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31.发明申请公开(公告)号：US20160298500A1
公开(公告)日：2016-10-13
申请号：US14682421
申请日：2015-04-09
Applicant: General Electric Company
Inventor： Andrew Maxwell Peter , Chiranjeev Singh Kalra , Douglas Carl Hofer
IPC: F01K25/10
CPC classification number: F01K25/103 , F01K5/00 , F01K7/32 , F02C1/10 , F04D25/04
Abstract: A regenerative closed loop thermodynamic power generation cycle system is presented. The system includes a high-pressure expander to deliver an exhaust stream. A conduit is fluidly coupled to the high-pressure expander, which is configured to split the exhaust stream from the high-pressure expander into a first exhaust stream and a second exhaust stream. The system further includes a first low-pressure expander and a second low-pressure expander. The first low-pressure expander is coupled to a pressurization device through a turbocompressor shaft, and fluidly coupled to receive the first exhaust stream. The second low-pressure expander is coupled to the high-pressure expander and an electrical generator through a turbogenerator shaft, and fluidly coupled to receive the second exhaust stream. A method for operating the regenerative closed loop thermodynamic power generation cycle system is also presented.
Abstract translation: 提出了一种再生闭环热力发电循环系统。 该系统包括用于输送排气流的高压膨胀器。 管道流体耦合到高压膨胀器，高压膨胀器构造成将来自高压膨胀器的排气流分成第一排气流和第二排气流。 该系统还包括第一低压膨胀机和第二低压膨胀机。 第一低压膨胀器通过涡轮压缩机轴联接到加压装置，并且流体耦合以接收第一排气流。 第二低压膨胀机通过涡轮发电机轴联接到高压膨胀机和发电机，并且流体耦合以接收第二排气流。 还提出了一种操作再生闭环热力发电循环系统的方法。
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公开(公告)号：US20160109177A1
公开(公告)日：2016-04-21
申请号：US14515854
申请日：2014-10-16
Applicant: General Electric Company
Inventor： Ching-Jen Tang , Douglas Carl Hofer , Vitali Victor Lissianski
IPC: F25J1/00
CPC classification number: F25J1/0022 , F25J1/0055 , F25J1/0212 , F25J1/0265 , F25J2205/20 , F25J2205/84 , F25J2220/66 , F25J2240/40 , F25J2240/60
Abstract: A system for natural gas liquefaction includes a natural gas source for providing a flow of natural gas and a moisture removal system located downstream of the natural gas source. The system includes a first heat exchanger located downstream of the moisture removal system for exchanging heat between the natural gas flow path and a first refrigerant flow path of a refrigerant cycle subsystem. The system includes one first throttle valve located downstream of heat exchanger for expanding the flow of natural gas and causing reduction in pressure and temperature of the flow of natural gas. The system includes a filter subassembly for separating solid particles present in the flow of natural gas. The system includes a second heat exchanger located downstream of the filter subassembly and is configured to transfer heat from a natural gas vapor flow path to a second refrigerant flow path of the refrigeration cycle subsystem.
Abstract translation: 用于天然气液化的系统包括用于提供天然气流的天然气源和位于天然气源下游的除湿系统。 该系统包括位于除湿系统下游的第一热交换器，用于在天然气流动路径和制冷剂循环子系统的第一制冷剂流动路径之间进行热交换。 该系统包括位于热交换器下游的一个第一节流阀，用于膨胀天然气流并导致天然气流的压力和温度的降低。 该系统包括用于分离存在于天然气流中的固体颗粒的过滤器子组件。 该系统包括位于过滤器子组件下游的第二热交换器，并且构造成将热量从天然气蒸气流动路径传递到制冷循环子系统的第二制冷剂流动路径。
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33.发明申请APPARATUS FOR RECIRCULATING A FLUID WITHIN A TURBOMACHINE AND METHOD FOR OPERATING THE SAME 审中-公开用于在涡轮调节剂中回收流体的装置及其操作方法公开(公告)号：US20140119881A1
公开(公告)日：2014-05-01
申请号：US13665268
申请日：2012-10-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Chiranjeev Singh Kalra , Douglas Carl Hofer , Norman Arnold Turnquist
IPC: F01D11/00
Abstract: A turbomachine for use with a high-temperature and high-pressure working fluid is provided. The turbomachine includes a rotatable shaft and a casing enclosing the rotatable shaft, which defines at least a first and second compartment fluidly coupled together. The first compartment at least partially encloses one of a compressor and an expander. The second compartment at least partially encloses a generator. Attached to opposite ends of the rotatable shaft is a compressor for compressing the working fluid and an expansion turbine for expanding the working fluid. A motor-generator is attached to the rotatable shaft between the compressor and expansion turbine. The turbomachine includes at least one sealing system positioned between the first and second compartments that includes a number of seals for regulating the flow rate of the working fluid between the first and second compartments and for suppressing the heat and pressure transfer between the first and second compartments.
