公开(公告)号：US11959643B2

公开(公告)日：2024-04-16

申请号：US17340856

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/60 ,  F23R3/06 ,  B33Y80/00

CPC classification number: F23R3/60 ,  F23R3/06 ,  B33Y80/00 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018

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 an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

公开(公告)号：US11920796B2

公开(公告)日：2024-03-05

申请号：US17340856

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/60 ,  F23R3/06 ,  B33Y80/00

CPC classification number: F23R3/60 ,  F23R3/06 ,  B33Y80/00 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018

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 an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

公开(公告)号：US20230313744A1

公开(公告)日：2023-10-05

申请号：US17712747

申请日：2022-04-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin ,  Stefan Joseph Cafaro

IPC: F02C9/40 ,  F23R3/36 ,  F02C7/32 ,  F02C9/48

CPC classification number: F02C9/40 ,  F23R3/36 ,  F02C7/32 ,  F02C9/48 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2270/304

Abstract: A method of operating a gas turbine engine is provided. The method includes: providing a flow of a primary fuel to a combustor of a turbomachine, the turbomachine including a compressor, a turbine, and a spool rotatable with the compressor and the turbine; receiving data indicative of a spool parameter of the spool; and modifying a flow of a secondary fuel to the combustor in response to the received data indicative of the spool parameter of the spool.

公开(公告)号：US11719441B2

公开(公告)日：2023-08-08

申请号：US17568341

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: F23R3/40 ,  F23R3/28

CPC classification number: F23R3/40 ,  F23R3/28

Abstract: Systems and methods including a reformer stack extended around a combustion chamber. The reformer stack is configured to provide output products to the combustion chamber.

公开(公告)号：US20230212991A1

公开(公告)日：2023-07-06

申请号：US17568313

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Michael Anthony Benjamin

IPC: F02C9/40 ,  F02C7/22 ,  F23R3/36

CPC classification number: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F05D2220/32 ,  F05D2240/35

Abstract: Systems and methods include a fuel cell stack extended around a combustion chamber that is configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution. The fuel cell stack is positioned at a downstream section of the combustion chamber along an axial direction.

公开(公告)号：US11549686B2

公开(公告)日：2023-01-10

申请号：US17751886

申请日：2022-05-24

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Daniel J. Kirtley

IPC: F23R3/00

Abstract: A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.

公开(公告)号：US11371701B1

公开(公告)日：2022-06-28

申请号：US17166687

申请日：2021-02-03

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Daniel J. Kirtley

IPC: F23R3/00

Abstract: A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.

公开(公告)号：US20220195931A1

公开(公告)日：2022-06-23

申请号：US17130040

申请日：2020-12-22

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade ,  Gurunath Gandikota

IPC: F02C7/24 ,  F02C7/22 ,  F23R3/28

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.

公开(公告)号：US11156360B2

公开(公告)日：2021-10-26

申请号：US16278341

申请日：2019-02-18

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Michael Anthony Benjamin ,  Pradeep Naik ,  Vishal Sanjay Kediya

IPC: F23R3/00 ,  F23R3/28 ,  F02C7/22

Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. A centerbody is positioned radially inward of the outer sleeve. The centerbody includes an outer annular wall extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve further includes a first radial wall extended from a downstream end of the outer annular wall. The centerbody defines a plenum radially inward thereof. The outer annular wall and the outer sleeve together define a first fuel air mixing passage extended along the longitudinal direction therebetween. A fuel injector is disposed in the plenum. The fuel injector includes a tubular outer wall extended co-directional to the fuel nozzle centerline. The outer wall defines a second fuel air mixing passage therewithin. The second fuel air mixing passage is extended through the first radial wall of the centerbody.

公开(公告)号：US11092076B2

公开(公告)日：2021-08-17

申请号：US15823732

申请日：2017-11-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Anquan Wang ,  Hojjat Nasr ,  Craig Alan Gonyou ,  Michael Anthony Benjamin

IPC: F02C7/18 ,  F23R3/00 ,  F23R3/28 ,  F23R3/04 ,  F23R3/10 ,  F02C3/04

Abstract: A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.