专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO1998002643A1 MICROTURBOMACHINERY 审中-公开
公开(公告)号：WO1998002643A1
公开(公告)日：1998-01-22
申请号：PCT/US1997012137
申请日：1997-07-14
申请人： MASSACHUSETTS INSTITUTE OF TECHNOLOGY
发明人： MASSACHUSETTS INSTITUTE OF TECHNOLOGY , EPSTEIN, Alan, H. , SENTURIA, Stephen, D. , WAITZ, Ian, A. , LANG, Jeffrey, H. , JACOBSON, Stuart, A. , EHRICH, Fredric, F. , SCHMIDT, Martin, A. , ANANTHASURESH, G., K. , SPEARING, Mark, S. , BREUER, Kenneth, S. , NAGLE, Steven, F.
IPC分类号： F01D05/28
CPC分类号： F23R3/42 , F01D5/28 , F01D15/06 , F01D25/20 , F01K13/00 , F02C3/05 , F02K9/48 , F05D2220/50 , F05D2230/14 , F05D2250/82 , F05D2250/84 , F05D2300/2261 , F05D2300/2283 , F05D2300/607 , F23C2900/03001
摘要： The invention provides a micro-gas turbine engine and associated microcomponentry. The engine components, including, e.g., a compressor, a diffuser having diffuser vanes, a combustion chamber, turbine guide vanes, and a turbine are each manufactured by, e.g., microfabrication techniques, of a structural material that can be common to all of the elements, e.g., a microelectronic material such as silicon or silicon carbide. Vapor deposition techniques, as well as bulk wafer etching techniques, can be employed to produce the engine. The engine includes a rotor having a shaft with a substantially untapered compressor disk on a first end, defining a centrifugal compressor, and a substantially untapered turbine disk on the opposite end, defining a radial inflow turbine. The rotor is preferably formed of a material characterized by a strength-to-density ratio that enables a rotor speed of at least about 500,000 rotations per minute. An annular, axial-flow combustion chamber is provided that is located axially between the compressor and turbine disks and that has a ratio of annular height to axial length of at least about 0.5. The micro-gas turbine engine can be configured with an integral microgenerator as a source of electrical power, and can be employed for a wide range of power, propulsion, and thermodynamic cycle applications.
摘要翻译：本发明提供一种微型燃气涡轮发动机和相关的微型部件。包括例如压缩机，具有扩散器叶片的扩散器，燃烧室，涡轮引导叶片和涡轮机的发动机部件各自通过例如微细加工技术来制造，所述结构材料可以是所有的元件，例如微电子材料，例如硅或碳化硅。可以采用气相沉积技术以及体晶片蚀刻技术来制造发动机。发动机包括具有轴的转子，其具有在第一端上具有基本上未经紧固的压缩机盘，限定离心压缩机的轴和在相对端上的基本上未配套的涡轮盘，限定径向流入涡轮机。转子优选地由特征在于强度与密度之比的材料形成，其能够使转子速度为每分钟至少大约50万转。提供了一种环形的轴向流动燃烧室，其轴向位于压缩机和涡轮盘之间，并且具有至少约0.5的环形高度与轴向长度的比率。微型燃气涡轮发动机可以配置有一个整体的微型发电机作为电力来源，并且可以用于广泛的动力，推进和热循环应用。

