公开(公告)号：US12152777B2

公开(公告)日：2024-11-26

申请号：US17340703

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/00 ,  F23R3/08 ,  F01D9/02

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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

公开(公告)号：US12146660B2

公开(公告)日：2024-11-19

申请号：US17340654

申请日：2021-06-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Daniel J. Kirtley ,  Shai Birmaher ,  Veeraraju Vanapalli ,  Karthikeyan Sampath ,  Deepak Ghiya ,  Perumallu Vukanti ,  Rajendra Mahadeorao Wankhade ,  Pradeep Naik

IPC: F23R3/00 ,  F23R3/60 ,  F02C7/18

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 liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

公开(公告)号：US12134986B1

公开(公告)日：2024-11-05

申请号：US18420337

申请日：2024-01-23

Applicant: General Electric Company

Inventor： Hiranya Kumar Nath ,  Ravindra Shankar Ganiger ,  Kwanwoo Kim ,  Dharmaraj Pachaiappan ,  Vivekta Sharma

IPC: F02C7/24

Abstract: Systems, apparatus, articles of manufacture, and methods are disclosed for an acoustic damping device. An example apparatus includes a first channel defining a first volume, the first channel open on a first end and closed on a second end, a second channel surrounding the first channel and defining a second volume, and a plurality of discs oriented within the first channel, respective discs of the plurality of discs including an opening in a center of the respective disc to allow at least one of a fluid or acoustic oscillation to move from the first end to the second end, the first channel including a plurality of apertures dispersed along an outer wall of the first channel and between the plurality of discs, the apertures to facilitate transfer of at least one of the fluid or the acoustic oscillation from the first channel to the second channel.

公开(公告)号：US12085283B2

公开(公告)日：2024-09-10

申请号：US17340764

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/42 ,  F02C3/02 ,  F02C3/14

CPC classification number: F23R3/42 ,  F02C3/02 ,  F02C3/14 ,  F05D2220/32 ,  F05D2240/35

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; and 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, wherein the forward and aft liner segments are coupled together at a moveable interface.

公开(公告)号：US20240003543A1

公开(公告)日：2024-01-04

申请号：US17853200

申请日：2022-06-29

Applicant: General Electric Company

Inventor： Ravikanth Avancha ,  Ravish Karve ,  Jeffrey Donald Clements ,  Hiranya Kumar Nath ,  Timothy Richard DePuy

IPC: F02C7/24 ,  F23R3/00

CPC classification number: F02C7/24 ,  F23R3/002 ,  F23R2900/00014

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order and together defining a working gas flowpath, the turbomachine including an acoustic liner, the acoustic liner having: a flowpath wall exposed to the working gas flowpath, the flowpath wall defining an opening; and a duct wall extending from the flowpath wall defining at least in part an acoustic passage defining a volume, the acoustic passage operable to attenuate noise through the working gas flowpath during an operating condition of the gas turbine engine.

公开(公告)号：US11835236B1

公开(公告)日：2023-12-05

申请号：US17857657

申请日：2022-07-05

Applicant: General Electric Company

Inventor： Hiranya Kumar Nath ,  Ravindra Shankar Ganiger ,  Steven Clayton Vise

IPC: F23R3/54 ,  F23R3/00 ,  F23R3/06

CPC classification number: F23R3/54 ,  F23R3/002 ,  F23R3/06 ,  F05D2240/35

Abstract: A combustor for a gas turbine engine includes a forward liner segment having an aft end portion. The forward liner segment at least partially defines a primary combustion chamber. The combustor further includes an aft liner segment having a forward end portion. A channel is defined between the forward liner segment and the aft liner segment. The channel directs a stream of dilution air in a counter-flow or reverse direction with respect to combustion gases flowing from the primary combustion chamber during operation of the combustor.

公开(公告)号：US11753965B1

公开(公告)日：2023-09-12

申请号：US17732179

申请日：2022-04-28

Applicant: General Electric Company

Inventor： Nageswar Rao Ganji ,  Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Trevor H. Wood ,  Srinivas Nuthi

IPC: F01D25/24 ,  F02C9/18

CPC classification number: F01D25/24 ,  F02C9/18 ,  F05D2250/38 ,  F05D2260/606

Abstract: Variable bleed valves with inner wall controlled-flow circuits are disclosed. An example apparatus disclosed herein includes a casing segment defining a first flow path, a variable bleed valve port defining a second flow path, and a channel formed in the casing segment, the channel including a first opening into the first flow path, and a second opening into the second flow path, the channel defining a third flow path between the first opening and the second opening.

公开(公告)号：US20230243502A1

公开(公告)日：2023-08-03

申请号：US17717603

申请日：2022-04-11

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/286 ,  F02C7/22

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 mixer. The fuel mixer can include an outer wall defining a longitudinal direction and having a mixture outlet, a first compressed air flow passage, and a second compressed air flow passage.

公开(公告)号：US20220390115A1

公开(公告)日：2022-12-08

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

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：US20220390114A1

公开(公告)日：2022-12-08

申请号：US17340764

申请日：2021-06-07

Applicant: General Electric Company

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

IPC: F23R3/42 ,  F02C3/02 ,  F02C3/14

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; and 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, wherein the forward and aft liner segments are coupled together at a moveable interface.