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公开(公告)号：US20220195937A1
公开(公告)日：2022-06-23
申请号：US17127236
申请日：2020-12-18
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw , Steve Myers , Andy M. Tibbs , Brandon P. Williams
Abstract: A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.
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公开(公告)号：US20220136446A1
公开(公告)日：2022-05-05
申请号：US17089262
申请日：2020-11-04
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw , Brandon P. Williams , Roger A. Seei
Abstract: An embodiment of a system for measuring fuel ignition within a torch igniter for a combustor in a gas turbine engine includes a housing surrounding and defining a combustion chamber, a first glow plug received through the housing, and control circuitry. An innermost end of the first glow plug extends into the combustion chamber while an outermost end opposite the innermost end extends away from the combustion chamber. The control circuitry is connected to the outermost end of the glow plug and is configured to measure a temperature of the innermost end of the glow plug based on electrical resistance of the glow plug. The control circuitry is further configured to determine an operational parameter of the torch igniter based on the temperature.
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公开(公告)号：US20220136444A1
公开(公告)日：2022-05-05
申请号：US17089236
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 comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end 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, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.
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公开(公告)号：US11149941B2
公开(公告)日：2021-10-19
申请号：US16220817
申请日：2018-12-14
Applicant: Delavan Inc.
Inventor： Lev Alexander Prociw , Jason A. Ryon
Abstract: An injection system includes a radial swirler defining an axis and including a plurality of radial swirl vanes configured to direct a radially inward flow of compressor discharge air entering swirler inlets between the radial swirl vanes in a swirling direction around the axis. The radial swirler includes an outlet oriented in an axial direction to direct swirling compressor discharge air in an axial direction. An injector ring is included radially outward from of the swirler inlets. The fuel injector ring is aligned with the axis and includes a plurality of injection orifices directed towards the swirler inlets for injecting fuel into the radial swirler.
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公开(公告)号：US11143406B2
公开(公告)日：2021-10-12
申请号：US15949787
申请日：2018-04-10
Applicant: Delavan, Inc.
Inventor： Lev Alexander Prociw , Jason A. Ryon , Gregory A. Zink
Abstract: A fuel injector for a turbomachine includes an outer heat shield configured to sit on and/or within a combustor dome to orient the fuel injector relative to the combustor dome and/or a fuel manifold. An inner surface of the outer heat shield includes an outer heat shield seal surface. The injector also includes a fuel prefilmer seated at least partially within the outer heat shield. An outer surface of the fuel prefilmer includes a prefilmer seal surface configured to mate with the outer heat shield seal surface such that the fuel prefilmer seats on the outer heat shield seal surface and such that the prefilmer seal surface is configured to allow the surfaces to slide relative to one another in both a radial and axial direction.
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Patent Agency Ranking
公开(公告)号：US11035296B2
公开(公告)日：2021-06-15
申请号：US16031724
申请日：2018-07-10
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Lev Alexander Prociw , Gregory A. Zink , Joseph Samo
Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.
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公开(公告)号：US10858997B2
公开(公告)日：2020-12-08
申请号：US16256237
申请日：2019-01-24
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Lev Alexander Prociw
IPC: B23K1/00 , F02C7/22 , F23R3/28 , B23K1/18 , B23K101/04
Abstract: A method of joining includes applying braze to a braze reservoir in a first component. A second component is engaged to the first component, wherein a joint location is defined between the first and second components. A wicking structure provides flow communication from the braze reservoir to the joint location. The method also includes joining the first and second components together at the joint location by applying heat to the braze to flow the braze from the reservoir through the wicking structure to the joint location to form a braze joint at the joint location.
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公开(公告)号：US20200018238A1
公开(公告)日：2020-01-16
申请号：US16031724
申请日：2018-07-10
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Lev Alexander Prociw , Gregory A. Zink , Joseph Samo
Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.
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公开(公告)号：US20190309948A1
公开(公告)日：2019-10-10
申请号：US15949779
申请日：2018-04-10
Applicant: Delavan, Inc.
Inventor： Lev Alexander Prociw , Jason A. Ryon , Gregory A. Zink
Abstract: A fuel injector for a multipoint injection system can include a body defining an air cavity for allowing air to flow therethrough and an interior cavity. A fuel is tube disposed at least partially within the interior cavity of the body. The fuel tube can include a first end configured to connect to a fuel injector connector of a fuel manifold, and a second end configured to connect to a fuel distributor of the fuel injector, wherein the fuel injector is configured to be disposed at least partially in a combustor dome. The fuel tube is configured to move in an axial direction to allow flexibility between the fuel manifold and the combustor dome.
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公开(公告)号：US20190195498A1
公开(公告)日：2019-06-27
申请号：US15850175
申请日：2017-12-21
Applicant: Delavan Inc.
Inventor： Lev Alexander Prociw , Jason A. Ryon , Jacob Greenfield
Abstract: A pilot nozzle for a dual fuel turbine engine includes an inner air circuit, a gaseous fuel circuit radially outward from the inner air circuit, a liquid fuel circuit radially outward from the inner air circuit, an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit, and a shroud radially outward from the outer air circuit. The shroud is configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits.
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