-
公开(公告)号：US09188063B2
公开(公告)日：2015-11-17
申请号：US13665497
申请日：2012-10-31
Applicant: DELAVAN INC
Inventor： Lev Alexander Prociw , Jason Ryon
CPC classification number: F23R3/14 , F02C7/22 , F23D11/107 , F23D2900/11101 , F23R3/10 , F23R3/12 , F23R3/28 , F23R3/286 , F23R3/30
Abstract: An injector for a multipoint combustor system includes an inner air swirler which defines an interior flow passage and a plurality of swirler inlet ports in an upstream portion thereof. The inlet ports are configured and adapted to impart swirl on flow in the interior flow passage. An outer air cap is mounted outboard of the inner swirler. A fuel passage is defined between the inner air swirler and the outer air cap, and includes a discharge outlet between downstream portions of the inner air swirler and the outer air cap for issuing fuel for combustion. The outer air cap defines an outer air circuit configured for substantially unswirled injection of compressor discharge air outboard of the interior flow passage.
Abstract translation: 用于多点燃烧器系统的喷射器包括内部空气旋流器，其在其上游部分中限定内部流动通道和多个旋流器入口。 入口端口被配置和适于在内部流动通道中产生流动的漩涡。 外部空气盖安装在内旋流器的外侧。 在内部空气旋流器和外部空气帽之间限定有燃料通道，并且在内部空气旋流器的下游部分和用于燃烧燃料的外部空气帽之间包括排出口。 外部空气帽限定了外部空气回路，该外部空气回路经配置以基本上不加注入内部流动通道外侧的压缩机排放空气。
-
公开(公告)号：US11719162B2
公开(公告)日：2023-08-08
申请号：US17686911
申请日：2022-03-04
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw
CPC classification number: F02C7/264 , F23D14/78 , F23R3/06 , B33Y80/00 , F05D2240/35 , F05D2260/232 , F05D2260/99 , F23D2214/00 , F23R2900/00018
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 the axially upstream end of the combustion chamber and situated on the axis, 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, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.
-
公开(公告)号：US11680528B2
公开(公告)日：2023-06-20
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
CPC classification number: F02C7/264 , F02C7/18 , F02C7/22 , F02C7/28 , F23R3/283 , F05D2240/35 , F05D2240/55 , F05D2260/201 , F05D2260/232 , F05D2260/30 , F05D2260/99 , F23R2900/03043 , F23R2900/03044
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.
-
公开(公告)号：US11415057B2
公开(公告)日：2022-08-16
申请号：US17089250
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 the axially upstream end of the combustion chamber and situated on the axis, 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, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.
-
35.发明申请公开(公告)号：US20220195935A1
公开(公告)日：2022-06-23
申请号：US17125107
申请日：2020-12-17
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw , Brandon P. Williams
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, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber, a tip defining the downstream end of the combustion chamber, 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 that fluidly connects the combustion chamber to the combustor. The tip is mounted through the combustor liner, the cap is downstream of the tip, and the torch igniter is downstream of the fuel nozzle and disposed radially between the combustor liner and the combustor case.
-
Patent Agency Ranking
公开(公告)号：US20220186669A1
公开(公告)日：2022-06-16
申请号：US17686911
申请日：2022-03-04
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 the axially upstream end of the combustion chamber and situated on the axis, 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, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.
-
公开(公告)号：US20220154932A1
公开(公告)日：2022-05-19
申请号：US16951631
申请日：2020-11-18
Applicant: Delavan Inc.
Inventor： Jason Ryon , Lev Alexander Prociw , Brandon P. Williams
Abstract: A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.
-
公开(公告)号：US11118785B2
公开(公告)日：2021-09-14
申请号：US16171859
申请日：2018-10-26
Applicant: Delavan Inc.
Inventor： Jason A. Ryon , Steven J. Myers , Philip E. O. Buelow , Lev Alexander Prociw
Abstract: A fuel injector for an exhaust heater includes a cover and an air blast nozzle. The cover has a nozzle seat, a fuel inlet, and an air inlet, the nozzle seat arranged along a flow axis. The air blast nozzle is seated in the nozzle seat and has a unibody. The air blast nozzle unibody is in fluid communication with the fuel inlet and the air inlet arranged along the flow axis to port fuel and air into a combustion volume, e.g., to heat a stream of exhaust gas flowing between an engine and a catalytic reactor by combustion with fuel introduced through the fuel inlet and air introduced through the air inlet.
-
公开(公告)号：US11060459B2
公开(公告)日：2021-07-13
申请号：US16031696
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.
-
公开(公告)号：US20200332998A1
公开(公告)日：2020-10-22
申请号：US16387153
申请日：2019-04-17
Applicant: Delavan Inc.
Inventor： Lev Alexander Prociw , Jason Ryon , Philip E. O. Buelow , Brandon Phillip Williams
Abstract: A fluid-gas mixer including a housing, defining a primary axis, for mixing fluid and gas, a mixer nozzle circumscribing the primary axis, wherein an annular gap between an outer surface of the mixer nozzle and an inner surface of the housing defines at least one outer gas path, a swirling gas passage defining an inner gas path for mixing with the outer gas path.
-
-
-
-
-
-
-
-
-
Search Results
98
records
(took 0.02 seconds)
