-
公开(公告)号：US20180266395A1
公开(公告)日：2018-09-20
申请号：US15982585
申请日：2018-05-17
发明人： Yuri ABRAMOV
CPC分类号： F03D9/25 , F02K1/00 , F03D1/04 , F03D1/0633 , F03D3/0454 , F05B2240/133 , F05D2250/323 , F05D2250/324 , G06F17/13 , G06F17/5009 , G06F17/5018 , G06F17/5086 , G06F2217/16 , Y02E10/721 , Y02T50/671
摘要： The invention provides a method for computational fluid dynamics and apparatuses making enable an efficient implementation and use of an enhanced jet-effect, either the Coanda-jet-effect, the hydrophobic jet-effect, or the waving-jet-effect, triggered by specifically shaped corpuses and tunnels. The method is based on the approaches of the kinetic theory of matter, thermodynamics, and continuum mechanics, providing generalized equations of fluid motion. The method is applicable for slow-flowing as well as fast-flowing real compressible-extendable fluids and enables optimal design of convergent-divergent nozzles, providing for the most efficient jet-thrust. The method can be applied to airfoil shape optimization for bodies flying separately and in a multi-stage cascaded sequence. The method enables apparatuses for electricity harvesting from the fluid heat-energy, providing a positive net-efficiency. The method enables efficient water-harvesting from air. The method enables generators for practical-expedient power harvesting using constructive interference of waves due to the waving jet-effect.
-
公开(公告)号：US09810178B2
公开(公告)日：2017-11-07
申请号：US14818596
申请日：2015-08-05
CPC分类号： F02K1/78 , F01D25/24 , F01D25/30 , F02K1/00 , F02K1/06 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2250/14
摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.
-
公开(公告)号：US20170037813A1
公开(公告)日：2017-02-09
申请号：US14818596
申请日：2015-08-05
CPC分类号： F02K1/78 , F01D25/24 , F01D25/30 , F02K1/00 , F02K1/06 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2250/14
摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.
摘要翻译： 涡轮风扇排气喷嘴包括：圆锥形内壳，同轴地设置在周围的外壳内，以限定其间的环形流动管道，其终止于外壳的后缘处的出口，并且内壳终止于出口后部的后缘; 以及托架，其周向地中断所述管道，其中所述外壳的后缘的至少一部分是垂直非共面的。
-
公开(公告)号：US09341082B2
公开(公告)日：2016-05-17
申请号：US14003180
申请日：2012-03-02
CPC分类号： F01D25/24 , B64D33/04 , F02K1/00 , F02K1/82 , F05D2250/71 , F05D2250/711 , Y02T50/671
摘要： A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region.
摘要翻译： 一种具有纵向轴线的涡轮发动机管道，其在其上游端包括外壁和芯部，只有其上游部分被外壁包围。 上游部分和下游部分之间的边界由芯和由垂直于外壁的直线形成的锐角的平分线形成的表面和垂直于芯的外表面的直线形成的表面之间的交点限定， 外壁的下游端。 芯的下游部分的外表面具有接近边界的急剧弯曲的凸起区域，该区域在径向平面中的曲率半径小于边界处的芯的半径的30倍，并且第一稍微 边界与锐曲的凸区域之间的弯曲区域。
-
公开(公告)号：US20160032907A1
公开(公告)日：2016-02-04
申请号：US14716541
申请日：2015-05-19
CPC分类号： F03H1/0081 , F02K1/00 , F02K1/28 , F02K7/00 , F02K7/10 , F02K9/00 , F03H1/00 , F05D2210/12 , F05D2220/10 , F05D2220/34
摘要： The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field.
摘要翻译： 本发明通过在空气流中引入或产生带电粒子并利用在带电粒子上运行的磁场来操纵空气流来克服现有技术中的缺陷。 本发明的实施例通过用移动磁场加速带电粒子来压缩空气流，其中磁场具有垂直于其通量线的速度。 带电粒子的增加的速度增加统计平均粒子速度，从而增加空气流中的压力。 然后将压缩空气流通过第二磁场加热和膨胀。 空气流的膨胀大大增加了空气流和其中的带电粒子的速度。 高速带电粒子与磁场的相互作用赋予垂直于磁通线的力，该力为磁场的运动提供动力。
-
公开(公告)号：US08951006B2
公开(公告)日：2015-02-10
申请号：US12527086
申请日：2007-11-23
申请人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
发明人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
CPC分类号： B64D29/08 , F02K1/00 , F05D2230/80 , Y02T50/671
摘要： The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，其类型包括具有外部结构（6）的下游结构，外部结构（6）与用于包围涡轮喷气发动机的下游部分的内部同心结构（9）一起限定，环形流动通道 其特征在于，至少所述内部结构（9）的一部分被安装成能够沿着所述机舱的纵向轴线的平移运动，使得其能够在工作位置之间移动，其中所述内部结构 用作涡轮喷气发动机的下游部分的壳体，以及内部结构暴露涡轮喷气发动机的所述下游部分的维护位置。
-
公开(公告)号：US20130013255A1
公开(公告)日：2013-01-10
申请号：US13177324
申请日：2011-07-06
申请人： YU DU , XIAOYAN ZHANG
发明人： YU DU , XIAOYAN ZHANG
IPC分类号： G06F15/00
CPC分类号： F02K1/00 , F01K13/02 , G05B13/041 , G05B23/0272 , G05B23/0294 , G06K9/6223 , G06Q10/06 , Y02P90/82
摘要： A method for obtaining operating parameters of a power plant includes data mining a historical operating condition database for the power plant with a partitional clustering algorithm to generate a statistical model, and calculating dynamic operating condition target values from the statistical model taking into account current operating condition data of the power plant. The method further includes performing a real-time energy-loss analysis based on the dynamic operating condition target values and automatically identifying at least one operating parameter of the power plant from the energy-loss analysis. The partitional clustering algorithm can be a k-means clustering algorithm.
