公开(公告)号：US20230366551A1

公开(公告)日：2023-11-16

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：US11808454B2

公开(公告)日：2023-11-07

申请号：US17663095

申请日：2022-05-12

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Saket Singh ,  Krishnendu Chakraborty

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R3/08 ,  F02C7/00

CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R3/06 ,  F23R3/08 ,  F02C7/00

Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a plurality of dilution inserts. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.

公开(公告)号：US20230296251A1

公开(公告)日：2023-09-21

申请号：US17812278

申请日：2022-07-13

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Perumallu Vukanti ,  Pradeep Naik ,  Ravindra Shankar Ganiger ,  Daniel J. Kirtley ,  Arvind Namadevan ,  Ranganatha Narasimha Chiranthan ,  Hiranya Nath

IPC: F23R3/00

CPC classification number: F23R3/007 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03043

Abstract: A combustion liner assembly includes metal liner having a hot side and a cold side, a ceramic matrix composite (CMC) liner tile configured to provide a heat shield for the metal liner, the CMC liner tile having a different thermal conductivity than the metal liner, and a connection device configured to attach the CMC liner tile to the metal liner. The connection device accommodates the different thermal conductivity of the CMC liner tile and the metal liner. The connection device is free from a radial fastener exposed to hot gases on the hot side of the metal liner, and the connection device allows radial movement and axial movement between the metal liner and the CMC liner tile.

公开(公告)号：US20230288065A1

公开(公告)日：2023-09-14

申请号：US17810678

申请日：2022-07-05

Applicant: General Electric Company

Inventor： Saket Singh ,  Ravindra Shankar Ganiger ,  Hiranya Nath ,  Perumallu Vukanti ,  Ajoy Patra ,  Karthikeyan Sampath ,  Pradeep Naik ,  Rimple Rangrej ,  Veera Venkata Amarnath Manem

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/03043

Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.

公开(公告)号：US20230266002A1

公开(公告)日：2023-08-24

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: F23D11/38 ,  F23R3/14 ,  F23R3/28 ,  F23R3/50

CPC classification number: F23D11/383 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042

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：US20230235884A1

公开(公告)日：2023-07-27

申请号：US17685883

申请日：2022-03-03

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2240/35

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.

公开(公告)号：US20230213194A1

公开(公告)日：2023-07-06

申请号：US17699735

申请日：2022-03-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Ajoy Patra ,  R Narasimha Chiranthan

IPC: F23R3/28 ,  F23R3/14

CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R2900/03042

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 with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.

公开(公告)号：US20230212984A1

公开(公告)日：2023-07-06

申请号：US17692411

申请日：2022-03-11

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F02C7/232 ,  F23R3/28

CPC classification number: F02C7/232 ,  F23R3/28 ,  F05D2220/32 ,  F05D2240/35

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. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.

公开(公告)号：US11692709B2

公开(公告)日：2023-07-04

申请号：US17199257

申请日：2021-03-11

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Manampathy G. Giridharan ,  Vishal Sanjay Kediya ,  Gregory A. Boardman

IPC: F23R3/28 ,  F23R3/12 ,  F23R3/34 ,  F02C7/22

CPC classification number: F23R3/286 ,  F23R3/12 ,  F23R3/343 ,  F02C7/222

Abstract: A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.

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.