Patents by Inventor Corey Bourassa
Corey Bourassa 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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Publication number: 20250232665Abstract: An RF communication system can include an RF transmitter, RF receiver, and a waveguide disposed between the RF transmitter and RF receiver. Each of the RF transmitter and RF receiver can include an RF antenna as well as RF electronics, the RF electronics useful to provide excitation signal to the RF antenna or to receive excitation from the RF antenna. The RF transmitter and/or RF receiver can also be a transceiver. In one form, the waveguide of the RF communication system acts as an electrical power bus. Alternatively and/or additionally, the waveguide of the RF communication system can also act as a structural member of a support structure. Alternatively and/or additionally, the waveguide of the RF communication system can also act as a heat transfer fluid circuit path. Alternatively and/or additionally, the waveguide of the RF communication system can also act as control path to convey a control signal.Type: ApplicationFiled: January 12, 2024Publication date: July 17, 2025Inventors: Gregory Alexander Natsui, Guanghua Wang, Corey Bourassa, Michael J. Dell'Anno
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Patent number: 12357933Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.Type: GrantFiled: February 15, 2024Date of Patent: July 15, 2025Assignee: General Electric CompanyInventors: Timothy Deryck Stone, Gregory Michael Laskowski, Robert Proctor, Curtis Stover, Robert Francis Manning, Victor Hugo Silva Correia, Jared Peter Buhler, Robert Carl Murray, Corey Bourassa, Byron Andrew Pritchard, Jr., Jonathan Russell Ratzlaff
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Patent number: 12345200Abstract: A turbine engine that includes a compressor section configured to receive particle-laden fluid and to at least partially compress the particle-laden fluid, and a primary fluid passageway fluidly coupled with the compressor section and including opposing first and second walls where the primary fluid passageway receives the particle-laden fluid that is compressed by the compressor section. One or more bleed holes in the first wall or the second wall fluidly couple the primary fluid passageway with an auxiliary flow passageway. At least one separator body is disposed in and extends along the primary fluid passageway. A support device couples to a portion of the at least one separator body.Type: GrantFiled: October 3, 2023Date of Patent: July 1, 2025Assignee: General Electric CompanyInventors: Satoshi Atsuchi, Corey Bourassa, James R. Noel, Erich Alois Krammer, Byron Andrew Pritchard, Mehmet Dede
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Publication number: 20250208674Abstract: A multi-domain cooling assembly configured to be coupled with one or more heat sources includes a body having an outer surface and at least one cooling chamber disposed inside the body. The at least one cooling chamber extends in at least two orthogonal dimensions and includes a working fluid to extract thermal energy from the one or more heat sources. The assembly includes a cooling channel disposed within the body and fluidly coupled with a passageway that carries cooling fluid into and out of the cooling channel. At least a portion of the cooling fluid is a liquid phase, a gas phase, or a liquid-gas mix phase. The cooling channel is fluidly separate from the at least one cooling chamber. The cooling channel is thermally coupled with the at least one cooling chamber. The at least one cooling chamber transfers thermal energy from the working fluid to the cooling fluid.Type: ApplicationFiled: March 10, 2025Publication date: June 26, 2025Inventors: Brian Magann Rush, Corey Bourassa, William Dwight Gerstler, Gary Mandrusiak
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Publication number: 20250010231Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.Type: ApplicationFiled: February 15, 2024Publication date: January 9, 2025Inventors: Timothy Deryck STONE, Gregory Michael LASKOWSKI, Robert PROCTOR, Curtis STOVER, Robert Francis Manning, Victor Hugo Silva CORREIA, Jared Peter BUHLER, Robert Carl MURRAY, Corey BOURASSA, Byron Andrew PRITCHARD, Jr., Jonathan Russell RATZLAFF
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Publication number: 20240240589Abstract: A turbine engine that includes a compressor section configured to receive particle-laden fluid and to at least partially compress the particle-laden fluid, and a primary fluid passageway fluidly coupled with the compressor section and including opposing first and second walls where the primary fluid passageway receives the particle-laden fluid that is compressed by the compressor section. One or more bleed holes in the first wall or the second wall fluidly couple the primary fluid passageway with an auxiliary flow passageway. At least one separator body is disposed in and extends along the primary fluid passageway. A support device couples to a portion of the at least one separator body.Type: ApplicationFiled: October 3, 2023Publication date: July 18, 2024Inventors: Satoshi Atsuchi, Corey Bourassa, James R. Noel, Erich Alois Krammer, Byron Andrew Pritchard, Mehmet Dede
