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1. 发明申请

US20210148232A1 ROTOR SYSTEM FOR GENERATING KINETIC ENERGY BY GENERATING AN UNBALANCED TORQUE BY MEANS OF MATERIAL ENERGY 有权
公开(公告)号：US20210148232A1
公开(公告)日：2021-05-20
申请号：US16684149
申请日：2019-11-14
申请人： Ming-Tung HUNG
发明人： Ming-Tung HUNG
IPC分类号： F01D1/18 , F01D15/12
摘要： A rotor system for generating kinetic energy by expanding an unbalanced torque by means of material energy is provided. The rotor has a horizontal rotating shaft and a plurality of sets of radiating members, and each of radiating members combines with a swingable mass and a slidable member that are combined with each other by a transmission system. The slidable member has two containers, each with an opening for holding the substances in the opposite direction, and after the substances are injected into a specific orientation, due to the total weight being greater than the swingable mass that plus the inclination and gravity, which causes the swingable mass to be swung at one hundred and eighty degrees. Therefore, an outer ring system and an inner ring system both generate the torsion toward the running direction so that the entire rotor system generates good operating kinetic energy.

2. 发明申请

US20180363489A1 GEARED TURBOFAN WITH INTEGRALLY BLADED ROTOR 审中-公开
公开(公告)号：US20180363489A1
公开(公告)日：2018-12-20
申请号：US16109842
申请日：2018-08-23
申请人： United Technologies Corporation
发明人： Frederick M. Schwarz
IPC分类号： F01D15/12 , F02C3/107 , F02K3/06 , F01D5/34 , F02C3/06 , F01D1/18 , F01D5/02
摘要： A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.

3. 发明授权

US09932856B2 Cooling apparatus for turbomachinery with method of installation 有权
公开(公告)号：US09932856B2
公开(公告)日：2018-04-03
申请号：US14550946
申请日：2014-11-22
申请人： General Electric Company
发明人： Hua Zhang , Douglas Scott Byrd , David Terry Trayhan, Jr.
IPC分类号： F01D25/12 , F01D1/18 , F02C7/143 , F02C3/30 , F02C6/06 , F02C6/10 , F02C7/18
CPC分类号： F01D25/12 , F01D1/18 , F02C3/30 , F02C3/305 , F02C6/06 , F02C6/10 , F02C7/1435 , F02C7/185 , F05D2260/212 , F05D2270/16
摘要： Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

4. 发明授权

US09644482B2 Method for manufacturing machine component, and rotary machine equipped with impeller manufactured by means of this method 有权
公开(公告)号：US09644482B2
公开(公告)日：2017-05-09
申请号：US14123269
申请日：2012-12-20
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Shimpei Okayasu , Hiroko Kitamoto , Daisuke Kawanishi , Hiroki Takagi , Nobuyori Yagi
IPC分类号： F01D1/18 , F04D29/02 , F04D29/28 , B23P15/00 , C21D11/00 , C21D1/30
CPC分类号： F01D1/18 , B23P15/006 , C21D1/30 , C21D11/00 , C21D2261/00 , F04D29/023 , F04D29/281 , F05D2230/10 , F05D2230/40 , Y10T29/49764
摘要： A method for manufacturing a machine component includes a process of estimating post-heat-treatment strength for the intermediate form of a base material after a certain mechanical working process is performed, and a process of comparing the estimated strength with reference strength required for a final form. According to a result of the comparison, heat treatment of the base material is performed after one of the mechanical working processes is performed.

