combustion chamber, at least one fuel cup and at least one dilution passage. The fuel cup being provided on the dome wall and being fluidly coupled to the combustion chamber. The fuel cup defining a fuel cup centerline. The at least on dilution passage terminating in at least on slot opening onto the dome wall, with the at least one slot having a longitudinal body axis.

公开(公告)号：US12031486B2

公开(公告)日：2024-07-09

申请号：US17717636

申请日：2022-04-11

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F02C7/232 ,  F23R3/34

CPC classification number: F02C7/232 ,  F23R3/34

Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.

公开(公告)号：US20240183536A1

公开(公告)日：2024-06-06

申请号：US18409690

申请日：2024-01-10

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

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. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.

公开(公告)号：US20240133556A1

公开(公告)日：2024-04-25

申请号：US18314565

申请日：2023-05-08

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin ,  Daniel D. Brown ,  Sibtosh Pal ,  Joseph Zelina

IPC: F23R3/60 ,  F02C7/20 ,  F23R3/06

CPC classification number: F23R3/60 ,  F02C7/20 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042

Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.