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：US11906168B2

公开(公告)日：2024-02-20

申请号：US17198150

申请日：2021-03-10

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Joseph Zelina ,  Clayton Stuart Cooper

IPC: F23R3/42 ,  F23R3/28 ,  F23R3/58 ,  F02C3/14 ,  F23R3/34 ,  F02C7/22 ,  F23R3/12

CPC classification number: F23R3/286 ,  F02C3/14 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F02C7/22 ,  F23R3/12 ,  F23R3/34 ,  F23R2900/00015

Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

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：US20230417415A1

公开(公告)日：2023-12-28

申请号：US18464550

申请日：2023-09-11

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Rimple Rakeshkumar Rangrej ,  Saket Singh ,  Narasimha Chiranthan R. ,  Shai Birmaher ,  Hiranya Kumar Nath ,  Ravindra Shankar Ganiger

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/08 ,  F23R3/06 ,  F23R3/34

CPC classification number: F23R3/16 ,  F23R3/002 ,  F23R3/08 ,  F23R3/06 ,  F23R3/346 ,  F23M5/085

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 forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

公开(公告)号：US20230341127A1

公开(公告)日：2023-10-26

申请号：US18342960

申请日：2023-06-28

Applicant: General Electric Company

Inventor： Ranjeet Kumar Mishra ,  Jayanth Sekar ,  Pradeep Naik ,  Gregory A. Boardman ,  Randall C. Boehm

IPC: F23R3/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R3/16

Abstract: A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.

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：US11788726B2

公开(公告)日：2023-10-17

申请号：US17653399

申请日：2022-03-03

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Ajoy Patra

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.