-
公开(公告)号：US20230408093A1
公开(公告)日：2023-12-21
申请号：US18460078
申请日：2023-09-01
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
Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.
-
公开(公告)号：US11747019B1
公开(公告)日：2023-09-05
申请号：US17929359
申请日：2022-09-02
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin , Steven C. Vise , Perumallu Vukanti , Sripathi Mohan , Rimple Rangrej
CPC classification number: F23R3/06 , F23R3/16 , F23R3/46 , F23R3/50 , F23R2900/03043
Abstract: A combustor liner has an annular outer liner and an annular inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each has a converging-diverging section extending into the dilution zone of the combustion chamber that form a throat between them. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing a flow of an oxidizer through a respective liner to the dilution zone of the combustion chamber.
-
公开(公告)号：US20230175695A1
公开(公告)日：2023-06-08
申请号：US17653399
申请日：2022-03-03
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
CPC classification number: 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：US20250020323A1
公开(公告)日：2025-01-16
申请号：US18435033
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Rimple Rangrej , Ranganatha Narasimha , Krishnendu Chakraborty , Shai Birmaher
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.
-
公开(公告)号：US12055293B2
公开(公告)日：2024-08-06
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
CPC classification number: F23R3/06 , F23R3/002 , 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.
-
Patent Agency Ranking
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：US20230358403A1
公开(公告)日：2023-11-09
申请号：US18354167
申请日：2023-07-18
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Nalk , Daniel J. Kirtley , Rimple Rangrej , Ranganatha Narasimha Chiranthan
CPC classification number: F23R3/26 , F23R3/002 , F23R3/12 , F23R2900/03045
Abstract: A combustor for a gas turbine engine. The combustor has a combustor liner that includes a vortex turbulence generator. The vortex turbulence generator has a flow passage extending therethrough, the flow passage being defined by a wall about a periphery of the flow passage, and a plurality of vortex generating turbulators disposed on the wall, each of the plurality of vortex generating turbulators a projection portion extending from a surface of the wall into the flow passage and generating a vortex turbulent flow of an oxidizer passing through the flow passage from a cold surface side of the combustor liner to a hot surface side of the combustor liner.
-
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
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：US11592182B1
公开(公告)日：2023-02-28
申请号：US17653384
申请日：2022-03-03
Applicant: General Electric Company
Inventor： Rimple Rangrej , Pradeep Naik , Perumallu Vukanti , Saket Singh
Abstract: A swirler assembly of a combustor of a gas turbine, the swirler assembly including a primary swirler having a primary swirler flow opening, and a swirler ferrule plate connected to an upstream side of the primary swirler. The swirler ferrule plate includes (a) a fuel nozzle opening, and (b) a plurality of oxidizer purge passages surrounding the fuel nozzle opening, each one of the plurality of oxidizer purge passages including (i) an inlet passage portion, and (ii) an outlet passage portion extended from the inlet passage portion to a downstream end of the swirler ferrule plate and having an outlet in fluid communication with the primary swirler flow opening. The outlet passage portion has an increasing cross-sectional area extending along the length of the outer passage portion from the inlet passage portion to the outlet that induces a pressure drop in a flow of oxidizer through the oxidizer flow passage.
-
-
-
-
-
-
-
-
-
Search Results
44
records
(took 0.013 seconds)
