公开(公告)号：US12038176B2

公开(公告)日：2024-07-16

申请号：US17651644

申请日：2022-02-18

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Kwanwoo Kim ,  Saket Singh ,  Perumallu Vukanti ,  Karthikeyan Sampath ,  Steven C. Vise ,  Nicholas R. Overman ,  Michael A. Benjamin

IPC: F23R3/14 ,  F23R3/28 ,  F23D11/38

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23D11/383

Abstract: A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.

公开(公告)号：US20240230088A9

公开(公告)日：2024-07-11

申请号：US18314418

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Rimple Rangrej ,  Pradeep Naik ,  Saket Singh ,  Deepak Ghiya ,  Perumallu Vukanti

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R2900/00014

Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.

公开(公告)号：US20240151396A1

公开(公告)日：2024-05-09

申请号：US18482949

申请日：2023-10-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Ajoy Patra ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Perumallu Vukanti ,  Michael T. Bucaro

IPC: F23R3/28

CPC classification number: F23R3/286

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

公开(公告)号：US11927349B2

公开(公告)日：2024-03-12

申请号：US17812897

申请日：2022-07-15

Applicant: General Electric Company

Inventor： Vijayaraj Sukumar ,  Perumallu Vukanti ,  Pradeep Naik ,  Ajoy Patra ,  Karthikeyan Sampath ,  Rimple Rangrej ,  Hiranya Nath ,  Krishnendu Chakraborty ,  Narasimhan S. Sahana ,  Saket Singh ,  Ravindra Shankar Ganiger

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/10 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R3/04 ,  F23R3/10 ,  F23R2900/00017 ,  F23R2900/03045

Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

公开(公告)号：US11906165B2

公开(公告)日：2024-02-20

申请号：US17717739

申请日：2022-04-11

Applicant: General Electric Company

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

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：US20230341125A1

公开(公告)日：2023-10-26

申请号：US17820373

申请日：2022-08-17

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Ravindra Shankar Ganiger ,  Pradeep Naik

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A combustor liner for a gas turbine includes a liner at least partially defining a combustion chamber. The liner includes a plurality of dilution openings therethrough, at least one dilution opening of the plurality of dilution openings defined by (a) a main dilution opening portion defining a main dilution opening perimeter, and (b) a plurality of secondary dilution opening portions arranged about the main dilution opening perimeter and extending outward from the main dilution opening portion.

公开(公告)号：US20230304665A1

公开(公告)日：2023-09-28

申请号：US18302346

申请日：2023-04-18

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 method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.

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：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：US20220390112A1

公开(公告)日：2022-12-08

申请号：US17340703

申请日：2021-06-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Perumallu Vukanti ,  Daniel J. Kirtley ,  Karthikeyan Sampath ,  Shai Birmaher ,  Pradeep Naik ,  Rajendra Mahadeorao Wankhade ,  Michael Anthony Benjamin ,  Veeraraju Vanapalli ,  Deepak Ghiya

IPC: F23R3/00 ,  F02C3/14

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.