摘要翻译： 一种用于获取发电厂的运行参数的方法，包括利用分散聚类算法对发电厂的历史运行状况数据库进行数据挖掘，生成统计模型，并根据当前运行状况从统计模型计算动态运行状态目标值 电厂数据。 该方法还包括基于动态运行条件目标值执行实时能量损失分析，并且从能量损失分析中自动识别发电厂的至少一个运行参数。 分组聚类算法可以是k均值聚类算法。
-
公开(公告)号：US08317129B1
公开(公告)日：2012-11-27
申请号：US12410828
申请日：2009-03-25
申请人： Edward Lawson , Aaron J. Kutzmann
发明人： Edward Lawson , Aaron J. Kutzmann
IPC分类号： B64B1/24
CPC分类号： B64D27/18 , B64C2039/105 , B64D33/04 , F02K1/00 , F05D2250/323 , Y02T50/12 , Y02T50/44 , Y02T50/672
摘要： Apparatus and methods provide for an engine nozzle having a universal convergent nozzle and a distinct nozzle aperture. Aspects of the disclosure provide a universal convergent nozzle that includes a nozzle throat and is attachable at a first end to an aircraft engine and at a second end to a distinct nozzle aperture. While the distinct nozzle aperture may include features that are specific to the corresponding engine mounting location, the universal convergent nozzle may be interchangeably used with any engine and distinct nozzle aperture at any engine mounting location. The configuration of the universal convergent nozzle ensures consistent engine performance and engine exhaust plume conditioning across all engine mounting locations, irrespective of the distinct nozzle aperture features downstream of the universal convergent nozzle.
摘要翻译： 装置和方法提供了具有通用会聚喷嘴和不同喷嘴孔的发动机喷嘴。 本公开的方面提供了一种通用会聚喷嘴，其包括喷嘴喉部，并且可在第一端附接到飞行器发动机，并且在第二端附接到不同的喷嘴孔。 虽然不同的喷嘴孔口可以包括特定于相应的发动机安装位置的特征，但是在任何发动机安装位置处，通用会聚喷嘴可以与任何发动机和不同的喷嘴孔口互换使用。 通用会聚喷嘴的配置确保了所有发动机安装位置的引擎性能和发动机排气羽流调节，而不管通用会聚喷嘴下游具有不同的喷嘴孔特征。
-
公开(公告)号：US20080120978A1
公开(公告)日：2008-05-29
申请号：US11808111
申请日：2007-06-06
申请人： Oscar D. Windham
发明人： Oscar D. Windham
CPC分类号： F02K1/00 , F05D2210/40 , F05D2250/15 , F05D2250/25
摘要： A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft. The propulsion system also contemplates a vehicle including the modified 3D spiral nozzle exhaust profile
摘要翻译： 用于喷气式或火箭推进式车辆的推进系统，其中所得的喷射式排气喷嘴轮廓为3D螺旋。 推进系统可应用于任何喷气式或火箭推进式车辆，包括飞机和船只。 推进系统还考虑了包括改进的3D螺旋喷嘴排气轮廓的车辆
-
10.发明申请Sprayable noble metal coating for high tempreature use on ceramic and smoothcoat coated aircraft engine parts 审中-公开可喷涂的贵金属涂层，用于陶瓷和光滑涂层飞机发动机零件的高温使用公开(公告)号：US20040228976A1
公开(公告)日：2004-11-18
申请号：US10726357
申请日：2003-12-03
IPC分类号： B05D001/02
CPC分类号： C23C30/00 , C23C4/02 , C23C4/123 , C23C4/18 , C23C24/04 , C23C28/345 , F01D5/28 , F02K1/00 , F05D2300/14 , F05D2300/142 , F05D2300/143 , F05D2300/21 , F05D2300/502 , Y02T50/67 , Y02T50/672 , Y02T50/6765
摘要： A method applies a heat-rejection coating directly on a substrate of a ceramic component. The steps include supplying a ceramic component, such as of a gas turbine engine, before applying a reflective-coating mixture onto the component, wherein the reflective-coating mixture comprises a metallic pigment and a reflective-coating-mixture carrier, and wherein the step of applying is accomplished by a method selected from the group consisting of air-assisted spraying, airless spraying, brushing, and decal transfer. The component having the reflective-coating mixture thereon is fired to form a reflective coating on the component.
摘要翻译： 一种方法是将排斥涂层直接施加到陶瓷部件的基底上。 所述步骤包括在将反射涂层混合物施加到所述部件之前提供诸如燃气涡轮发动机的陶瓷部件，其中所述反射涂层混合物包括金属颜料和反射涂层混合物载体，并且其中所述步骤 通过选自空气辅助喷雾，无空气喷涂，刷涂和贴花转移的方法来实现。 对其上具有反射涂层混合物的部件进行烧制以在部件上形成反射涂层。
-
-
-
-
-
-
-
-
-
搜索结果
90 条记录 (耗时 0.028 秒)
