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公开(公告)号：US11745847B2
公开(公告)日：2023-09-05
申请号：US17114908
申请日：2020-12-08
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gregory Alexander Natsui , Brian Magann Rush
CPC classification number: B64C1/38 , B64C1/0683 , B64C3/36 , B64C30/00 , F28D15/0266 , F28D15/046
Abstract: 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.
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公开(公告)号：US11407488B2
公开(公告)日：2022-08-09
申请号：US17120674
申请日：2020-12-14
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Corey Bourassa , Douglas Carl Hofer , Gregory Alexander Natsui , Brian Magann Rush
Abstract: 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.
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公开(公告)号：US11352120B2
公开(公告)日：2022-06-07
申请号：US16685563
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Brian Magann Rush , Gregory Alexander Natsui
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, the nose cover being configured for restricting the flow of coolant until the nose cover is ablated or melted away.
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公开(公告)号：US20210147088A1
公开(公告)日：2021-05-20
申请号：US16685563
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Brian Magann Rush , Gregory Alexander Natsui
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, the nose cover being configured for restricting the flow of coolant until the nose cover is ablated or melted away.
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公开(公告)号：US20250100671A1
公开(公告)日：2025-03-27
申请号：US18472800
申请日：2023-09-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas William Rathay , Gregory Alexander Natsui
Abstract: A vehicle having a body extending between a nose section and a tail section. The nose section terminating at a tip. The body having a centerline axis extending from the tip. The nose section having an outer wall terminating at the tip. The outer wall including an outer wall centerline axis, an inner surface and an outer surface.
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Patent Agency Ranking
公开(公告)号：US20230141059A1
公开(公告)日：2023-05-11
申请号：US17524196
申请日：2021-11-11
Applicant: General Electric Company
Inventor： Constantinos Minas , Harry Kirk Mathews, JR. , Gregory Alexander Natsui , Lana Maria Osusky
CPC classification number: F01D19/02 , F01D25/12 , F05D2220/323 , F05D2260/232 , F05D2260/85 , F05D2270/3032 , F05D2270/112
Abstract: An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.
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公开(公告)号：US11577817B2
公开(公告)日：2023-02-14
申请号：US17173612
申请日：2021-02-11
Applicant: General Electric Company
Abstract: 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.
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公开(公告)号：US11427330B2
公开(公告)日：2022-08-30
申请号：US16685541
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gregory Alexander Natsui , Brian Magann Rush
Abstract: 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.
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公开(公告)号：US20220177111A1
公开(公告)日：2022-06-09
申请号：US17114908
申请日：2020-12-08
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gregory Alexander Natsui , Brian Magann Rush
Abstract: 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.
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公开(公告)号：US11260953B2
公开(公告)日：2022-03-01
申请号：US16685527
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Brian Magann Rush , Narendra Digamber Joshi , Timothy John Sommerer , Gregory Alexander Natsui , Brian Gene Brzek , Douglas Carl Hofer
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.
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