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公开(公告)号：US11408609B2
公开(公告)日：2022-08-09
申请号：US16171941
申请日：2018-10-26
Applicant: Delavan Inc.
Inventor： Lev Alexander Prociw , Jason A. Ryon , Gregory A. Zink
Abstract: A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.
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公开(公告)号：US20220195936A1
公开(公告)日：2022-06-23
申请号：US17125114
申请日：2020-12-17
Applicant: Delavan Inc.
Inventor： Jason Ryon , Brandon P. Williams , Lev Alexander Prociw
Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.
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公开(公告)号：US20220136696A1
公开(公告)日：2022-05-05
申请号：US17089254
申请日：2020-11-04
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw
Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.
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公开(公告)号：US11131459B2
公开(公告)日：2021-09-28
申请号：US15716295
申请日：2017-09-26
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Lev Alexander Prociw , Jacob Greenfield
Abstract: An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.
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公开(公告)号：US11002193B2
公开(公告)日：2021-05-11
申请号：US15844282
申请日：2017-12-15
Applicant: Delavan Inc.
Inventor： Jacob Greenfield , Jason A. Ryon , Lev Alexander Prociw
Abstract: A turbomachine fuel injector system includes an air distributor configured to be mounted to and contained within a casing and to provide air to mix with a fuel from one or more fuel distribution systems. The system includes a fuel manifold configured to be mounted indirectly to the casing such that the fuel manifold system is contained within the casing but is independent such that fuel manifold does not touch or directly mount to either an interior of the casing or touch the air distributor within the casing to prevent or reduce thermal transfer from the air distributor to the fuel manifold.
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Patent Agency Ranking
公开(公告)号：US10941938B2
公开(公告)日：2021-03-09
申请号：US15902800
申请日：2018-02-22
Applicant: Delavan Inc.
Inventor： Andy W. Tibbs , Gregory A. Zink , Thomas J. Ocken , Lev Alexander Prociw
Abstract: In accordance with at least one aspect of this disclosure, a fuel injector can include an annular body defining a gas fuel inlet therein, and a structure extending radially outward from the annular body and configured to extend into an air circuit. The structure can include a gas channel defined within the structure at least partially along a radial length of the structure. The gas channel is in fluid communication with the gas fuel inlet where the structure meets the annular body. The structure also includes a slot opening defined at least partially along a radial length of the structure and configured to fluidically connect the gas channel and the air circuit to all gas fuel to effuse into the air circuit.
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公开(公告)号：US10830440B2
公开(公告)日：2020-11-10
申请号：US15948482
申请日：2018-04-09
Applicant: Delavan Inc.
Inventor： Lev Alexander Prociw
Abstract: A combustor for a gas turbine engine includes an inner combustor wall and an outer combustor wall radially outboard of the inner combustor wall. The inner and outer combustor walls define a combustion space therebetween with an upstream inlet and a downstream outlet. A combustor dome connects between inner and outer combustor walls at the upstream inlet of the combustion space. The combustor dome includes a plurality of circumferentially spaced apart nozzles and a plurality of tiles mounted to the combustor dome to fluidly separate a downstream side of the combustor dome from an upstream side of the combustor dome.
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公开(公告)号：US20200306703A1
公开(公告)日：2020-10-01
申请号：US16370731
申请日：2019-03-29
Applicant: Delavan Inc.
Inventor： Jason Ryon , Philip E. O. Buelow , Lev Alexander Prociw , Brandon Phillip Williams
Abstract: A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.
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89.发明授权公开(公告)号：US10578022B2
公开(公告)日：2020-03-03
申请号：US15714314
申请日：2017-09-25
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Jacob Greenfield , Lev Alexander Prociw
Abstract: A transfer tube assembly includes an outer tube defining a first flow path and an inner tube positioned within the first flow path. The inner tube defines a second flow path in fluid isolation from the first flow path. A connecting segment is downstream from the inner tube and the outer tube. The connecting segment has a first bore in fluid communication with the first flow path and a second bore in fluid communication with the second flow path.
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公开(公告)号：US10527286B2
公开(公告)日：2020-01-07
申请号：US15381609
申请日：2016-12-16
Applicant: Delavan Inc
Inventor： Lev Alexander Prociw , Jason A. Ryon
Abstract: A nozzle includes a nozzle body with an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler. A first fuel circuit is axially between the first and second radial swirlers. A second fuel circuit is axially downstream of the second radial swirler, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage. An intermediate air passage can be defined between an intermediate wall and the second radial swirler, wherein the intermediate air passage is a converging non-swirling air passage.
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