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11. 发明授权

US06457315B1 Hybrid refrigeration cycle for combustion turbine inlet air cooling 有权
标题翻译：燃气轮机入口空气冷却的混合制冷循环
公开(公告)号：US06457315B1
公开(公告)日：2002-10-01
申请号：US10020085
申请日：2001-12-07
申请人： Rong-Jwyn Lee , Jong Juh Chen , Jame Yao , Douglas G. Elliot , Pallav Jain
发明人： Rong-Jwyn Lee , Jong Juh Chen , Jame Yao , Douglas G. Elliot , Pallav Jain
IPC分类号： F02C100
CPC分类号： F02C7/143 , F02C7/16 , F05D2210/14 , Y02T50/675
摘要： A method and apparatus for enhancing the power output and operational efficiency of a combustion turbine system using a combined refrigerant substantially comprising a first refrigerant and a second refrigerant, whereby the combined refrigerant exhibits a total pressure substantially greater than each respective first and second refrigerant at a temperature inside an evaporative chiller. In a preferred embodiment, the combined refrigerant cools turbine inlet air through the exchange of heat from the inlet air, in an air chiller, with a coolant which is cooled by the combined refrigerant in the evaporative chiller. The combined refrigerant, after it is used to cool the coolant in the evaporative chiller, is separated through the use of a liquid absorbent which absorbs the second refrigerant to form a solution pair. The non-absorbed first refrigerant is compressed, condensed and then recirculated to eventually join the second refrigerant which is desorbed from the solution pair in a regenerator. The economic advantage of the present invention is enhanced by thermally linking the heat required to regenerate the second absorptive refrigerant from the solution pair with the hot exhaust of heat available from the gas turbine.
摘要翻译：一种用于使用基本上包括第一制冷剂和第二制冷剂的组合制冷剂来提高燃料涡轮机系统的功率输出和操作效率的方法和装置，由此组合的制冷剂表现出总体压力基本上大于相应的第一和第二制冷剂的总压力蒸发式冷水机内部温度。在一个优选实施例中，组合的制冷剂通过来自空气冷却器中的入口空气的热量与通过蒸发式冷却器中的组合制冷剂冷却的冷却剂来冷却涡轮机入口空气。组合的制冷剂在用于冷却蒸发冷却器中的冷却剂之后，通过使用吸收第二制冷剂以形成溶液对的液体吸收剂分离。未吸收的第一制冷剂被压缩，冷凝，然后再循环，以最终连接在再生器中从溶液对解吸的第二制冷剂。通过将从溶液对再生第二吸收性制冷剂所需的热与从燃气轮机获得的热的热排出热连接来增强本发明的经济优势。

12. 发明授权

US09410478B2 Intercooled gas turbine with closed combined power cycle 有权
标题翻译：具有闭合组合动力循环的中间燃气轮机
公开(公告)号：US09410478B2
公开(公告)日：2016-08-09
申请号：US14134427
申请日：2013-12-19
申请人： Rolls-Royce North American Technologies, Inc.
发明人： James C. Loebig , Robert Manning
IPC分类号： F02C7/143 , F02C3/04 , F02C7/12 , F02K3/06
CPC分类号： F02C3/04 , F02C7/12 , F02C7/143 , F02K3/06 , F05D2210/14 , F05D2220/62 , F05D2220/72 , F05D2220/76 , Y02T50/675 , Y10T29/49229
摘要： A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.
摘要翻译：涡轮发动机包括风扇，其作为压缩机进气和作为压缩机旁路空气向涡轮发动机提供空气流，定位成接收压缩机进气并输出第一级压缩空气的第一级压缩机和定位成冷却的锅炉使用流体的第一级压缩空气。第二级压缩机定位成接收冷却的第一级压缩空气。泵被配置为将流体作为液体泵送到锅炉中，从第一级压缩空气中提取能量，并使第一级压缩空气冷却。

