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    • 1. 发明申请
    • MANUFACTURING A COMPONENT OF SINGLE CRYSTAL OR DIRECTIONALLY SOLIDIFIED MATERIAL
    • 制造单晶或方向固化材料的组分
    • WO2013029959A1
    • 2013-03-07
    • PCT/EP2012/065619
    • 2012-08-09
    • SIEMENS AKTIENGESELLSCHAFTDAVIS, AnthonyHAJE, Detlef
    • DAVIS, AnthonyHAJE, Detlef
    • C23C24/10C23C26/02B22F3/105C30B29/52C30B13/24C30B13/34C30B30/00
    • C30B13/30B22F3/1055C23C24/106C23C26/02C30B11/00C30B13/24C30B29/52Y02P10/295
    • The present invention relates to a method for manufacturing a component (10) of a single crystal or a directionally solidified material, said component (10) being manufactured having a predefined shape (12), comprising at least the following steps: superimposing at least a powder layer (14) of a powder of a first material onto at least a surface (16) of a substrate (18) out of a second, single crystal or directionally solidified, material; transforming the powder layer (14) into a substrate layer (20) with a new surface (22) of the substrate (18) by altering at least a physical condition of the first material of the powder by applying energy to the powder layer (14); wherein said substrate layer (20) is becoming a part of the substrate (18); wherein the second, single crystal or directionally solidified, material of the substrate (18) has a grain orientation (24) and the material of the substrate layer (20) has a grain orientation (26); wherein the material of the substrate layer (20) adopts the same grain orientation (24) as the grain orientation (26) of the substrate (18) during the transforming process and wherein the steps are repeated till the component (10) has grown layer by layer into the predefined shape (12) while a process temperature (T p ) is maintained below a melting temperature (T m ) of at least the first material and the component (10) has been manufactured thereby.
    • 本发明涉及一种用于制造单晶或定向凝固材料的组分(10)的方法,所述组分(10)被制造成具有预定形状(12),至少包括以下步骤:至少叠加一个 第一材料的粉末的粉末层(14)在第二单晶或定向凝固材料的至少一个基底(18)的表面(16)上; 通过向粉末层(14)施加能量来改变粉末的第一材料的至少物理条件,将粉末层(14)转变成具有基底(18)的新表面(22)的基底层(20) ); 其中所述衬底层(20)正在成为衬底(18)的一部分; 其中所述基底(18)的所述第二单晶或定向凝固的材料具有晶粒取向(24),并且所述基底层(20)的材料具有晶粒取向(26); 其中所述基底层(20)的材料在转变过程中采用与所述基底(18)的晶粒取向(26)相同的晶粒取向(24),并且其中所述步骤被重复,直到所述组分(10)具有生长层 处理温度(Tp)保持在至少第一材料和组分(10)的熔化温度(Tm)以下的同时,形成预定形状(12)。
    • 2. 发明申请
    • NOZZLE GUIDE VANE WITH COOLED PLATFORM FOR A GAS TURBINE
    • 用于气体涡轮的冷却平台的喷嘴导向槽
    • WO2012007250A1
    • 2012-01-19
    • PCT/EP2011/060144
    • 2011-06-17
    • SIEMENS AKTIENGESELLSCHAFTDAVIS, AnthonyWALKER, Paul, Mathew
    • DAVIS, AnthonyWALKER, Paul, Mathew
    • F01D9/04
    • F01D25/12F01D9/041F05D2240/81Y10T29/49316
    • Platform part for supporting a nozzle guide vane for a gas turbine, the platform part comprising: a gas passage surface (113) arranged to be in contact with a streaming operation gas; and at least one cooling channel (117) shaped for guiding a cooling fluid within the cooling channel, wherein the cooling channel is formed in an inside of the platform part, wherein a cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface, wherein the platform part is an integrally formed part representing a segment in a circumferential direction of the gas turbine, wherein the cooling channel comprises a first cooling channel portion (121) and a second cooling channel portion (123) arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas, wherein the first cooling channel portion (121) and the second cooling channel portion (123) are interconnected.