5. 发明申请

US20170022814A1 KINETIC ENERGY ATOM-POWERED ENGINE 审中-公开
标题翻译：动力能源发动机
公开(公告)号：US20170022814A1
公开(公告)日：2017-01-26
申请号：US15282991
申请日：2016-09-30
申请人： Lee Ervin
发明人： Lee Ervin
IPC分类号： F01D1/18 , B81B5/00 , F03B17/00 , F01D25/00 , F01D25/14
CPC分类号： F01D1/18 , B81B5/00 , B81B2201/03 , B81B2201/034 , B81B2203/06 , F01D25/005 , F01D25/14 , F03B17/00 , Y02E10/20 , Y02E10/28
摘要： A device for converting the kinetic energy of molecules into useful work includes an actuator configured to move within a fluid or gas due to collisions with the molecules of the fluid or gas. The actuator has dimensions that subject it to the Brownian motion of the surrounding molecules. The actuator utilizes objects having multiple surfaces where the different surfaces result in differing coefficients of restitution. The Brownian motion of surrounding molecules produce molecular impacts with the surfaces. Each surface then experiences relative differences in transferred energy from the kinetic collisions. The sum effect of the collisions produces net velocity in a desired direction. The controlled motion can be utilized in a variety of manners to perform work, such as generating electricity or transporting materials.
摘要翻译：用于将分子的动能转化为有用功的装置包括致动器，其构造成由于与流体或气体的分子碰撞而在流体或气体内移动。致动器具有使其受到周围分子的布朗运动的尺寸。致动器利用具有多个表面的物体，其中不同的表面导致不同的恢复系数。周围分子的布朗运动与表面产生分子冲击。每个表面然后经历来自动力学碰撞的转移能量的相对差异。碰撞的总和效应产生所需方向的净速度。受控运动可以以各种方式用于执行工作，例如发电或运输材料。

6. 发明申请

US20160186567A1 COMPRESSED GAS ENGINE 审中-公开
标题翻译：压缩气体发动机
公开(公告)号：US20160186567A1
公开(公告)日：2016-06-30
申请号：US14582234
申请日：2014-12-24
申请人： Michael Miller
发明人： Michael Miller
IPC分类号： F01D1/18 , F01D17/10
CPC分类号： F03G3/00 , F03G7/10
摘要： An engine has two pressure vessels arranged as a diametrically opposed pair. Each pressure vessel has an operating pressure sufficient to hold gas at a pre-defined pressure. At least one gas compressor is in communication with each pressure vessel, and the gas compressor is capable of compressing a gas in each pressure vessel to the pre-defined pressure. A pressure relief mechanism is in communication with each pressure vessel. The pressure relief mechanism is capable of returning the gas in each vessel to atmospheric pressure.
摘要翻译：发动机具有两个直径相对的配置的压力容器。每个压力容器具有足以将气体保持在预定压力的操作压力。至少一个气体压缩机与每个压力容器连通，并且气体压缩机能够将每个压力容器中的气体压缩至预定压力。压力释放机构与每个压力容器连通。压力释放机构能够将每个容器中的气体返回至大气压力。

7. 发明申请

US20160146043A1 COOLING APPARATUS FOR TURBOMACHINERY WITH METHOD OF INSTALLATION 有权
标题翻译：用于安装方法的涡轮机的冷却装置
公开(公告)号：US20160146043A1
公开(公告)日：2016-05-26
申请号：US14550946
申请日：2014-11-22
申请人： General Electric Company
发明人： Hua Zhang , Douglas Scott Byrd , David Terry Trayhan, JR.
IPC分类号： F01D25/12 , F01D1/18
CPC分类号： F01D25/12 , F01D1/18 , F02C3/30 , F02C3/305 , F02C6/06 , F02C6/10 , F02C7/1435 , F02C7/185 , F05D2260/212 , F05D2270/16
摘要： Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.
摘要翻译：本公开的实施例提供了用于涡轮机械的冷却系统和安装方法。在一个实施例中，本公开的装置可以包括用于将冷却空气从发电系统的压缩机路由到发电系统的涡轮机部件的通风管道; 以及与所述通气导管流体连通的喷嘴，其中所述喷嘴将水从供水部分输送到所述通气导管中。

