公开(公告)号：US11971172B2

公开(公告)日：2024-04-30

申请号：US17509470

申请日：2021-10-25

Applicant: General Electric Company

Inventor： David A. Lind ,  Ajoy Patra ,  Ting-Yu Tu ,  Pradeep Naik ,  Gregory A. Boardman

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34 ,  F23C7/00

CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R3/34 ,  F23C7/004

Abstract: A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.

公开(公告)号：US20240133553A1

公开(公告)日：2024-04-25

申请号：US17969913

申请日：2022-10-19

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: F23R3/28 ,  F02C7/22 ,  F23R3/00

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.

公开(公告)号：US11965653B2

公开(公告)日：2024-04-23

申请号：US17355689

申请日：2021-06-23

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Gregory A. Boardman

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R2900/03045

Abstract: A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.

公开(公告)号：US20230383949A1

公开(公告)日：2023-11-30

申请号：US17932806

申请日：2022-09-16

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Karthikeyan Sampath ,  Pradeep Naik ,  Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Hiranya Nath ,  Ravindra Shankar Ganiger

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042

Abstract: A combustor for a gas turbine has a combustor liner including an upstream liner portion, and a downstream liner portion. The upstream liner portion includes an outer shell and a heat shield panel, with a baffle cavity therebetween. The outer shell includes an outer shell cooling opening for providing a flow of compressed air to the baffle cavity, and the heat shield panel includes a heat shield panel cooling opening at a downstream end of the heat shield panel. A fence is arranged at a downstream side of the heat shield panel cooling opening and extends beyond a hot side surface of the heat shield panel into a combustion chamber. The heat shield panel cooling opening provides a flow of the compressed air therethrough from the baffle cavity for cooling of the heat shield panel and for providing at least partial dilution of combustion gases within the combustion chamber.

公开(公告)号：US20230366548A1

公开(公告)日：2023-11-16

申请号：US17823198

申请日：2022-08-30

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Perumallu Vukanti ,  Ajoy Patra ,  Pradeep Naik ,  Hiranya Nath

IPC: F23R3/00

CPC classification number: F23R3/005

Abstract: A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.

公开(公告)号：US11815269B2

公开(公告)日：2023-11-14

申请号：US17586082

申请日：2022-01-27

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/28

CPC classification number: F23R3/286

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

公开(公告)号：US11761632B2

公开(公告)日：2023-09-19

申请号：US17394848

申请日：2021-08-05

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Allen M. Danis ,  Scott M. Bush ,  Steven Clayton Vise ,  Hari Ravi Chandra ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Neeraj Kumar Mishra ,  Arvind Kumar Rao ,  Balasubramaniam Venkatanarayanan ,  Ranjeet Kumar Mishra

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.

公开(公告)号：US11719438B2

公开(公告)日：2023-08-08

申请号：US17201846

申请日：2021-03-15

Applicant: General Electric Company

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

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

CPC classification number: F23R3/002 ,  F23R3/06 ,  B33Y80/00 ,  F23R2900/03044

Abstract: A liner for a combustor in a gas turbine engine. The liner may include a liner body having a cold side and a hot side. The liner may include a dilution opening and a passage extending through the liner body. The passage may be positioned adjacent the dilution opening. The passage may be angled with respect to an interior surface of the liner body. A dilution flow may flow through the dilution opening from the cold side to the hot side and a secondary flow may flow through the passage from the cold side to the hot side. The secondary flow may exit into the hot side behind the dilution flow and may suppresses wakes formed behind the dilution flow on the hot side of the liner.

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：US11692708B1

公开(公告)日：2023-07-04

申请号：US17809379

申请日：2022-06-28

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Perumallu Vukanti ,  Ajoy Patra ,  Pradeep Naik ,  Hiranya Nath

IPC: F23R3/14 ,  F23R3/06

CPC classification number: F23R3/14 ,  F23R3/06 ,  F23R2900/03044

Abstract: A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber, and that a plurality of dilution openings therethrough. Each dilution opening includes an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage that extends through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall. The plurality of swirl vanes are arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.