公开(公告)号：US20250067435A1

公开(公告)日：2025-02-27

申请号：US18943011

申请日：2024-11-11

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Pradeep Naik ,  Michael A. Benjamin

IPC: F23R3/06 ,  F23R3/26

Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and a set of dilution passages. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The set of dilution passages extending through at least one of the inner liner or the outer liner. Each dilution passage of the set of dilution passages extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.

公开(公告)号：US12163660B2

公开(公告)日：2024-12-10

申请号：US18484987

申请日：2023-10-11

Applicant: General Electric Company

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

IPC: 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.

公开(公告)号：US12104795B2

公开(公告)日：2024-10-01

申请号：US17664975

申请日：2022-05-25

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin

IPC: F23R3/26 ,  F23R3/04 ,  F23R3/42 ,  F23R3/06 ,  F23R3/08

CPC classification number: F23R3/42 ,  F23R3/04 ,  F23R3/26 ,  F23R3/06 ,  F23R3/08

Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.

公开(公告)号：US20240318822A1

公开(公告)日：2024-09-26

申请号：US18663324

申请日：2024-05-14

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Sibtosh Pal ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Ajoy Patra ,  Michael T. Bucaro ,  Aritra Chakraborty ,  Arijit Sinha Roy ,  Pabitra Badhuk ,  Bhavya Naidu Panduri

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.

公开(公告)号：US20240280265A1

公开(公告)日：2024-08-22

申请号：US18452958

申请日：2023-08-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nayan Vinod Patel ,  Michael A. Benjamin

IPC: F23R3/34 ,  F02C7/22 ,  F23R3/06 ,  F23R3/14 ,  F23R3/28 ,  F23R3/36

CPC classification number: F23R3/06 ,  F23R3/34 ,  F02C7/22 ,  F23R3/14 ,  F23R3/28 ,  F23R3/346 ,  F23R3/36

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 combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

公开(公告)号：US20240247807A1

公开(公告)日：2024-07-25

申请号：US18585509

申请日：2024-02-23

Applicant: General Electric Company

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

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

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：US20240230100A9

公开(公告)日：2024-07-11

申请号：US18314565

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin ,  Daniel D. Brown ,  Sibtosh Pal ,  Joseph Zelina

IPC: F23R3/60 ,  F02C7/20 ,  F23R3/06

CPC classification number: F23R3/60 ,  F02C7/20 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042

Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.

公开(公告)号：US20240117967A1

公开(公告)日：2024-04-11

申请号：US18359346

申请日：2023-07-26

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING

IPC: F23R3/06 ,  F23R3/14 ,  F23R3/28

CPC classification number: F23R3/06 ,  F23R3/14 ,  F23R3/286

Abstract: There is described a fuel injector for a gas turbine engine. The fuel injector comprises an air passageway having an inlet region and an outlet region in fluid communication with the inlet region at an air passageway interface, the inlet region being configured to receive a flow of air from a compressor of the gas turbine engine at an air inlet, the outlet region being configured to receive the flow of air from the inlet region via the air passageway interface and discharge the flow of air to a combustor head of the gas turbine engine. The fuel injector also comprises a fuel passageway having a fuel outlet configured to discharge a flow of fuel into the combustor head. A width of the inlet region in a direction perpendicular to a centreline of the air passageway decreases continuously from the air inlet to the air passageway interface.

公开(公告)号：US20240102655A1

公开(公告)日：2024-03-28

申请号：US18164491

申请日：2023-02-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Justin M Locke ,  Dennis M Moura ,  Duane C McCormick ,  Scott A Liljenberg ,  Theodore R Strickland ,  William Proscia

IPC: F23R3/28 ,  F23D11/38 ,  F23K5/06 ,  F23R3/06 ,  F23R3/12 ,  F23R3/14 ,  F23R3/34 ,  F23R3/50

CPC classification number: F23R3/28 ,  F23D11/38 ,  F23K5/06 ,  F23R3/06 ,  F23R3/12 ,  F23R3/14 ,  F23R3/346 ,  F23R3/50 ,  F23R2900/00014 ,  F23R2900/03042

Abstract: A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

公开(公告)号：US11940151B2

公开(公告)日：2024-03-26

申请号：US17694978

申请日：2022-03-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Michael T. Bucaro ,  Clayton S. Cooper

IPC: F23R3/28 ,  F23R3/00 ,  F23R3/06 ,  F23R3/50

CPC classification number: F23R3/286 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50

Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.