    • 用于支撑用于燃气轮机的喷嘴导向叶片的平台部分,所述平台部分包括:布置成与流动操作气体接触的气体通道表面(113) 以及至少一个冷却通道(117),其形状用于引导冷却通道内的冷却流体,其中所述冷却通道形成在所述平台部分的内部,其中所述冷却通道的内表面的冷却部分处于热接触 其中所述平台部分是表示所述燃气轮机的圆周方向上的段的整体形成部分,其中所述冷却通道包括第一冷却通道部分(121)和第二冷却通道部分(123),所述第一冷却通道部分 相对于操作气体的流动方向在第一冷却通道部分的下游,其中第一冷却通道部分(121)和第二冷却通道部分(123)相互连接。
    • 4. 发明申请
    • IMPINGEMENT COOLING OF GAS TURBINE BLADES OR VANES
    • 气体涡轮叶片或风口的冲击冷却
    • WO2012084454A1
    • 2012-06-28
    • PCT/EP2011/071598
    • 2011-12-02
    • SIEMENS AKTIENGESELLSCHAFTDAVIS, Anthony
    • DAVIS, Anthony
    • F01D5/18
    • F01D5/189F05D2230/51F05D2230/60F05D2260/201F05D2260/30Y10T29/49359
    • The present invention relates to aerofoil-shaped gas turbine components such as gas turbine rotor blades and stator vanes, and to impingement tubes used in such components for cooling purposes. The present invention further relates to a method for assembling impingement tubes in such components. According the invention an impingement tube is being formed from at least two separate sections each extending span wise through a hollow aerofoil. The first of said at least two sections of the impingement tube is inserted first into the hallow aerofoil and manoeuvred in direction of a trailing edge region of the hollow aerofoil into position in a rear of a cavity of the hollow aerofoil. The second of said at least two sections of the impingement tube is inserted into the hallow aerofoil adjacent to said first section second. The first section and second section of said impingement tube are connected together by a locking means, wherein said locking means locking said impingement tube into place in the hollow aerofoil, characterized in that said locking means is arranged in an axially direction between said sections and has a main extension which extends in a radial direction of the hollow aerofoil.
    • 本发明涉及诸如燃气轮机转子叶片和定子叶片的翼型燃气轮机部件以及用于这些部件的用于冷却目的的冲击管。 本发明还涉及在这些部件中组装冲击管的方法。 根据本发明,冲击管由至少两个分开的部分形成,每个部分跨越通过中空翼型跨越。 冲击管的所述至少两个部分中的第一个首先插入到中空机翼中,并且在中空机翼的后缘区域的方向上操纵到位于中空机翼的空腔后部的位置。 所述冲击管的所述至少两个部分中的第二个插入与所述第一部分第二部分相邻的所述中空机翼中。 所述冲击管的第一部分和第二部分通过锁定装置连接在一起,其中所述锁定装置将所述冲击管锁定在中空机翼中的适当位置,其特征在于,所述锁定装置沿着轴向方向布置在所述部分之间并具有 主延伸部,其在中空翼型件的径向方向上延伸。
    • 5. 发明申请
    • BLADE FOR A TURBO MACHINE
    • 涡轮机叶片
    • WO2012028424A1
    • 2012-03-08
    • PCT/EP2011/063641
    • 2011-08-08
    • SIEMENS AKTIENGESELLSCHAFTDAVIS, Anthony
    • DAVIS, Anthony
    • F01D5/08F01D5/18
    • F01D25/12F01D5/082F01D5/187F01D11/04F05D2240/81F05D2260/201
    • Blade (1) for a turbomachine, particularly a gas turbine, the blade (1) particularly being arrangeable on a turbine rotor of the gas turbine, the blade (1) comprising: a root portion having two narrow sides (4, 5) and two broad sides; a cooling air supply passage (10) in the root portion; and a cooling air bleed (13) being arranged in the root portion and being in fluid connection with the cooling air supply passage (10); wherein the cooling air bleed (13) comprises a nozzle (14) on one of the narrow sides (4, 5) of the root portion, wherein the nozzle (14) is formed by a hole and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to the longitudinal direction of the blade (1).
