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公开(公告)号：US20230144971A1
公开(公告)日：2023-05-11
申请号：US17663093
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
CPC classification number: F23R3/06 , F23R3/16 , F23R2900/03045
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 passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate 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 (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
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公开(公告)号：US20230094199A1
公开(公告)日：2023-03-30
申请号：US17649218
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Rimple Rangrej , Krishnendu Chakraborty
IPC: F23R3/26
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. The outer liner has an annular outer liner slot dilution opening, with a plurality of outer liner swirl vanes disposed within the annular outer liner slot dilution opening. The inner liner of the combustor liner includes an annular inner liner slot dilution opening, and also includes a plurality of inner liner swirl vanes disposed within the annular inner liner slot dilution opening.
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公开(公告)号：US20220412560A1
公开(公告)日：2022-12-29
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
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.
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公开(公告)号：US20220390110A1
公开(公告)日：2022-12-08
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
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 a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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公开(公告)号：US11454396B1
公开(公告)日：2022-09-27
申请号：US17340614
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Gregory A. Boardman , Vishal Sanjay Kediya , Pradeep Naik , Jeffrey M. Martini
Abstract: A fuel injector and mini-mixer system includes a mixing element tube configured to mix air and fuel prior to injecting the air and fuel into a combustor, an injector positioned within the mixing element tube, the injector being configured to inject a fluid into the mixing element tube, one or more air inlet slots positioned on one or more sides of the injector, one or more fuel injection holes configured to inject fuel into the mixing element tube, and one or more delta wing vortex generators positioned within an internal wall of the mixing element tube, the one or more delta wing vortex generators configured to generate a vortex pair that accelerates the mixing of air and fuel injected into the mixing element tube. Additional air slots can be provided downstream of the delta wing vortex generators to energize the vortex pair or lift fuel away to prevent flameholding.
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Patent Agency Ranking
公开(公告)号：US20220290861A1
公开(公告)日：2022-09-15
申请号：US17201846
申请日：2021-03-15
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Rimple Rangrej , Saket Singh , Pradeep Naik
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.
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公开(公告)号：US10976053B2
公开(公告)日：2021-04-13
申请号：US15793129
申请日：2017-10-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly includes a volute wall extended annularly around a combustor centerline, extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline, and defining a combustion chamber therewithin, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, an annular outer wall extended at least partially along the lengthwise direction from the volute wall, the annular inner wall and the annular outer wall being separated along a radial direction from the combustor centerline, and a primary flow passage being defined between the annular inner wall and the annular outer wall in fluid communication with the combustion chamber, and a flow passage wall extending between a portion of the volute wall and a portion of the annular outer wall.
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公开(公告)号：US10976052B2
公开(公告)日：2021-04-13
申请号：US15793104
申请日：2017-10-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.
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公开(公告)号：US10808934B2
公开(公告)日：2020-10-20
申请号：US15865809
申请日：2018-01-09
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Jeffrey Michael Martini , Michael Anthony Benjamin , Pradeep Naik
Abstract: A fuel injector for a gas turbine engine including an outer sleeve. An upstream end of the outer sleeve defines an inlet opening and a downstream end defines an exit opening, each of which defined within the outer sleeve. The outer sleeve defines a radial opening extended therethrough along the radial direction. At least a portion of the outer sleeve defines a plurality of grooves. The outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline. The fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve. A first member of an arm is coupled to the outer sleeve. A second member of the arm is contoured defining a fuel injection port generally concentric to the fuel injector centerline.
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公开(公告)号：US20200025385A1
公开(公告)日：2020-01-23
申请号：US16375958
申请日：2019-04-05
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini
Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.
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