2. 发明申请

WO2004059147A3 HETEROSCOPIC TURBINE 审中-公开
标题翻译：异位涡轮
公开(公告)号：WO2004059147A3
公开(公告)日：2005-07-14
申请号：PCT/US0339999
申请日：2003-12-16
申请人： FORCED PHYSICS CORP
发明人： DAVIS SCOTT
IPC分类号： F04D19/04 , F04D29/58 , F28F13/00 , F03D3/06
CPC分类号： F28F13/02 , B82Y15/00 , F01D1/36 , F04D19/042 , F04D29/582 , F04D33/00 , F05D2250/82 , F05D2250/84 , F28F13/00
摘要： A heteroscopic turbine with a Knudsen number of less than ten. In one embodiment, the heteroscopic turbine generates a flow (7) from a gas. The turbine includes at least a moving surface (1) and a plurality of turbine blades (5, 11) on or in said surface. Each of the blades has a height comparable to a mean free path distance that characterizes molecules in the gas, and the blades are spaced apart by a distance comparable to the mean free path distance. In operation, the surface moves such that the turbine blades pass through the gas at a speed comparable to the mean thermal velocity. In different embodiments, the turbine can perform filtering of molecules in the gas based on direction and/or speed (velocity). Also, techniques by which such a turbine operates.
摘要翻译：具有Knudsen数小于10的异型涡轮机。在一个实施例中，异型透视涡轮从气体产生流（7）。涡轮机包括在所述表面上或所述表面中的至少一个移动表面（1）和多个涡轮机叶片（5,11）。每个叶片具有与表征气体中的分子的平均自由程距离相当的高度，并且叶片间隔开与平均自由程距离相当的距离。在操作中，表面移动，使得涡轮叶片以与平均热速度相当的速度通过气体。在不同的实施例中，涡轮机可以基于方向和/或速度（速度）执行气体中分子的过滤。而且，这种涡轮机运行的技术也是如此。

3. 发明申请

WO2004059265A2 MOLECULAR SPEED AND DIRECTION SELECTION 审中-公开
标题翻译：分子速度和方向选择
公开(公告)号：WO2004059265A2
公开(公告)日：2004-07-15
申请号：PCT/US0339998
申请日：2003-12-16
申请人： FORCED PHYSICS CORP
发明人： DAVIS SCOTT
IPC分类号： F04D19/04 , F04D29/58 , F28F13/00 , G01J
CPC分类号： F28F13/02 , B82Y15/00 , F01D1/36 , F04D19/042 , F04D29/582 , F04D33/00 , F05D2250/82 , F05D2250/84 , F28F13/00
摘要： A technique of generating a flow (7) from a gas. The technique includes the steps of selecting molecules from the gas on a nanoscopic or microscopic scale, and generating the flow from the selected molecules. The gas can be air. In one embodiment, the molecules are selected based on the direction of movement of the molecules. In another embodiment, the molecules are selected based on the velocities (i.e., direction and speed) of the molecules. Also, devices that implement the technique.
摘要翻译：从气体产生气流（7）的技术。该技术包括从纳米级或微观尺度的气体中选择分子并从所选分子产生流动的步骤。气体可以是空气。在一个实施方案中，根据分子的运动方向来选择分子。在另一个实施方案中，基于分子的速度（即方向和速度）来选择分子。此外，实施该技术的设备。

4. 发明申请

WO2004057260A2 HEAT EXCHANGE TECHNIQUE 审中-公开
标题翻译：热交换技术
公开(公告)号：WO2004057260A2
公开(公告)日：2004-07-08
申请号：PCT/US2003/040637
申请日：2003-12-19
申请人： FORCED PHYSICS CORPORATION
发明人： DAVIS, Scott
IPC分类号： F28F
CPC分类号： F28F13/02 , B82Y15/00 , F01D1/36 , F04D19/042 , F04D29/582 , F04D33/00 , F05D2250/82 , F05D2250/84 , F28F13/00
摘要： A method and device that transfers heat to or from a gas. The method includes the steps of moving a surface with sufficient speed to disrupt a velocity boundary layer for molecules of the gas in contact with the surface, and cooling or heating the surface. The surface can be a heteroscopic structure that selects molecules from the gas. Cooling results in a transfer of energy from the molecules to the surface, whereas heating results in a transfer of energy from the surface to the molecules.
摘要翻译：将热量传递给或来自气体的方法和装置。该方法包括以足够的速度移动表面以破坏与表面接触的气体分子的速度边界层以及冷却或加热表面的步骤。表面可以是从气体中选择分子的杂交结构。冷却导致能量从分子转移到表面，而加热导致能量从表面转移到分子。

