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公开(公告)号：US11879691B2
公开(公告)日：2024-01-23
申请号：US16621019
申请日：2017-06-12
Applicant: General Electric Company
Inventor： William Dwight Gerstler , Douglas Carl Hofer , Adegboyega Masud Makinde , Stephen Francis Rutkowski , Chiranjeev S. Kalra
CPC classification number: F28D21/0003 , F28F9/0132 , F28D1/0246 , F28D7/0008 , F28D7/0025 , F28D21/001 , F28D2021/0024 , F28D2021/0026 , F28F1/006 , F28F7/02 , F28F9/013 , F28F9/0246 , F28F9/182 , F28F2009/0287 , F28F2225/04 , F28F2235/00 , F28F2240/00 , F28F2250/102 , F28F2255/14
Abstract: A counter-flow heat exchanger including a core region and a plenum region. The core region including a first set of heat exchanging passageways and a second set of heat exchanging passageways disposed at least partially therein. A plenum region is disposed adjacent opposed distal ends of the core region. Each of the plenum regions including a fluid inlet plenum, a fluid outlet plenum and a tube plate disposed therebetween. The first set of heat exchanging passageways is truncated and defines a first tube-side fluid flow path in a first direction. The second set of heat exchanging passageways defines a second tube-side fluid flow path in a second opposing direction. Each of the heat exchanging passageways extending from a fluid inlet plenum to a fluid outlet plenum. The tube plates and the core region include one of a cast metal formed thereabout each of the heat exchanging passageways or a braze bond formed between each of the heat exchanging passageways.
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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：US20220158540A1
公开(公告)日：2022-05-19
申请号：US17439157
申请日：2019-03-15
Applicant: General Electric Company
Inventor： Zheyu Zhang , Ramanujam Ramabhadran , Douglas Carl Hofer , Ahmed Elasser
Abstract: A customizable power conversion system (1000) is configured to operate with multiple alternating current (AC) and direct current (DC) power sources (1001,1003) and supplies multiple AC and DC loads (1018,1020,1022,1024). The customizable power conversion system is also configured to be assembled from a plurality of customizable power converters (1004,1006,1008,1010,1012), each of which is configured to function as a building block of the customizable power conversion system. More particularly, each customizable power converter may be configured as any DC/DC, DC/AC, AC/DC, or AC/AC converter, such as any of i) an inverter, ii) a DC/DC converter for use with a photovoltaic (PV) array (or string of PV arrays), and iii) a DC/DC converter for use with an energy storage element (e.g., a battery or battery string).
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公开(公告)号：US20210147060A1
公开(公告)日：2021-05-20
申请号：US16685504
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Timothy John Sommerer , Nicholas William Rathay , Narendra Digamber Joshi , Douglas Carl Hofer , Hongbo Cao
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, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.
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公开(公告)号：US20190293117A1
公开(公告)日：2019-09-26
申请号：US15933672
申请日：2018-03-23
Applicant: General Electric Company
Inventor： Bugra Han Ertas , Douglas Carl Hofer
Abstract: Heat engines employing fluid bearing assemblies hermetically sealed with a closed flowpath for a working fluid are generally disclosed. For example, the heat engine includes a rotating drivetrain and a fluid bearing assembly. The rotating drivetrain includes a compressor section, an expander section, and a heat exchanger. The compressor section and expander section together define at least in part a closed flowpath for the flow of a working fluid. The heat exchanger is thermally coupled to the closed flowpath for adding heat to the working fluid. The fluid bearing assembly is configured to utilize the working fluid to support the rotating drivetrain. Further, the fluid bearing assembly is hermetically sealed with the closed flowpath.
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Patent Agency Ranking
公开(公告)号：US10072889B2
公开(公告)日：2018-09-11
申请号：US14749390
申请日：2015-06-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Vitali Victor Lissianski , Douglas Carl Hofer , Roger Allen Shisler , Nikolett Sipoecz , Xianyun Bi
CPC classification number: F25J1/0022 , F01D15/005 , F01K25/10 , F25J1/0035 , F25J1/0037 , F25J1/004 , F25J1/0042 , F25J1/0052 , F25J1/0087 , F25J1/0208 , F25J1/021 , F25J1/0257 , F25J1/0283 , F25J2220/64 , F25J2230/08 , F25J2230/30 , F25J2240/02 , F25J2240/04 , F25J2240/30 , F25J2240/40 , F25J2245/02
Abstract: The subject matter disclosed herein relates to a liquefaction system. Specifically, the present disclosure relates to systems and methods for condensing a pressurized gaseous working fluid, such as natural gas, using at least one turboexpander in combination with other cooling devices and techniques. In one embodiment, a turboexpander may be used in combination with a heat exchanger using vapor compression refrigeration to condense natural gas.
