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公开(公告)号：US20230323815A1
公开(公告)日：2023-10-12
申请号：US17717402
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Gregory Alexander Natsui , Giridhar Jothiprasad , Lana Maria Osusky , Thomas Malkus
CPC classification number: F02C7/18 , F01D25/12 , F05D2260/213 , F05D2220/32 , F02C7/141
Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.
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公开(公告)号：US20210147061A1
公开(公告)日：2021-05-20
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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公开(公告)号：US12104535B2
公开(公告)日：2024-10-01
申请号：US17717402
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Gregory Alexander Natsui , Giridhar Jothiprasad , Lana Maria Osusky , Thomas Malkus
CPC classification number: F02C7/18 , F01D25/12 , F02C7/141 , F05D2220/32 , F05D2260/213
Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.
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公开(公告)号：US20230278695A1
公开(公告)日：2023-09-07
申请号：US17688085
申请日：2022-03-07
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gregory Alexander Natsui , Thomas Earl Dyson
Abstract: 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.
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公开(公告)号：US11702952B2
公开(公告)日：2023-07-18
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 , F05D2270/112 , F05D2270/3032
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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Patent Agency Ranking
公开(公告)号：US11840941B2
公开(公告)日：2023-12-12
申请号：US17673084
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lana Maria Osusky , Gustavo A. Ledezma , Daniel Endecott Osgood , Gregory Alexander Natsui
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2200/11 , F05D2200/14 , F05D2200/212 , F05D2200/221 , F05D2260/20 , F05D2260/202 , F05D2260/2214
Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation:
(
D
H
+
2
t
)
2
(
(
D
H
+
2
t
)
/
D
H
)
1
/
3
to define a performance area factor (PAF).-
公开(公告)号：US20230258091A1
公开(公告)日：2023-08-17
申请号：US17673084
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lana Maria Osusky , Gustavo A. Ledezma , Daniel Endecott Osgood , Gregory Alexander Natsui
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2260/202 , F05D2260/2214 , F05D2200/11 , F05D2200/14 , F05D2200/221 , F05D2200/212
Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation:
(
D
H
+
2
t
)
2
(
(
D
H
+
2
t
)
/
D
H
)
1
/
3
to define a performance area factor (PAF).-
公开(公告)号：US20220250734A1
公开(公告)日：2022-08-11
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：US20220185446A1
公开(公告)日：2022-06-16
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
IPC: B64C1/38
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：US20230340888A1
公开(公告)日：2023-10-26
申请号：US18341905
申请日：2023-06-27
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 , F05D2270/112 , F05D2270/3032
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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