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公开(公告)号：US20240271790A1
公开(公告)日：2024-08-15
申请号：US18109555
申请日：2023-02-14
发明人： Brandon P. Williams , Jason A. Ryon , Roger Seei
摘要： A system includes an injector including a scheduling valve assembly and a nozzle in fluid communication with the scheduling valve assembly. The injector includes two fluid circuits, a primary circuit and a secondary circuit, between the inlet of the injector and two respective outlets for staged flow output. A cooling circuit is in fluid communication with the inlet of the injector. The cooling circuit is in thermal communication with the secondary circuit for selectively cooling the secondary circuit at low flow and no flow conditions of the secondary circuit. A separate valve is connected in fluid communication in the cooling circuit for controlling flow through the cooling circuit. The separate valve is configured for active control regardless of pressure at the inlet of the injector. The scheduling valve assembly is configured for passive control of the primary and secondary circuits based on pressure at the inlet of the injector.
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公开(公告)号：US20240173786A1
公开(公告)日：2024-05-30
申请号：US18428177
申请日：2024-01-31
IPC分类号： B23K1/00 , B23K31/02 , B23P15/00 , F23R3/28 , B23K26/342 , B23K101/06
CPC分类号： B23K1/0018 , B23K31/027 , B23P15/00 , F23R3/28 , B23K26/342 , B23K2101/06 , F02M2200/80 , F23R2900/00018
摘要： A method of making a fluid injection component for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining an elbow into the deposited material, wherein machining the elbow includes forming a braze joint surface in the deposited material. Depositing can include laser cladding the material onto the piece of tube stock.
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公开(公告)号：US20240035659A1
公开(公告)日：2024-02-01
申请号：US18379341
申请日：2023-10-12
发明人： Lev A. Prociw , Jason A. Ryon
IPC分类号： F23R3/00
摘要： A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.
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公开(公告)号：US20230097301A1
公开(公告)日：2023-03-30
申请号：US18074847
申请日：2022-12-05
摘要： An injection system includes an inner nozzle body defining a first air path along a longitudinal axis. The first air path defines a converging-diverging section between an upstream portion of the first air path and an outlet orifice of the first air path. A main orifice is defined at a narrowest portion of the converging-diverging section. A fuel circuit wall is outboard of the inner nozzle body. A fuel path is defined between the fuel circuit wall and the inner nozzle body. An outer nozzle body outboard of the fuel circuit wall has a second air path defined through the inner nozzle body for communication of air from the outer nozzle body into the first air path, wherein the second air path meets the first air path at a second orifice in the first air path downstream of the main orifice of the inner nozzle body.
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公开(公告)号：US20240280209A1
公开(公告)日：2024-08-22
申请号：US18111092
申请日：2023-02-17
发明人： Jason A. Ryon , Viktor Kilchyk , Eric Surawski
IPC分类号： F16L59/06 , B64G1/58 , F16L59/065 , F16L59/07
CPC分类号： F16L59/06 , B64G1/58 , F16L59/065 , F16L59/07 , F28F2013/008
摘要： A system includes a wall panel with an exterior wall. An interior wall is separated from the interior wall by a variable insulation gap occupied by an insulation medium. A flow driver is connected in fluid communication with the insulation medium. The flow driver is configured to selectively switch properties of the insulation medium in the variable insulation gap between a conduction mode and in an insulation mode. The insulation medium has a first effective thermal conductivity in the insulation mode, and a second effective thermal conductivity in the conduction mode. The first effective thermal conductively is lower than the second effective thermal conductivity.
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公开(公告)号：US20240271794A1
公开(公告)日：2024-08-15
申请号：US18141328
申请日：2023-04-28
发明人： Kevin Thompson , Jason A. Ryon
摘要： A combustor section support structure can include a fuel manifold and one or more radial stud assemblies connected to the fuel manifold and configured to allow the fuel manifold to move radially relative to an engine case and to fix the fuel manifold axially relative to the engine case. Each of the one or more radial stud assemblies can include a first portion mounted to the fuel manifold and a second portion configured to mount to an engine case. The first portion and the second portion can be configured to slide relative to each other to allow relative radial movement, but to prevent substantial axial relative movement. The first portion and the second portion form a ball joint assembly configured to allow misalignment induced rotation at the ball joint assembly.
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公开(公告)号：US20240271788A1
公开(公告)日：2024-08-15
申请号：US18109804
申请日：2023-02-14
发明人： Jason A. Ryon , Brandon P. Williams
CPC分类号： F23R3/28 , F23R3/60 , F23R2900/00005 , F23R2900/00012 , F23R2900/00017
摘要： A combustor section support structure can include a fuel manifold and one or more radial stud assemblies connected to the fuel manifold and configured to allow the fuel manifold to move radially relative to an engine case and to fix the fuel manifold axially relative to the engine case. Each of the one or more radial stud assemblies can include a first portion mounted to the fuel manifold and a second portion configured to mount to an engine case. The first portion and the second portion can be configured to slide relative to each other to allow relative radial movement, but to prevent axial relative movement. A system can include a fuel manifold configured to distribute fuel to one or more fuel nozzles of a turbomachine, and a fuel inlet assembly configured to connect to the fuel manifold through an engine case. The fuel inlet assembly can be configured to axially retain the fuel manifold relative to the engine case and to allow radial movement of the fuel manifold relative to the engine case.
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公开(公告)号：US20240068402A1
公开(公告)日：2024-02-29
申请号：US17895941
申请日：2022-08-25
CPC分类号： F02C7/232 , F23R3/28 , F05D2220/32 , F05D2240/36
摘要： A fuel injector assembly can include a housing structure defining a circular shape, and one or more fuel injectors disposed in and/or formed integrally with the housing structure. The housing structure can be configured to angle the one or more fuel injectors in a direction such that the one or more fuel injectors effuse flow in a vector having a tangential flow component.
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公开(公告)号：US11898493B2
公开(公告)日：2024-02-13
申请号：US18202662
申请日：2023-05-26
CPC分类号： F02C7/185 , F02C7/224 , F23R3/283 , F02C9/18 , F05D2260/213 , F05D2260/232 , F05D2270/303
摘要： A system includes an air manifold, a fuel manifold, and a plurality of fuel injectors. At least one of the fuel injectors includes a heat exchanger portion for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.
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公开(公告)号：US20230323811A1
公开(公告)日：2023-10-12
申请号：US18210139
申请日：2023-06-15
CPC分类号： F02C7/04 , F02C3/00 , F23R3/002 , F23R2900/03343 , F02C7/264 , F05D2220/32 , F23R3/343
摘要： An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.
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