5. 发明申请

WO2008030176A1 SUBSTRATE-PENETRATING ELECTRICAL CONNECTIONS 审中-公开
标题翻译：基板电气连接
公开(公告)号：WO2008030176A1
公开(公告)日：2008-03-13
申请号：PCT/SE2007/050617
申请日：2007-09-04
申请人： NANOSPACE AB , RANGSTEN, Pelle , JOHANSSON, Håkan , BEJHED, Johan
发明人： RANGSTEN, Pelle , JOHANSSON, Håkan , BEJHED, Johan
IPC分类号： H05K3/36 , H01L23/48 , H01R12/34
CPC分类号： B82Y15/00 , B64G1/1078 , B64G1/26 , B64G1/401 , B81B7/0006 , B81B2207/092 , B81B2207/096 , F02K9/62 , F02K9/80 , F05D2250/82 , F05D2250/84 , Y10T29/49083 , Y10T29/49099 , Y10T29/49155 , Y10T29/49346 , Y10T29/49718 , Y10T29/49746
摘要： A wafer assembly (30) comprises a substrate (71), in turn comprising a wafer (70) or a stack of wafers. The wafer assembly (30) further comprises an electrical connection (32) arranged through at least a part of the substrate (71). The electrical connection (32) is made by low-resistance silicon. The electrical connection (32) is positioned in a hole (84) penetrating at least a part of the substrate (71). A surface (78) of the substrate (71) confining the hole (84) is electrically insulating. The electrical connection (32) has at least one protrusion (75), which protrudes transversally to a main extension (83) of the hole (84) and the protrusion (75) protrudes outside a minimum hole diameter (85), as projected in the main extension (83) of the hole (84). Preferably, the protrusion (75) is supported by a support surface (81) of the substrate (71). A manufacturing method is also disclosed.
摘要翻译：晶片组件（30）包括基板（71），其又包括晶片（70）或晶片堆叠。晶片组件（30）还包括布置成穿过衬底（71）的至少一部分的电连接（32）。电连接（32）由低电阻硅制成。电连接（32）位于贯穿基板（71）的至少一部分的孔（84）中。限制孔（84）的基板（71）的表面（78）是电绝缘的。电连接（32）具有至少一个突出部（75），该突起横向突出到孔（84）的主延伸部（83），并且突起（75）突出到最小孔直径（85）的外侧，如投影在孔（84）的主延伸部（83）。优选地，突起（75）由衬底（71）的支撑表面（81）支撑。还公开了一种制造方法。

6. 发明申请

WO1997047013A1 MICRO GAS RHEOSTAT 审中-公开
公开(公告)号：WO1997047013A1
公开(公告)日：1997-12-11
申请号：PCT/US1997009962
申请日：1997-06-06
申请人： MAROTTA SCIENTIFIC CONTROLS, INC.
发明人： MAROTTA SCIENTIFIC CONTROLS, INC. , REINICKE, Robert, H. , BRUNEAU, Stephen, D.
IPC分类号： G21D01/00
CPC分类号： B64G1/26 , B64G1/401 , B64G1/402 , F02K9/805 , F05D2250/82 , F05D2250/84 , F15C5/00
摘要： A device and method for controlling small flows of gas for satellite orientation thrusters comprises a photoetched silicon body (10) etched to provide one or more particular flow paths, and optionally filters, wherein the flow path is defined by the silicon body (10) and a sealing glass layer (11) bonded thereto. Flow is controlled through the flow path(s) by heating the body (10) to decrease the gas flow.
摘要翻译：用于控制用于卫星定向推进器的小气流的装置和方法包括被蚀刻以提供一个或多个特定流动路径的光刻硅体（10）和任选的过滤器，其中流动路径由硅体（10）和与其结合的密封玻璃层（11）。通过加热主体（10）通过流动路径控制流量以减少气体流量。

