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1.发明申请公开(公告)号：US20170108291A1
公开(公告)日：2017-04-20
申请号：US15399439
申请日：2017-01-05
Applicant: General Electric Company
CPC classification number: F28F3/04 , B23P15/26 , F02C3/04 , F02C7/18 , F02K3/115 , F05D2220/323 , F05D2260/213 , F05D2260/2212 , F05D2260/22141 , F28D1/0246 , F28D1/06 , F28F1/16 , F28F3/02 , F28F3/048 , F28F3/12 , F28F13/003 , F28F13/12 , F28F21/084 , F28F2215/04 , Y02T50/671 , Y02T50/676 , Y10T29/4935
Abstract: A surface cooler includes a plate-like layer and a plurality of spaced-apart fins extending substantially perpendicular from an uppermost layer of the plate-like layer. The plurality of fins defining a plurality of air flow paths. The plurality of spaced-apart fins are configured to augment heat transfer of the surface cooler by increasing the turbulence levels of a fluid flowing through the airflow paths by promoting increased mixing with a resulting increase in the heat transfer coefficient of the surface cooler. A method of forming the surface cooler and an engine including the surface cooler.
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2.发明申请METHOD AND APPARATUS FOR DECONGEALING A LUBRICATING FLUID IN A HEAT EXCHANGER APPARATUS 有权用于在热交换器装置中分解润滑油的方法和装置公开(公告)号：US20160090863A1
公开(公告)日：2016-03-31
申请号：US14502750
申请日：2014-09-30
Applicant: General Electric Company
Inventor： Carlos Enrique Diaz , William Dwight Gerstler , Michael Ralph Storage
CPC classification number: F01D25/18 , F02C7/00 , F28D20/003
Abstract: A decongealing channel for use in a heat exchanger apparatus, including a supersaturated solution contained therein and an actuation component in fluid communication with a lubricating fluid coupled to the decongealing channel. The actuation component is responsive to a change in pressure exerted thereon by the lubricating fluid so as to actuate an exothermic response in the supersaturated solution. The heat exchanger apparatus is disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a manifold portion, one or more flow through openings extending therethrough the manifold portion to define one or more flow through channels having contained therein the lubricating fluid. In addition, the manifold portion including one or more additional openings extending therethrough to define one or more decongealing channels. Further disclosed is an engine including the heat exchanger apparatus and a method of decongealing a lubricating fluid in the heat exchanger apparatus.
Abstract translation: 一种在热交换器装置中使用的去饱和通道，包括其中所含的过饱和溶液和与连接到去饱和通道的润滑流体流体连通的致动部件。 致动部件响应于润滑流体施加在其上的压力变化，以便致动过饱和溶液中的放热响应。 热交换器装置设置在飞机发动机的旁路风扇管道中。 所述热交换器装置包括歧管部分，一个或多个流过所述歧管部分的流过开口以限定一个或多个通过其中包含润滑流体的通道。 此外，歧管部分包括一个或多个延伸穿过其中的附加开口，以限定一个或多个去饱和通道。 还公开了一种发动机，其包括热交换器装置和在热交换器装置中使润滑流体退热的方法。
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公开(公告)号：US11199132B2
公开(公告)日：2021-12-14
申请号：US16326783
申请日：2017-08-08
Applicant: General Electric Company
Inventor： Carlos Enrique Diaz , Alvaro Enrique Hernandez , Mehdi Milani Baladi , David William Kimball
Abstract: An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.
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公开(公告)号：US20150083367A1
公开(公告)日：2015-03-26
申请号：US14143233
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Carlos Enrique Diaz , William Dwight Gerstler , Michael Ralph Storage
CPC classification number: F16K31/002 , F01D25/125 , F02C7/18 , F02K3/115 , F03G7/065 , F05D2260/606 , F05D2300/505 , F28F27/02 , Y02T50/671 , Y02T50/675
Abstract: An aviation bypass valve for use in a heat exchanger apparatus, including a shape memory alloy material. The heat exchanger apparatus further including an air-cooled oil cooler disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a bypass valve in fluid communication with the air cooled oil cooler. The bypass valve including a valve body, a piston disposed in the valve body and moveable therein and an actuation component. The actuation component including a shape memory alloy. The actuation component responsive to a change in at least one of a thermal condition and a pressure exerted thereon so as to move the piston, thereby opening and closing the bypass valve.
Abstract translation: 一种用于热交换器装置的航空旁通阀，包括形状记忆合金材料。 该热交换器装置还包括设置在飞机发动机的旁通风扇导管中的空气冷却油冷却器。 该热交换器装置包括与空气冷却油冷却器流体连通的旁通阀。 旁通阀包括阀体，设置在阀体中并可在其中移动的活塞和致动部件。 致动部件包括形状记忆合金。 致动部件响应于热条件和施加在其上的压力中的至少一个的变化，以便移动活塞，从而打开和关闭旁通阀。
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公开(公告)号：US20140352315A1
公开(公告)日：2014-12-04
申请号：US13907187
申请日：2013-05-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Carlos Enrique Diaz
IPC: B64D33/10
CPC classification number: B64D33/10 , B64D29/00 , B64D2033/024 , F01D25/24 , F02C3/04 , F02C7/141 , F02C7/18 , F02K3/115 , F05D2220/32 , F05D2260/213 , Y02T50/672 , Y02T50/675
Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.
