Patents by Inventor Nicholas William Rathay
Nicholas William Rathay has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11898757Abstract: A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.Type: GrantFiled: August 3, 2021Date of Patent: February 13, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Publication number: 20240011399Abstract: An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.Type: ApplicationFiled: May 2, 2023Publication date: January 11, 2024Inventors: Thomas Earl Dyson, Nicholas William Rathay, Brendon James Leary, Gregory Terrence Garay, Gustavo Adolfo Ledezma, David Wayne Weber, Aaron Ezekiel Smith
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Patent number: 11814965Abstract: A turbomachine blade, and a coupon for a turbomachine blade, are disclosed. The blade may include an airfoil body having a pressure side and a suction side connected by a leading edge and a trailing edge, a coolant feed passage defined in the airfoil body, and a coolant reuse passage defined in the airfoil body. The blade may also include a first cooling circuit defined in the airfoil body. The first cooling circuit may include a rearward passage extending toward the trailing edge from and fluidly coupled to the coolant feed passage, and a radially spreading return passage extending away from the trailing edge toward and fluidly coupled to the coolant reuse passage. The cooling circuit may also include a radially extending turn passage coupling the rearward passage and the radially spreading return passage. A first set of obstructions may be positioned in the radially extending turn passage.Type: GrantFiled: November 10, 2021Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: Thomas Earl Dyson, Nicholas William Rathay, Adam John Fredmonski
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Publication number: 20230349298Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.Type: ApplicationFiled: June 29, 2023Publication date: November 2, 2023Inventors: Nicholas William Rathay, Thomas Earl Dyson, Brian Brzek
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Publication number: 20230278695Abstract: A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.Type: ApplicationFiled: March 7, 2022Publication date: September 7, 2023Inventors: Nicholas William Rathay, Gregory Alexander Natsui, Thomas Earl Dyson
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Patent number: 11745859Abstract: A flow control actuator includes a first side wall, a second side wall opposite and substantially parallel to the first side wall, an upstream wall mechanically coupled to upstream ends of the first and second side walls, and a downstream cap mechanically coupled to downstream ends of the first and second side walls. The first side wall, the second side wall, the upstream wall and the downstream cap collectively define an interior of the flow control actuator. An energy source is disposed in at least one of the first sidewall and the second sidewall. At least one fuel injector is disposed in the upstream wall, the first sidewall and/or the second sidewall for dispersing fuel into the flow control actuator. At least one air inlet is disposed in the upstream wall, the first sidewall and/or the second sidewall for introducing air into the flow control actuator. Fuel from fuel injector and air from the air inlet are ignited in the flow control actuator.Type: GrantFiled: August 31, 2018Date of Patent: September 5, 2023Assignee: General Electric CompanyInventors: Nicholas William Rathay, Narendra Digamber Joshi
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Patent number: 11745847Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: GrantFiled: December 8, 2020Date of Patent: September 5, 2023Assignee: General Electric CompanyInventors: Nicholas William Rathay, Gregory Alexander Natsui, Brian Magann Rush
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Patent number: 11732594Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.Type: GrantFiled: November 27, 2019Date of Patent: August 22, 2023Assignee: General Electric CompanyInventors: Nicholas William Rathay, Thomas Earl Dyson, Brian Brzek
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Patent number: 11655718Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.Type: GrantFiled: May 10, 2021Date of Patent: May 23, 2023Assignee: General Electric CompanyInventors: Thomas Earl Dyson, Nicholas William Rathay, Brendon James Leary, Gregory Terrence Garay, Gustavo Adolfo Ledezma, David Wayne Weber, Aaron Ezekiel Smith
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Publication number: 20230145370Abstract: A turbomachine blade, and a coupon for a turbomachine blade, are disclosed. The blade may include an airfoil body having a pressure side and a suction side connected by a leading edge and a trailing edge, a coolant feed passage defined in the airfoil body, and a coolant reuse passage defined in the airfoil body. The blade may also include a first cooling circuit defined in the airfoil body. The first cooling circuit may include a rearward passage extending toward the trailing edge from and fluidly coupled to the coolant feed passage, and a radially spreading return passage extending away from the trailing edge toward and fluidly coupled to the coolant reuse passage. The cooling circuit may also include a radially extending turn passage coupling the rearward passage and the radially spreading return passage. A first set of obstructions may be positioned in the radially extending turn passage.Type: ApplicationFiled: November 10, 2021Publication date: May 11, 2023Inventors: Thomas Earl Dyson, Nicholas William Rathay, Adam John Fredmonski
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Patent number: 11577817Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: GrantFiled: February 11, 2021Date of Patent: February 14, 2023Assignee: General Electric CompanyInventors: Douglas Carl Hofer, Nicholas William Rathay, Gregory Alexander Natsui, Corey Bourassa
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Patent number: 11512598Abstract: A cooling assembly comprises a coolant source chamber inside an airfoil that directs coolant inside the airfoil that extends between a hub end and a tip end that includes a tip body and tip rail along a radial length. A first body cooling chamber and a second body cooling chamber are disposed inside the tip body. The second body cooling chamber is positioned between the tip end and the first body cooling chamber. At least one of the first or second body cooling chambers are fluidly coupled with the coolant source chamber. The coolant source chamber directs the coolant into the first or second body cooling chambers. A rail cooling chamber disposed inside of the tip rail is fluidly coupled with the first or second body cooling chambers. The first or second body cooling chambers directs coolant out of the body cooling chambers and into the rail cooling chamber.Type: GrantFiled: March 14, 2018Date of Patent: November 29, 2022Assignee: General Electric CompanyInventors: Nicholas William Rathay, Travis Packer, Keith Lord, Jeffrey Jones, Jacob Kittleson, Gustavo Ledezma
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Publication number: 20220364528Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.Type: ApplicationFiled: July 14, 2022Publication date: November 17, 2022Inventors: Nicholas William Rathay, Timothy John Sommerer, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11486259Abstract: An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.Type: GrantFiled: November 5, 2021Date of Patent: November 1, 2022Assignee: General Electric CompanyInventors: Daniel Endecott Osgood, Kirk Douglas Gallier, Zachary Daniel Webster, Gregory Terrence Garay, Nicholas William Rathay, Daniel Lee Durstock
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Patent number: 11427330Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.Type: GrantFiled: November 15, 2019Date of Patent: August 30, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Gregory Alexander Natsui, Brian Magann Rush
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Patent number: 11415080Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.Type: GrantFiled: May 14, 2018Date of Patent: August 16, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Timothy John Sommerer, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Publication number: 20220250734Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: ApplicationFiled: February 11, 2021Publication date: August 11, 2022Inventors: Douglas Carl Hofer, Nicholas William Rathay, Gregory Alexander Natsui, Corey Bourassa
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Patent number: 11407488Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: GrantFiled: December 14, 2020Date of Patent: August 9, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Corey Bourassa, Douglas Carl Hofer, Gregory Alexander Natsui, Brian Magann Rush
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Publication number: 20220185446Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: ApplicationFiled: December 14, 2020Publication date: June 16, 2022Inventors: Nicholas William Rathay, Corey Bourassa, Douglas Carl Hofer, Gregory Alexander Natsui, Brian Magann Rush
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Publication number: 20220177111Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.Type: ApplicationFiled: December 8, 2020Publication date: June 9, 2022Inventors: Nicholas William Rathay, Gregory Alexander Natsui, Brian Magann Rush