7. 发明申请

WO1997046820A1 MICROVALVE AND MICROTHRUSTER FOR SATELLITES AND METHODS OF MAKING AND USING THE SAME 审中-公开
标题翻译：用于卫星的微型和微型计算机及其制造和使用方法
公开(公告)号：WO1997046820A1
公开(公告)日：1997-12-11
申请号：PCT/US1997009725
申请日：1997-06-04
申请人： MAROTTA SCIENTIFIC CONTROLS, INC.
发明人： MAROTTA SCIENTIFIC CONTROLS, INC. , REINICKE, Robert, H.
IPC分类号： F16K31/06
CPC分类号： F16K31/0655 , B64G1/26 , B64G1/401 , B64G1/402 , F02K9/58 , F05D2250/82 , F05D2250/84 , F15C5/00 , F16K31/0651 , Y10T137/0318 , Y10T137/794
摘要： A microvalve comprises a valve housing (20, 24) defining an interior space, a fluid entrance (14) and a fluid exit (15), a selectively energizable magnet (21), an armature (10) disposed within the interior space of the housing and moveable therein between the fluid entrance and exit, and a permanent magnet (33) for urging the armature in a closed position agianst a valve seat. A microthruster (160) is provided by fashioning a valve discharge as a nozzle. The valve is guided without any sliding fit mechanism and is suitable for controlling gas or liquid fluid flows.
摘要翻译：微型阀包括限定内部空间的阀壳体（20,24），流体入口（14）和流体出口（15），可选择性激励的磁体（21），设置在内部空间的内部空间内的电枢（10）在流体入口和出口之间容纳和移动，以及用于在关闭位置推动电枢的永磁体（33），用于阀座。通过形成作为喷嘴的阀排出口来提供微型推动器（160）。引导阀无任何滑动配合机构，适用于控制气体或液体流体流动。

8. 发明申请

WO2008030175A1 NOZZLE ARRANGEMENT FOR USE IN A GAS THRUSTER, GAS THRUSTER, METHOD FOR MANUFACTURING A NOZZLE ARRANGEMENT, METHOD FOR IN-SITU REPAIRING OF A NOZZLE ARRANGEMENT AND A METHOD FOR OPERATING A GAS THRUSTERS 审中-公开
标题翻译：用于燃气喷射器的喷嘴装置，气体压路机，制造喷嘴装置的方法，用于现场修理喷嘴装置的方法和操作气体喷射器的方法
公开(公告)号：WO2008030175A1
公开(公告)日：2008-03-13
申请号：PCT/SE2007/050615
申请日：2007-09-04
申请人： NANOSPACE AB , GRÖNLAND, Tor-Arne , RANGSTEN, Pelle , JOHANSSON, Håkan , BEJHED, Johan
发明人： GRÖNLAND, Tor-Arne , RANGSTEN, Pelle , JOHANSSON, Håkan , BEJHED, Johan
IPC分类号： F02K9/62 , B64G1/40 , F03H5/00
CPC分类号： B82Y15/00 , B64G1/1078 , B64G1/26 , B64G1/401 , B81B7/0006 , B81B2207/092 , B81B2207/096 , F02K9/62 , F02K9/80 , F05D2250/82 , F05D2250/84 , Y10T29/49083 , Y10T29/49099 , Y10T29/49155 , Y10T29/49346 , Y10T29/49718 , Y10T29/49746
摘要： A nozzle arrangement for use in a gas thruster is presented. At least one heater micro structure (20) is arranged in a stagnation chamber (12) of the gas thruster. The heater microstructure (20) comprises a core of silicon or a silicon compound coated by a surface metal or metal compound coating. The heater microstructure (20) is manufactured in silicon or a silicon compound and covered by a surface metal coating. The heater microstructure (20) is mounted in the stagnation chamber (12) before or after the coverage of the surface metal or metal compound coating. The coverage is performed by heating the heater microstructure and flowing a gas comprising low quantities of a metal compound. The compound decomposes at the heated heater microstructure (20), forming the surface metal or metal compound coating. The same principles of coating can be used for repairing the heater microstructure (20) in situ. The driving gas comprises preferably a compound exhibiting an exothermic reaction when coming into contact with a catalytically active material. If the gas is exposed to heater microstructures being covered with the catalytically active material, the gas is further heated by the catalytic reaction.
摘要翻译：提出了一种用于气体推进器的喷嘴装置。至少一个加热器微结构（20）布置在气体推进器的停滞室（12）中。加热器微结构（20）包括由核或硅化合物涂覆的表面金属或金属化合物涂层。加热器微结构（20）由硅或硅化合物制成并被表面金属涂层覆盖。加热器微结构（20）在表面金属或金属化合物涂层的覆盖之前或之后安装在停滞室（12）中。通过加热加热器微结构并流动包含少量金属化合物的气体来进行覆盖。该化合物在加热的加热器微结构（20）处分解，形成表面金属或金属化合物涂层。相同的涂层原理可用于原位修复加热器微结构（20）。当与催化活性材料接触时，驱动气体优选包含表现出放热反应的化合物。如果气体暴露于被催化活性材料覆盖的加热器微结构，则气体被催化反应进一步加热。

