公开(公告)号：US20170370585A1

公开(公告)日：2017-12-28

申请号：US15189085

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

IPC: F23R3/06 ,  F02C7/18 ,  F23R3/28 ,  F23R3/14 ,  F23R3/00

CPC classification number: F23R3/06 ,  F02C7/18 ,  F05D2220/32 ,  F05D2270/082 ,  F23R3/002 ,  F23R3/007 ,  F23R3/045 ,  F23R3/14 ,  F23R3/286 ,  F23R2900/03043 ,  F23R2900/03044 ,  Y02T50/675 ,  Y02T50/677

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.

公开(公告)号：US20250155124A1

公开(公告)日：2025-05-15

申请号：US18507877

申请日：2023-11-13

Applicant: General Electric Company

Inventor： Joseph Zelina ,  Clayton S. Cooper ,  Sibtosh Pal ,  Pradeep Naik ,  Sripathi Mohan ,  Michael A. Benjamin

IPC: F23R3/34 ,  F02C3/30

Abstract: A turbine engine includes a compressor section for providing a compressed air flow, a fuel system for providing a primary combustor fuel supply, and a secondary combustor fuel supply. A primary combustor, located downstream of the compressor section, combusts the compressed air flow and the primary combustor fuel supply to generate primary combustion products. A turbine section, located downstream of the primary combustor, includes a turbine and a secondary combustor that further combusts the primary combustion products and the fuel from the secondary combustor fuel supply. A steam system provides a steam supply to the secondary combustor. The secondary combustor further combusts the primary combustion products and the secondary combustor fuel supply to generate secondary combustion products, and the turbine section is rotated by the secondary combustor steam supply and the inter-turbine combustion products.

公开(公告)号：US20250067439A1

公开(公告)日：2025-02-27

申请号：US18453506

申请日：2023-08-22

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

IPC: F23R3/28

Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

公开(公告)号：US20250035311A1

公开(公告)日：2025-01-30

申请号：US18804465

申请日：2024-08-14

Applicant: General Electric Company

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

IPC: F23R3/28 ,  F02C7/22 ,  F23C7/00 ,  F23D17/00 ,  F23L7/00 ,  F23R3/14 ,  F23R3/36

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 assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.

公开(公告)号：US12173900B2

公开(公告)日：2024-12-24

申请号：US17663093

申请日：2022-05-12

Applicant: General Electric Company

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

IPC: F23R3/06 ,  F23R3/16

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 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：US20240418369A1

公开(公告)日：2024-12-19

申请号：US18359178

申请日：2023-07-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Clayton Stuart Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan ,  Ajoy Patra ,  Karthikeyan Sampath

IPC: F23R3/00 ,  F23R3/34 ,  F23R3/42

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

公开(公告)号：US12152778B1

公开(公告)日：2024-11-26

申请号：US18345342

申请日：2023-06-30

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik

IPC: F23R3/06 ,  F23R3/00

Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side, a dilution opening extending through the liner body, a first passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, and a second passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, the second passage being separate from the first passage and being located on a diametrically opposing side of the dilution opening from the first passage. A dilution flow flows through the dilution opening from the cold side to the hot side and a secondary flow flows through the first passage and the second passage from the cold side to the hot side.

公开(公告)号：US12130013B2

公开(公告)日：2024-10-29

申请号：US17396155

申请日：2021-08-06

Applicant: General Electric Company

Inventor： Steven C. Vise ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Pradeep Naik ,  Kwanwoo Kim ,  Shai Birmaher ,  Perumallu Vukanti ,  Saket Singh ,  Karthikeyan Sampath

IPC: F23D11/38 ,  B05B7/10

CPC classification number: F23D11/383 ,  B05B7/10

Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

公开(公告)号：US12123596B2

公开(公告)日：2024-10-22

申请号：US17389022

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Neeraj Mishra

IPC: F23R3/14

CPC classification number: F23R3/14 ,  F05D2240/127 ,  F05D2240/35 ,  F05D2250/183

Abstract: A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.

公开(公告)号：US12018839B2

公开(公告)日：2024-06-25

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: F02C7/22 ,  F23R3/00 ,  F23R3/28

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.