13. 发明申请

US20150198380A1 HEAT TRANSFER DEVICE FOR HIGH HEAT FLUX APPLICATIONS AND RELATED METHODS THEREOF 审中-公开
标题翻译：用于高热通量应用的热传递装置及其相关方法
公开(公告)号：US20150198380A1
公开(公告)日：2015-07-16
申请号：US14415423
申请日：2013-07-18
申请人： University of Virginia Patent Foundation
发明人： Hossein Haj-Hariri , Seyed Reza Monazami Miralipour
IPC分类号： F28D15/04 , F25B21/02
CPC分类号： F28D15/04 , B64G1/50 , B64G1/58 , F01D5/187 , F05D2210/14 , F05D2260/207 , F05D2260/213 , F25B21/02 , F28D15/02 , F28D15/046 , F28F13/187 , H01L23/427 , H01L2924/0002 , Y02T50/676 , H01L2924/00
摘要： A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, 10 prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using a non-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members.
摘要翻译：提供但不限于此的具有增强的蒸发和增加的冷却能力的独特组合的两相传热装置的装置和相关方法。与装置和方法相关的优点包括但不限于：每单位面积的增加的冷却能力，受控和优化的蒸发，10防止沸腾以及防止蒸发器的干燥。与方法相关的一个方面可以包括但不限于此，使用非润湿涂层或结构来保持工作流体远离蒸发器的细长构件之间的空间并使用润湿涂层或结构来形成工作薄膜围绕细长构件的远侧区域的流体。

14. 发明申请

WO02004788A1 TURBINE, POWER GENERATION SYSTEM THEREFOR AND METHOD OF POWER GENERATION 审中-公开
标题翻译：发电机，发电系统及其发电方法
公开(公告)号：WO02004788A1
公开(公告)日：2002-01-17
申请号：PCT/AU2001/000813
申请日：2001-07-06
IPC分类号： F01D1/36 , F01D15/00 , F25B11/00 , F25B27/00 , F25B40/00 , H01L35/00 , F01D1/08 , F01D5/04 , F01D9/02 , F01D17/14
CPC分类号： F01D15/005 , F01D1/36 , F05D2210/14 , F25B11/00 , F25B27/00 , F25B40/00 , H01L35/00
摘要： A turbine includes a rotor (2) rotatable within a rotor chamber including a plurality of blades (5) about its periphery. Drag surfaces are created by the plurality of disc surfaces in the rotor (2), five discs being shown, and these receive a working fluid which is caused to flow spirally towards a central aperture (7) in the rotor (2). The working fluid may be provided at hypersonic or lower speeds and may be provided by a fuel burning means. A thermoelectric generator utilising the turbine is also disclosed.
摘要翻译：涡轮机包括在包括围绕其周边的多个叶片（5）的转子室内可旋转的转子（2）。通过转子（2）中的多个盘表面产生拖动表面，示出了五个盘，并且这些盘接收工作流体，螺旋地朝向转子（2）中的中心孔（7）流动。工作流体可以以超音速或低速提供，并且可以由燃料燃烧装置提供。还公开了一种利用涡轮机的热电发电机。

15. 发明申请

WO2015088109A1 초임계유체 냉각 가스터빈 장치 审中-公开
标题翻译：超临界流体冷却气体涡轮装置
公开(公告)号：WO2015088109A1
公开(公告)日：2015-06-18
申请号：PCT/KR2014/003547
申请日：2014-04-29
申请人： 연세대학교 산학협력단
发明人： 조형희 , 김경민 , 문호규 , 김범석 , 박준수 , 김선호
IPC分类号： F02C7/14 , F02C7/12
CPC分类号： F02C7/18 , F02C1/08 , F02C6/18 , F02C7/12 , F02C7/16 , F05D2210/14 , F23M5/08 , F23R3/005
摘要： 본 발명의 일측면에 따르면, 공기를 압축하는 압축기, 압축기로부터 배출된 공기와 연료가 연소되는 연소기 및 연소기로부터 배출되는 연소 가스로 구동되는 터빈을 구비한 가스 터빈 장치에 있어서,연소기 및 터빈에는 냉각유로가 설치되고, 냉각유로로 초임계유체를 냉각유체로서 흘려 연소기 및 터빈을 냉각하는 것을 특징으로 하는 초임계유체 냉각 가스터빈 장치가 제공될 수 있다.
摘要翻译：根据本发明的一个方面，提供一种超临界流体冷却燃气轮机装置，包括：用于压缩空气的压缩机; 用于燃烧从压缩机排出的燃料和空气的燃烧器; 以及由从燃烧器排出的燃烧气体驱动的涡轮，其中在燃烧器中设置冷却通道，并且通过作为冷却流体的超临界流体流过冷却通道而使燃烧器和涡轮机冷却。