8. 发明申请

US20150211380A1 TURBINE ENGINE COMPRISING A MEANS FOR MEASURING THE SPEED AND TORQUE OF A SHAFT OF THE TURBINE ENGINE AND METHOD FOR MONITORING SAID SHAFT 有权
标题翻译：涡轮发动机包括用于测量涡轮发动机轴的转速和扭矩的手段和用于监测上述轴的方法
公开(公告)号：US20150211380A1
公开(公告)日：2015-07-30
申请号：US14426147
申请日：2013-09-05
申请人： SNECMA
发明人： Augustin Curlier , Olivier Belmonte , Gilles Le Gouellec
IPC分类号： F01D21/00 , F01D1/18 , F01D25/24
CPC分类号： F01D21/003 , F01D1/18 , F01D25/24 , F02K3/025 , F05D2260/80 , F05D2270/304 , F05D2270/335 , F05D2270/809 , G01L3/105 , G01M15/14 , G01P3/488 , Y02T50/671
摘要： Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).
摘要翻译：涡轮发动机（1），特别是用于飞行器，包括可旋转地安装在涡轮发动机（1）的壳体（3）中的至少一个轴向轴（2），所述涡轮发动机（1）包括环形参考部分）包括短（11）和长（12）纵向参考齿，第一装置用于检测短（11）和长（12）基准齿的通过，以便测量涡轮发动机的轴（2）的速度（1）围绕其轴线（X），包括纵向测量齿（21）的环形测量部分（20）; 以及用于检测长参考齿（12）和测量齿（21）的通过以便测量涡轮发动机（1）的轴（2,102）的扭矩的第二装置。

9. 发明授权

US07708522B2 Rotary heat engine 失效
标题翻译：旋转热机
公开(公告)号：US07708522B2
公开(公告)日：2010-05-04
申请号：US11324604
申请日：2006-01-03
申请人： Andrew Schlote
发明人： Andrew Schlote
IPC分类号： F01D1/18
CPC分类号： F01D1/22 , F01D1/32 , Y02T50/672
摘要： A rotor of a supersonic rotary heat engine comprises a rotor axis about which the rotor is adapted and configured to rotate, a plurality of thrust matter passageways, and a plurality of cooling passageways. Each of the thrust matter passageways is at least partially bound by a gas permeable wall. The outlet port of each thrust matter passageway is adapted and configured to discharge gaseous fluid into an exhaust environment external to the rotor in a manner creating a torque on the rotor about the rotor axis. Each of the cooling passageways is in fluid communication with a respective one of the thrust matter passageways via the gas permeable wall that at least partially bounds the respective thrust matter passageway.
摘要翻译：超音速旋转热机的转子包括转子轴线，转子适于旋转，多个推力物质通道和多个冷却通道。每个推力物质通道至少部分地由气体可渗透的壁限制。每个推力物质通道的出口被适配和构造成以在转子周围绕转子轴线产生转矩的方式将气体流体排放到转子外部的排气环境中。每个冷却通道经由气体可渗透壁与至少部分地限定相应的推力物质通道的推力物质通道中的相应一个流体连通。

10. 发明申请

US20060034677A1 PRESSURIZED FLUID TURBINE ENGINE 有权
标题翻译：加压流体涡轮发动机
公开(公告)号：US20060034677A1
公开(公告)日：2006-02-16
申请号：US10839697
申请日：2004-05-04
申请人： Neldon Johnson
发明人： Neldon Johnson
IPC分类号： F01D1/18
CPC分类号： F03B3/00 , F01D1/32 , Y02E10/223
摘要： A bladeless pressurized fluid turbine engine having a bladeless turbine, internal, concentric or circumferential shaft fluid ways which transmit pressurized gas to the turbine, and a pressurized fluid intake assembly. The intake assembly has a fixed outer housing, two or more shaft seals sealing between the shaft and the outer housing forming fluid supply chambers between adjacent shaft seals, and a pair of shaft bearings bearing between the shaft and the outer housing. The outer housing has one or more fluid intake ports for each fluid supply chamber and each shaft fluid way has a shaft fluid intake which is hydraulically connected to a fluid supply chamber.
摘要翻译：具有无压涡轮机，内部，同心或圆周轴流体通道的无叶加压流体涡轮发动机，其将加压气体传输到涡轮机，以及加压流体进料组件。进气组件具有固定的外壳体，密封在轴和外壳体之间的两个或更多个轴封形成在相邻的轴密封件之间形成流体供应室，以及轴与轴与外壳之间的一对轴承。外壳体具有用于每个流体供应室的一个或多个流体进入端口，并且每个轴流体路径具有液压地连接到流体供应室的轴流体入口。

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