Abstract translation: 在具有包括压缩机助力器，涡轮机和机舱的压缩机的燃气涡轮发动机的飞机中，用于冷却设置到涡轮以冷却涡轮机的压缩机排出空气的系统包括设置在气体的机舱隔室中的热交换器 涡轮发动机，被配置为通过将来自压缩机排放空气的热量传递给冷却流体来冷却压缩机排放空气; 以及冷却流体回路，其被配置为使冷却流体循环通过所述热交换器和散热器，其中所述散热器是所述机舱隔室的入口，所述压缩机助力器的入口或所述燃气轮机的出口导向叶片中的至少一个 发动机。
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Patent Agency Ranking
公开(公告)号：US20190195128A1
公开(公告)日：2019-06-27
申请号：US16326783
申请日：2017-08-08
Applicant: General Electric Company
Inventor： Carlos Enrique Diaz , Alvaro Enrique Hernandez , Mehdi Milani Baladi , David William Kimball
CPC classification number: F02C7/042 , B60K11/08 , B60Y2200/50 , B60Y2200/51 , B64D27/10 , B64D27/16 , B64D29/00 , B64D33/08 , B64D2241/00 , F01D25/28 , F02C7/04 , F02C7/18 , F03G7/065 , F05D2220/323 , F05D2230/60 , F05D2270/05 , Y02T50/672 , Y02T50/675
Abstract: An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.
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7.发明申请METHOD AND APPARATUS FOR GENERATING LATENT HEAT AT LOW TEMPERATURES USING EXOTHERMIC SALT CRYSTALLIZATION 审中-公开使用高温盐析法在低温下产生热源的方法和装置公开(公告)号：US20170009118A1
公开(公告)日：2017-01-12
申请号：US14796171
申请日：2015-07-10
Applicant: General Electric Company
Inventor： Robert Edgar Colborn , William Dwight Gerstler , Carlos Enrique Diaz , Maria Rocco LaTorre
CPC classification number: C09K5/063 , F01D25/10 , F02C7/00 , F05D2260/207 , Y02T50/675
Abstract: A method and apparatus for generating latent heat at low temperatures using an exothermic salt crystallization reaction in a supersaturated solution. The method and apparatus includes a supersaturated solution including a salt-based solute in a solvent. In an embodiment, the supersaturated solution is comprised of a salt-based solute of at least 50 wt. % sodium acetate trihydrate in a solvent of 70 vol. % ethylene glycol and 30 vol. % water. The supersaturated solution remains stable at a temperature below a melting point of the salt-based solute and is triggered to crystallize in a controlled manner to generate latent heat. The method and apparatus further including an actuation component, in fluid communication with a lubricating fluid, to initiate an exothermic crystallization response in the supersaturated solution. The supersaturated solution is suitable for use in a heat exchanger apparatus of an engine. The crystallized salt will re-dissolve at elevated temperatures thus allowing for multiple use cycles.
Abstract translation: 一种用于在过饱和溶液中使用放热盐结晶反应在低温下产生潜热的方法和装置。 该方法和装置包括在溶剂中包含盐基溶质的过饱和溶液。 在一个实施方案中，过饱和溶液由至少50重量％的盐基溶质组成。 ％乙酸钠三水合物在70vol。 ％乙二醇和30体积％ ％ 水。 过饱和溶液在低于盐基溶质的熔点的温度下保持稳定，并以受控的方式触发结晶以产生潜热。 所述方法和装置还包括与润滑流体流体连通的致动部件，以在过饱和溶液中引发放热结晶响应。 过饱和溶液适用于发动机的热交换器装置。 结晶的盐将在升高的温度下再溶解，从而允许多次使用循环。
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公开(公告)号：US09422063B2
公开(公告)日：2016-08-23
申请号：US13907187
申请日：2013-05-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Carlos Enrique Diaz
CPC classification number: B64D33/10 , B64D29/00 , B64D2033/024 , F01D25/24 , F02C3/04 , F02C7/141 , F02C7/18 , F02K3/115 , F05D2220/32 , F05D2260/213 , Y02T50/672 , Y02T50/675
Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.
Abstract translation: 在具有包括压缩机助力器，涡轮机和机舱的压缩机的燃气涡轮发动机的飞机中，用于冷却设置到涡轮以冷却涡轮机的压缩机排出空气的系统包括设置在气体的机舱隔室中的热交换器 涡轮发动机，被配置为通过将来自压缩机排放空气的热量传递给冷却流体来冷却压缩机排放空气; 以及冷却流体回路，其被配置为使冷却流体循环通过所述热交换器和散热器，其中所述散热器是所述机舱隔室的入口，所述压缩机助力器的入口或所述燃气轮机的出口导向叶片中的至少一个 发动机。
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9.发明申请RETURN FLUID AIR COOLER SYSTEM FOR TURBINE COOLING WITH OPTIONAL POWER EXTRACTION 有权返回流体空气冷却系统用于涡轮机冷却与可选功率提取公开(公告)号：US20140345292A1
公开(公告)日：2014-11-27
申请号：US13900189
申请日：2013-05-22
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F02C7/047 , F05D2260/213 , Y02T50/676
Abstract: In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.
Abstract translation: 在包括燃气涡轮发动机的飞行器中，用于冷却燃气涡轮发动机的系统包括设置在飞行器的机翼中的箱，所述箱被配置为存储冷却流体供应; 以及设置在所述燃气涡轮发动机中的热交换器，其构造成将热量从所述压缩机排出空气与所述冷却流体进行交换。
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公开(公告)号：US10654579B2
公开(公告)日：2020-05-19
申请号：US15209880
申请日：2016-07-14
Applicant: General Electric Company
Inventor： Carlos Enrique Diaz
Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.
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