16. 发明申请

US20160273549A1 CENTRIFUGAL COMPRESSOR ASSEMBLY AND METHOD 审中-公开
公开(公告)号：US20160273549A1
公开(公告)日：2016-09-22
申请号：US15167128
申请日：2016-05-27
申请人： TRANE INTERNATIONAL INC.
发明人： Paul F. Haley , Rick T. James
IPC分类号： F04D29/46 , F25B39/00 , F25B1/10 , F04D29/42 , F25B1/053
CPC分类号： F04D29/462 , F04D29/4213 , F05D2210/14 , F05D2240/128 , F05D2250/51 , F25B1/053 , F25B1/10 , F25B39/00 , F25B39/02 , F25B2339/0242
摘要： A centrifugal compressor assembly for compressing refrigerant in a 250-ton capacity or larger chiller system comprising a motor, preferably a compact, high energy density motor or permanent magnet motor, for driving a shaft at a range of sustained operating speeds under the control of a variable speed drive. Another embodiment of the centrifugal compressor assembly comprises a mixed flow impeller and a vaneless diffuser sized such that a final stage compressor operates with an optimal specific speed range for targeted combinations of head and capacity, while a non-final stage compressor operates above the optimum specific speed of the final stage compressor. Another embodiment of the centrifugal compressor assembly comprises an integrated inlet flow conditioning assembly comprising a flow conditioning nose, a plurality of inlet guide vanes and a flow conditioning body that positions inlet guide vanes to condition flow of refrigerant into an impeller to achieve a target approximately constant angle swirl distribution with minimal guide vane turning.

17. 发明申请

US20150167554A1 GAS TURBINE DEVICE USING SUPERCRITICAL FLUID AS COOLING FLUID 有权
标题翻译：使用超临界流体作为冷却流体的气体涡轮装置
公开(公告)号：US20150167554A1
公开(公告)日：2015-06-18
申请号：US14262970
申请日：2014-04-28
申请人： INDUSTRY-ACADEMIC COOPERATION FOUNDATION YONSEI UNIVERSITY
发明人： Hyung Hee CHO , Kyung Min KIM , Ho Kyu MOON , Beom Seok KIM , Jun Su PARK , Seon Ho KIM
IPC分类号： F02C7/18 , F02C3/04
CPC分类号： F02C7/18 , F02C1/08 , F02C6/18 , F02C7/12 , F02C7/16 , F05D2210/14 , F23M5/08 , F23R3/005
摘要： The present invention relates to a gas turbine device using a supercritical fluid as a cooling fluid, the gas turbine device having a compressor for compressing air, a combustor for burning the air emitted from the compressor and fuel, and a turbine driven by the burned gas emitted from the combustor, wherein the gas turbine device includes cooling passages formed in the combustor and the turbine, along which the supercritical fluid as a cooling fluid flows to allow the combustor and the turbine to be cooled.
摘要翻译：本发明涉及一种使用超临界流体作为冷却流体的燃气轮机装置，该燃气轮机装置具有用于压缩空气的压缩机，用于燃烧从压缩机和燃料排出的空气的燃烧器以及由燃烧气体驱动的涡轮机从燃烧器排出的燃气涡轮机装置包括形成在燃烧器和涡轮机中的冷却通道，作为冷却流体的超临界流体沿着该涡轮流动以允许燃烧器和涡轮机被冷却。

18. 发明申请

US20140352317A1 INTERCOOLED GAS TURBINE WITH CLOSED COMBINED POWER CYCLE 有权
标题翻译：具有闭合组合功率循环的混合气体涡轮机
公开(公告)号：US20140352317A1
公开(公告)日：2014-12-04
申请号：US14134427
申请日：2013-12-19
申请人： Rolls-Royce North American Technologies, Inc.
发明人： James C. Loebig , Robert Manning
IPC分类号： F02C3/04 , F02C7/12
CPC分类号： F02C3/04 , F02C7/12 , F02C7/143 , F02K3/06 , F05D2210/14 , F05D2220/62 , F05D2220/72 , F05D2220/76 , Y02T50/675 , Y10T29/49229
摘要： A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.
摘要翻译：涡轮发动机包括风扇，其作为压缩机进气和作为压缩机旁路空气向涡轮发动机提供空气流，定位成接收压缩机进气并输出第一级压缩空气的第一级压缩机和定位成冷却的锅炉使用流体的第一级压缩空气。第二级压缩机定位成接收冷却的第一级压缩空气。泵被配置为将流体作为液体泵送到锅炉中，从第一级压缩空气中提取能量，并使第一级压缩空气冷却。