9. 发明申请

WO2007135455A1 MICRO PULSE JET ENGINE 审中-公开
标题翻译：微型喷枪引擎
公开(公告)号：WO2007135455A1
公开(公告)日：2007-11-29
申请号：PCT/GB2007/050243
申请日：2007-05-09
申请人： BAE SYSTEMS PLC , HUCKER, Martyn, John , WARSOP, Clyde , HOLDEN, Harriet, Ann
发明人： HUCKER, Martyn, John , WARSOP, Clyde , HOLDEN, Harriet, Ann
IPC分类号： F02K7/04
CPC分类号： F02K7/02 , F02K7/04 , F05D2230/14 , F05D2250/82 , F05D2250/84 , F05D2300/222
摘要： A millimetre-scale pulse jet engine comprises an engine body that defines a combustion chamber, a fuel, an air intake, and an exhaust. The fuel inlet is arranged to inject fuel directly into the combustion chamber. The air intake and the exhaust are in fluid communication with the combustion chamber, and the combustion chamber is configured such that air from the air intake and fuel from the fuel inlet cyclically combust in the combustion chamber to produce exhaust gases.
摘要翻译：毫米级脉冲喷气发动机包括限定燃烧室，燃料，进气口和排气的发动机体。燃料入口设置成将燃料直接喷入燃烧室。进气口和排气口与燃烧室流体连通，并且燃烧室构造成使得来自进气口的空气和来自燃料入口的燃料在燃烧室中周期性地燃烧以产生废气。

10. 发明申请

WO2006083320A3 ULTRA MICRO GAS TURBINE 审中-公开
标题翻译：超微型燃气涡轮机
公开(公告)号：WO2006083320A3
公开(公告)日：2006-09-28
申请号：PCT/US2005024290
申请日：2005-07-07
申请人： UNIV MICHIGAN STATE , AKBARI PEZHMAN , MULLER NORBERT , IANCU FLORIN
发明人： AKBARI PEZHMAN , MULLER NORBERT , IANCU FLORIN
IPC分类号： F02C5/10 , F01D1/12 , F02C3/05
CPC分类号： F01D1/12 , F02C3/05 , F02C5/10 , F05D2230/14 , F05D2250/82 , F05D2250/84 , F05D2260/963
摘要： The present invention provides an ultra micro gas turbine engine which includes a wave rotor. In various embidiments, the ultra micro gas turbine engine of the present invention includes a rotating disk which has a compressor, a wave rotor and a turbine, a first stationary member which include an inlet and a first wave rotor port end plate, a second stationary menber which includes and outlet and a second wave rotor port end plate and a combustion chamber which includes a fuel inlet and an igniter.
摘要翻译：本发明提供了一种包括波转子的超微型燃气涡轮发动机。在各种实施例中，本发明的超微型燃气涡轮发动机包括：旋转盘，其具有压缩机，波转子和涡轮;第一固定构件，其包括入口和第一波动转子端口端板;第二固定构件包括出口和第二波转子端口端板的燃烧室和包括燃料入口和点火器的燃烧室。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式