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Patent number: 12031501Abstract: A cooling system includes a conduit extending from an upstream end to a downstream end and retains a gas. A heat exchanger is fluidly coupled with and disposed within a surface of the conduit. A portion of the gas is directed into the heat exchanger via one or more passages extending between the conduit and the heat exchanger, and a portion of the gas is directed out of the heat exchanger via the one or more passages. The heat exchanger directs cooling fluid in one or more directions within the heat exchanger along one or more passageways of plural passageways. The heat exchanger directs the portion of the gas in one or more directions within the heat exchanger along one or more other passageways of the plural passageways. The heat exchanger cools the gas by exchanging heat from the gas to the cooling fluid within the heat exchanger.Type: GrantFiled: November 27, 2019Date of Patent: July 9, 2024Assignee: General Electric CompanyInventors: Nicholas William Rathay, Corey Bourassa, Brian Magann Rush, William Dwight Gerstler
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Patent number: 11918943Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.Type: GrantFiled: November 23, 2022Date of Patent: March 5, 2024Assignee: General Electric CompanyInventors: Timothy Deryck Stone, Gregory Michael Laskowski, Robert Proctor, Curtis Stover, Robert Francis Manning, Victor Hugo Silva Correia, Jared Peter Buhler, Robert Carl Murray, Corey Bourassa, Byron Andrew Pritchard, Jr., Jonathan Russell Ratzlaff
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Patent number: 11815019Abstract: A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway.Type: GrantFiled: April 14, 2021Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: Satoshi Atsuchi, Corey Bourassa, James R. Noel, Erich Alois Krammer, Byron Andrew Pritchard, Mehmet Dede
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Patent number: 11719157Abstract: A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway.Type: GrantFiled: March 12, 2021Date of Patent: August 8, 2023Assignee: General Electric CompanyInventors: Satoshi Atsuchi, Corey Bourassa, James R. Noel, Erich Alois Krammer, Byron Andrew Pritchard, Mehmet Dede
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Publication number: 20230226476Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.Type: ApplicationFiled: November 23, 2022Publication date: July 20, 2023Inventors: Timothy Deryck STONE, Gregory Michael LASKOWSKI, Robert PROCTOR, Curtis STOVER, Robert Francis Manning, Victor Hugo Silva CORREIA, Jared Peter BUHLER, Robert Carl MURRAY, Corey BOURASSA, Byron Andrew PRITCHARD, JR., Jonathan Russell RATZLAFF
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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: 11573053Abstract: A cyclone cooler device includes a housing that defines an interior channel elongated along a center axis. One or more of the fluid passage or configuration of an inlet end of the channel is shaped to induce a swirling flow of a cooling fluid within the channel while the channel is thermally coupled with one or more heat sources. The swirling flow of the cooling fluid removes thermal energy from and cools the one or more heat sources. During the swirling flow, the cooling fluid rotates around the center axis of the channel while also moving along the length of the center axis. The cooling fluid changes phases during the swirling flow to cool the heat source(s).Type: GrantFiled: August 13, 2019Date of Patent: February 7, 2023Assignee: General Electric CompanyInventors: Hendrik Pieter Jacobus de Bock, Corey Bourassa, William Dwight Gerstler
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Patent number: 11541340Abstract: A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.Type: GrantFiled: May 20, 2021Date of Patent: January 3, 2023Assignee: General Electric CompanyInventors: Timothy Deryck Stone, Gregory Michael Laskowski, Robert Proctor, Curtis Stover, Robert Francis Manning, Victor Hugo Silva Correia, Jared Peter Buhler, Robert Carl Murray, Corey Bourassa, Byron Andrew Pritchard, Jr., Jonathan Russell Ratzlaff
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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: 20210388763Abstract: A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway.Type: ApplicationFiled: April 14, 2021Publication date: December 16, 2021Inventors: Satoshi Atsuchi, Corey Bourassa, James R. Noel, Erich Alois Krammer, Byron Andrew Pritchard, Mehmet Dede
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Patent number: 11199111Abstract: An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.Type: GrantFiled: June 15, 2020Date of Patent: December 14, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Jared Peter Buhler, Christopher Charles Glynn, Corey Bourassa, Monty Lee Shelton, Robert Francis Manning, Victor Hugo Silva Correia
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Publication number: 20210365086Abstract: A multi-domain cooling assembly configured to be coupled with one or more heat sources includes a body having an outer surface and at least one cooling chamber disposed inside the body. The at least one cooling chamber extends in at least two orthogonal dimensions and includes a working fluid to extract thermal energy from the one or more heat sources. The assembly includes a cooling channel disposed within the body and fluidly coupled with a passageway that carries cooling fluid into and out of the cooling channel. At least a portion of the cooling fluid is a liquid phase, a gas phase, or a liquid-gas mix phase. The cooling channel is fluidly separate from the at least one cooling chamber. The cooling channel is thermally coupled with the at least one cooling chamber. The at least one cooling chamber transfers thermal energy from the working fluid to the cooling fluid.Type: ApplicationFiled: August 4, 2021Publication date: November 25, 2021Inventors: Brian Magann Rush, Corey Bourassa, William Dwight Gerstler, Gary Mandrusiak