19. 发明申请

US20140216034A1 Thermal Power Generation System and Method for Generating Thermal Electric Power 有权
标题翻译：热电发电系统及其发电方法
公开(公告)号：US20140216034A1
公开(公告)日：2014-08-07
申请号：US14081500
申请日：2013-11-15
申请人： Hitachi, Ltd.
发明人： Shohei NUMATA , Susumu NAKANO , Takanori SHIBATA , Hidefumi ARAKI
IPC分类号： F01K13/00
CPC分类号： F01K13/00 , F01K25/103 , F02C3/30 , F02C3/34 , F02C6/18 , F05D2210/12 , F05D2210/14 , Y02E20/16 , Y02E20/344 , Y02E50/11 , Y02E60/15
摘要： A thermal power generation system includes a combustor burning oxygen and fuel with supercritical CO2, a turbine driven by the supercritical CO2 and water vapor fed from the combustor, a low-pressure supercritical CO2 storage storing low-pressure supercritical CO2 from the turbine, a compressor compressing the low-pressure supercritical CO2, a high-pressure supercritical CO2 storage storing high-pressure supercritical CO2 from the compressor, and a high-pressure supercritical CO2 feeder supplying between the high-pressure supercritical CO2 storage and the combustor, in which the high-pressure supercritical CO2 feeder supplies the high-pressure supercritical CO2 to the combustor at a constant pressure. Thus, the thermal power generation system can perform adjustment of an electric power supply required to use unstable renewable energy sources such as solar and wind power, can achieve high efficiency power generation with high temperature working fluid, and can reduce emissions of environmental load substances such as NOx and CO2.
摘要翻译：火力发电系统包括燃烧氧和燃料的燃烧器，其具有超临界CO 2，由超临界CO2驱动的涡轮机和从燃烧器供给的水蒸气，低压超临界CO 2储存器，其存储来自涡轮机的低压超临界CO 2，压缩机压缩来自压缩机的高压超临界CO 2储存高压超临界CO 2的高压超临界CO 2储存器和在高压超临界CO 2储存器和燃烧器之间供给的高压超临界CO 2进料器，其中高压压力超临界CO 2进料器以恒定的压力向燃烧室提供高压超临界CO 2。因此，火力发电系统可以对使用太阳能和风力发电等不稳定的可再生能源所需的电力供应进行调整，可以通过高温工作流体实现高效率发电，并且可以减少环境负荷物质的排放，例如作为NOx和CO2。

20. 发明授权

US09909574B1 Electrothermal space thruster heater for decomposable propellants 有权
公开(公告)号：US09909574B1
公开(公告)日：2018-03-06
申请号：US15143857
申请日：2016-05-02
申请人： CU Aerospace, LLC
发明人： Neil J. Heimanowski , Curtis A. Woodruff , Rodney L. Burton , David L. Carroll
IPC分类号： F03H1/00 , F02K9/97 , F02K9/42 , F02K9/62
CPC分类号： F03H1/0093 , B64G1/26 , B64G1/406 , F02K9/425 , F02K9/62 , F02K9/97 , F05D2210/14
摘要： A method for operating self-pressurizing propellants in space thruster chambers and nozzles heated by resistive, radiative or nuclear methods at temperatures hundreds of degrees above the decomposition temperature. The method is defined by reducing the chamber volume Vc and increasing the nozzle throat area A* such that a propellant vapor with sonic velocity a* experiences a high temperature residence time that is less than 10 milliseconds. In other aspects of the invention propellant vapor is formed from a self-pressurizing propellant and the residence time is such that the propellant vapor does not decompose nor does the propellant vapor polymerize to a solid.

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