-
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
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
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
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.
-
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.
-
Patent Agency Ranking
公开(公告)号：US20230042970A1
公开(公告)日：2023-02-09
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
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：US20230033628A1
公开(公告)日：2023-02-02
申请号：US17389030
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik
Abstract: A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.
-
公开(公告)号：US20230003385A1
公开(公告)日：2023-01-05
申请号：US17367036
申请日：2021-07-02
Applicant: General Electric Company
Inventor： Pradeep Naik , Gregory A. Boardman , Vishal Sanjay Kediya
Abstract: A premixer array for a gas turbine engine includes a plurality of swirled premixer tubes and a plurality of non-swirled premixer tubes. The premixer array further includes a pilot tube for providing a pilot product. The plurality of swirled premixer tubes may guide and spread out the pilot product in a radial direction, in a circumferential direction, or both in a radial direction and a circumferential direction. The plurality of swirled premixer tubes may include clockwise swirled and counterclockwise swirled premixers. Also, included is a method of controlling the flow of pilot products.
-
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
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
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.
-
-
-
-
-
-
-
-
-
Search Results
219
records
(took 0.027 seconds)
