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.

公开(公告)号：US20230204215A1

公开(公告)日：2023-06-29

申请号：US17675270

申请日：2022-02-18

Applicant: General Electric Company

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

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

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23C7/004 ,  F23D17/002 ,  F23L7/002 ,  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：US20230204213A1

公开(公告)日：2023-06-29

申请号：US17691781

申请日：2022-03-10

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Michael T. Bucaro ,  Ajoy Patra ,  Manampathy G. Giridharan ,  Steven C. Vise ,  Michael A. Benjamin ,  Sripathi Mohan ,  R Narasimha Chiranthan ,  Joseph Zelina

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23D11/383

Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives 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. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

公开(公告)号：US11686474B2

公开(公告)日：2023-06-27

申请号：US17192613

申请日：2021-03-04

Applicant: General Electric Company

Inventor： Kwanwoo Kim ,  Clayton Cooper ,  Steven Vise ,  Shai Birmaher ,  Pradeep Naik ,  Andrew Wickersham

IPC: F23R3/28 ,  F02C7/22 ,  F23M20/00

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23M20/005 ,  F05D2240/35 ,  F05D2260/963 ,  F23R2900/00014

Abstract: A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.

公开(公告)号：US20230143185A1

公开(公告)日：2023-05-11

申请号：US17663103

申请日：2022-05-12

Applicant: General Electric Company

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

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R2900/03043

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 array having a plurality of dilution passages, each dilution passage of the plurality of dilution passages having a concatenated geometry repeating in a predetermined pattern and extending circumferentially around the liner body. The dilution passage integrates 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 injects the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor. The dilution array is repeated along an axial length of the liner body.