    • 用于涡轮机械(特别是燃气轮机)的叶片(1),叶片(1)特别可布置在燃气轮机的涡轮转子上,叶片(1)包括:根部,其具有两个窄边(4,5)和 两面宽阔 根部中的冷却空气供给通路(10) 和冷却空气排出口(13),其布置在所述根部中并与所述冷却空气供给通道(10)流体连通; 其中,所述冷却空气流出口(13)包括在所述根部的一个窄边(4,5)上的喷嘴(14),其中所述喷嘴(14)由孔形成,并且所述孔的轴向方向 相对于叶片(1)的纵向方向向上倾斜92°至135°。
    • 7. 发明申请
    • OBJECT SCANNING SYSTEM
    • 对象扫描系统
    • WO2009058782A1
    • 2009-05-07
    • PCT/US2008/081462
    • 2008-10-28
    • IMTEC CORPORATIONDAVIS, Anthony
    • DAVIS, Anthony
    • G01T1/24
    • G01T1/2018
    • The present invention relates generally to the field of electronic and digital radiography and computed tomography scanning systems. More specifically, the invention relates to scanning unit (10) with the capability transmit and receive X-rays in an inventive manner. Even more specifically, the invention involves a method of using a linear path to transmit X-rays through, sequentially, an object, a scintillator (30), a lens (40) and an imaging sensor (50). Even more specifically, the invention relates to an X-ray scanner that uses an amorphous silicon detector plate (50) to detect photons transmitted from a scintillator with lens (42) or fiber coupling (44). Finally, the invention relates to a method for utilizing an amorphous silicon area detector (50) to create digital radiographs of parts which are themselves larger than the active area of the amorphous silicon array.
    • 本发明一般涉及电子和数字射线照相术和计算机断层摄影扫描系统的领域。 更具体地,本发明涉及具有以发明方式传输和接收X射线的能力的扫描单元(10)。 更具体地,本发明涉及使用线性路径通过物体,闪烁体(30),透镜(40)和成像传感器(50),依次地透射X射线的方法。 更具体地,本发明涉及一种使用非晶硅检测器板(50)来检测从具有透镜(42)或光纤耦合器(44)的闪烁体发射的光子的X射线扫描器。 最后,本发明涉及一种利用非晶硅区域检测器(50)产生本身大于非晶硅阵列有源区的部分的数字X射线照片的方法。
    • 10. 发明申请
    • PLATFORM COOLING OF TURBINE VANE
    • 涡轮风扇平台冷却
    • WO2008132082A1
    • 2008-11-06
    • PCT/EP2008/054783
    • 2008-04-21
    • SIEMENS AKTIENGESELLSCHAFTDAVIS, Anthony
    • DAVIS, Anthony
    • F01D9/02
    • F01D9/023F01D9/041F01D25/246F05D2240/81
    • A turbine vane (17a) is provided which comprises a radial outer platform (25a), a radial inner platform (27a) and an airfoil (37) extending between the outer platform (25a) and the inner platform (27a). Each platform has a gas washed surface (39, 41) showing towards the respective other platform, a non gas washed surface (43, 45) showing away from the respective other platform and a peripheral surface (58, 62) extending from the gas washed surface (39, 41) to the non gas washed surface (43, 45). The peripheral surface comprises an upstream section (59, 63) that is designed to be directed towards the gas flow washing the gas washed surface (39, 41). Cooling fluid channels (55, 57, 67, 69, 71, 73) with an opening in the peripheral surface (59, 63) or in the gas washed surface (39, 41) are located in at least a section of the outer platform (25a) and/or in at least a section of the inner platform (27a). The respective section directly adjoins the upstream section (59, 63) of the respective platform's peripheral surface (58, 62).
    • 提供一种涡轮叶片(17a),其包括在外平台(25a)和内平台(27a)之间延伸的径向外平台(25a),径向内平台(27a)和翼型件(37)。 每个平台具有向相应的其他平台示出的气体洗涤表面(39,41),与相应的另一个平台相隔离的非气体洗涤表面(43,44)和从气体洗涤的外部表面(58,62) 表面(39,41)到非气体洗涤表面(43,45)。 外围表面包括上游部分(59,63),该上游部分被设计成指向洗涤气体洗涤表面(39,41)的气流。 在外围表面(59,63)中或在气体清洗表面(39,41)中具有开口的冷却流体通道(55,57,67,69,71,73)位于外部平台的至少一部分 (25a)和/或在所述内平台(27a)的至少一部分中。 相应的部分直接邻接相应平台的周边表面(58,62)的上游部分(59,63)。