Abstract translation: 提供了一种用于高温和高压工作流体的涡轮机。 涡轮机包括可旋转的轴和包围可旋转轴的壳体，其限定至少一个流体耦合在一起的第一和第二隔室。 第一隔室至少部分地包围压缩机和膨胀机之一。 第二隔室至少部分地包围发电机。 连接到可旋转轴的相对端的是用于压缩工作流体的压缩机和用于使工作流体膨胀的膨胀涡轮机。 电动发电机连接在压缩机和膨胀涡轮机之间的可旋转轴上。 涡轮机包括位于第一和第二隔室之间的至少一个密封系统，其包括多个密封件，用于调节第一和第二隔室之间的工作流体的流速，并且用于抑制第一和第二隔室之间的热和压力传递 。
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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：US20220344740A1
公开(公告)日：2022-10-27
申请号：US17763121
申请日：2019-09-26
Applicant: General Electric Company
Inventor： Anil Raj Duggal , Richard Louis Hart , Douglas Carl Hofer
IPC: H01M10/633 , H01M10/613 , H01M10/6566 , H01M10/658 , G01R31/367
Abstract: An energy storage system is disclosed. The energy storage system includes an insulated housing defining an interior chamber, a battery disposed within the interior chamber of the insulated housing, a cooling system configured to manage a temperature of the interior chamber of the insulated housing, and a temperature controller communicatively coupled to the cooling system and comprising at least one processor in communication with at least one memory device. The at least one processor is configured to determine a reference current level at the battery, compute, based on the reference current level, a target temperature for the interior chamber of the insulated housing, and instruct the cooling system to maintain the temperature in the interior chamber of the insulated housing at the target temperature.
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Patent Agency Ranking
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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公开(公告)号：US10801549B2
公开(公告)日：2020-10-13
申请号：US15993819
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Bugra Han Ertas , Douglas Carl Hofer , Younkoo Jeong
Abstract: An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.
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公开(公告)号：US20190368549A1
公开(公告)日：2019-12-05
申请号：US15993819
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Bugra Han Ertas , Douglas Carl Hofer , Younkoo Jeong
Abstract: An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.
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公开(公告)号：US20180089361A1
公开(公告)日：2018-03-29
申请号：US15280118
申请日：2016-09-29
Applicant: General Electric Company
Inventor： Tao Guo , Michael Ernest Boisclair , Joseph Anthony Cotroneo , Douglas Carl Hofer , Amir Mujezinovic , Vsevolod Yuriyevich Ostrovskiy
CPC classification number: G06F17/5086 , F01D5/141 , F01D5/16 , F01D5/225 , F01D9/02 , F04D29/324 , F04D29/542 , F05D2220/31 , F05D2220/32 , F05D2230/50 , F05D2240/12 , F05D2240/125 , F05D2240/30 , F05D2240/307 , F05D2250/29 , F05D2260/96
Abstract: The present disclosure is directed to a method for scaling an airfoil for placement in a turbomachine. The method disclosed herein includes radially scaling a master airfoil to form a scaled airfoil. The method may also include tuning the scaled airfoil. For example, tuning the scaled airfoil may include axially scaling. The scaled airfoil generally has similar characteristics to the master airfoil.
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公开(公告)号：US20170350650A1
公开(公告)日：2017-12-07
申请号：US15171775
申请日：2016-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Douglas Carl Hofer , Joseph Philip DiPietro
CPC classification number: B01D53/002 , B01D53/229 , B01D53/26 , B01D2257/504 , F25J3/0266 , F25J2200/02 , F25J2205/40 , F25J2205/80 , F25J2210/04 , F25J2210/70 , F25J2215/04 , F25J2220/82 , F25J2230/20 , F25J2230/30 , F25J2240/90 , F25J2245/02 , F25J2270/90 , F25J2290/70 , Y02C10/10 , Y02C10/12
Abstract: A carbon dioxide capture system includes a first heat exchanger configured to exchange heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a first turboexpander including a first compressor driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor. The carbon dioxide membrane unit is configured to separate the exhaust stream into the lean carbon dioxide effluent stream and a rich carbon dioxide effluent stream. The carbon dioxide membrane unit is further configured to channel the lean carbon dioxide effluent stream to the first heat exchanger.
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