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公开(公告)号：US20180179952A1
公开(公告)日：2018-06-28
申请号：US15390120
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Andrew Maxwell Peter , Peter Daniel Silkowski , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Douglas Carl Hofer
CPC classification number: F02C3/16 , F01D5/02 , F02C3/04 , F02C5/02 , F02C9/28 , F05D2220/32 , F05D2240/35 , Y02E20/16
Abstract: A turbine engine includes a rotating detonation combustor including a housing defining at least one combustion chamber. The rotating detonation combustor is configured for a rotating detonation process to occur within the at least one combustion chamber to generate a combustion flow including a first portion and a second portion. The turbine engine also includes a turbine coupled in flow communication with the rotating detonation combustor. The turbine is configured to receive the combustion flow from the rotating detonation combustor. The turbine includes a first blade and a second blade that rotate about an axis at a rotational frequency. The rotating detonation combustor and the turbine are configured for the combustion flow first portion to contact the first blade substantially continuously as the first blade rotates.
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公开(公告)号：US20180179950A1
公开(公告)日：2018-06-28
申请号：US15390024
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Andrew Maxwell Peter , Peter Daniel Silkowski , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Douglas Carl Hofer
CPC classification number: F02C3/16 , F02C5/02 , F05D2240/35 , F23R7/00
Abstract: A turbine engine assembly including a plurality of rotating detonation combustors configured for a rotating detonation process to occur to produce a flow of combustion gas. The plurality of rotating detonation combustors are oriented such that the flow of combustion gas discharged therefrom flows helically relative to a centerline of the turbine engine assembly. The assembly also includes a turbine coupled downstream from the plurality of rotating detonation combustors. The turbine is configured to receive the flow of combustion gas.
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公开(公告)号：US20150354374A1
公开(公告)日：2015-12-10
申请号：US14299538
申请日：2014-06-09
Applicant: General Electric Company
Inventor： Douglas Carl Hofer , Rajiv Sampath , Edip Sevincer , Ganesh Krishnamoorthy , Chiranjeev Singh Kalra
CPC classification number: F01D5/225 , B23P15/006 , F01D5/34 , F05D2230/11 , F05D2230/25 , F05D2230/53 , Y10T29/49323
Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.
Abstract translation: 提供涡轮叶片。 涡轮叶片包括内边缘，从所述内边缘径向向外延伸的多个相邻的转子叶片，与多个相邻的转子叶片中的每一个整体连接的护罩段，从而形成多个相邻的护罩段， 在每个相邻的护罩段之间。 当扭转力施加到多个相邻的转子叶片时，该间隙具有便于将多个相邻的护罩段互锁的几何形状。
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公开(公告)号：US20150093232A1
公开(公告)日：2015-04-02
申请号：US14042881
申请日：2013-10-01
Applicant: General Electric Company
Inventor： Rajesh Kumar Venkata Gadamsetty , Chaitanya Venkata Rama Krishna Ongole , Douglas Carl Hofer , Vittorio Michelassi
CPC classification number: F04D21/00 , F04D17/02 , F04D17/08 , F04D29/284
Abstract: A supersonic compressor rotor and method of compressing a fluid is disclosed. The rotor includes a first and a second rotor disk, a first set and a second set of rotor vanes. The first set and second set of rotor vanes are coupled to and disposed between the first and second rotor disks. Further, the first set of rotor vanes are offset from the second set of rotor vanes. The rotor includes a first set of flow channels defined by the first set of rotor vanes disposed between the first and second rotor disks. Similarly, the rotor includes a second set of flow channels defined by the second set of rotor vanes disposed between the first and second rotor disks. Further, the rotor includes a compression ramp disposed on a rotor vane surface opposite to an adjacent rotor vane surface.
Abstract translation: 公开了一种超音速压缩机转子和压缩流体的方法。 转子包括第一和第二转子盘，第一组和第二组转子叶片。 第一组和第二组转子叶片联接到第一和第二转子盘之间并设置在第一和第二转子盘之间。 此外，第一组转子叶片偏离第二组转子叶片。 转子包括由设置在第一和第二转子盘之间的第一组转子叶片限定的第一组流动通道。 类似地，转子包括由设置在第一和第二转子盘之间的第二组转子叶片限定的第二组流动通道。 此外，转子包括设置在与相邻的转子叶片表面相对的转子叶片表面上的压缩斜坡。
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