公开(公告)号：US12104239B2

公开(公告)日：2024-10-01

申请号：US18451414

申请日：2023-08-17

申请人： General Electric Company

发明人： Andrew Philip Woodfield ,  Thomas Froats Broderick ,  William Andrew Sharp, II

IPC分类号： C22F1/18 ,  B21K3/04 ,  B22D7/00 ,  C22C14/00 ,  F01D5/28

CPC分类号： C22F1/183 ,  B21K3/04 ,  B22D7/005 ,  C22C14/00 ,  F01D5/28 ,  F05D2300/174 ,  Y02T50/60

摘要： A composition of matter is generally provided, in one embodiment, a titanium alloy comprising about 5 wt % to about 8 wt % aluminum; about 2.5 wt % to about 5.5 wt % vanadium; about 0.1 wt % to about 2 wt % of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt % to about 0.2 wt % carbon; up to about 0.3 wt % oxygen; silicon and copper; and titanium. A turbine component is also generally provided, in one embodiment, that comprises an article made from a titanium alloy. Additionally, methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature.

公开(公告)号：US11951528B2

公开(公告)日：2024-04-09

申请号：US17445454

申请日：2021-08-19

申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

发明人： Timothy Paul Fuesting ,  Gangshu Shen ,  Eugene Sun

IPC分类号： B21J1/06 ,  B21J5/00 ,  B21J5/02 ,  B21J9/02 ,  B21K3/04 ,  C22C19/05 ,  C22F1/10

CPC分类号： B21J1/06 ,  B21J5/008 ,  B21J5/02 ,  B21J9/022 ,  B21K3/04 ,  C22C19/056 ,  C22F1/10

摘要： The disclosure describes example systems and techniques for controlling microstructure of a superalloy substrate by controlling temperature during forging and using multiple die forging stages to formation of grain boundary phases of the superalloy, and components formed by such example systems and techniques. The method includes heating a substrate to within a forging temperature range. The substrate includes a nickel-based superalloy, and the forging temperature range is below an eta phase solvus temperature of the substrate. The method includes applying a plurality of die forging stages to the substrate to form a component preform. The method includes maintaining the substrate within the forging temperature range during application of the plurality of die forging stages and cooling the component preform.

公开(公告)号：US09995311B2

公开(公告)日：2018-06-12

申请号：US14443116

申请日：2014-05-09

申请人： LG ELECTRONICS INC.

发明人： Sang Yuk Son ,  Choon Myun Chung ,  Tae Man Yang

IPC分类号： F04D29/28 ,  B21K3/04 ,  B21J5/00 ,  B21D11/20 ,  B23K11/11 ,  F04D29/44 ,  F04D17/10 ,  F04D29/30 ,  B23K11/16 ,  B23K26/32 ,  B23K11/00 ,  B23K26/244 ,  F04D29/62 ,  B23K101/00 ,  B23K103/04

CPC分类号： F04D29/281 ,  B21D11/20 ,  B21J5/00 ,  B21K3/04 ,  B23K11/0026 ,  B23K11/11 ,  B23K11/115 ,  B23K11/16 ,  B23K26/244 ,  B23K26/32 ,  B23K2101/001 ,  B23K2103/04 ,  F04D17/10 ,  F04D29/282 ,  F04D29/30 ,  F04D29/441 ,  F04D29/626 ,  Y10T29/49329

摘要： A centrifugal fan is provided that includes a main plate configured to be rotated about a rotational axis, a shroud, having a suction opening, and a plurality of blades arranged in a circumferential direction between the main plate and the shroud to allow air suctioned in through the suction opening to flow from a front edge to a rear edge of each blade. Assuming a first cross section, a second cross section, a third cross section, and a fourth cross section of each blade sequentially taken at layers from the shroud to the main plate, a front edge of the first cross section is located farther from the rotational axis than a front edge of the fourth cross section, and a rear edge of the first cross section is located closer to the rotational axis than a rear edge of the fourth cross section.

公开(公告)号：US09566641B2

公开(公告)日：2017-02-14

申请号：US14937109

申请日：2015-11-10

申请人： ROLLS-ROYCE PLC

发明人： Graeme McElroy

IPC分类号： B21J5/02 ,  B21K3/00 ,  B21J9/02 ,  B21K3/04

CPC分类号： B21K3/00 ,  B21J5/025 ,  B21J9/027 ,  B21K3/04

摘要： A forging apparatus and method is disclosed in which a die has two separate cavities, each having a first cavity portion and a second cavity portion. A billet of material is received in a first cavity portion and struck by a striking portion of an extrusion punch so as to be forced into the corresponding second cavity portion to form a shaped component. The billet of material can be placed into either of the two cavities for extrusion. This may increase the number of extrusion operations that can be performed by a single die.

摘要翻译： 公开了一种锻造设备和方法，其中模具具有两个分开的空腔，每个空腔具有第一空腔部分和第二空腔部分。 材料坯料被容纳在第一空腔部分中，并被挤压冲头的打击部分撞击，以便被迫进入相应的第二空腔部分以形成成形部件。 材料坯料可以放置在两个空腔中的任一个中用于挤出。 这可以增加可以由单个模具执行的挤出操作的数量。

公开(公告)号：US09315927B2

公开(公告)日：2016-04-19

申请号：US13809706

申请日：2011-07-11

申请人： Bruno Jacques Gérard Dambrine ,  Thierry Godon ,  Alain Robert Yves Perroux

发明人： Bruno Jacques Gérard Dambrine ,  Thierry Godon ,  Alain Robert Yves Perroux

IPC分类号： D03D1/00 ,  B23P15/04 ,  D03D25/00 ,  B21K3/04 ,  F01D5/14 ,  B23K20/02 ,  B22F3/15 ,  C22C47/06 ,  F01D5/28 ,  F04D29/32 ,  B29C65/00 ,  B29L31/08 ,  B29C65/48

CPC分类号： D03D25/00 ,  B21K3/04 ,  B22F3/15 ,  B22F2998/00 ,  B23K20/021 ,  B23P15/04 ,  B29C65/48 ,  B29C65/483 ,  B29C65/484 ,  B29C66/12461 ,  B29C66/12463 ,  B29C66/301 ,  B29C66/53 ,  B29C66/721 ,  B29C66/742 ,  B29L2031/082 ,  C22C47/066 ,  D03D1/00 ,  F01D5/141 ,  F01D5/282 ,  F04D29/324 ,  F05D2220/325 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/614 ,  F05D2300/702 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336 ,  B22F5/04

摘要： A method for producing a solid part, including weaving a three-dimensional fibrous structure, the weaving being carried out with metal braids consisting of a plurality of metal strands mutually twisted about the longitudinal axis of the braid; and performing hot isostatic pressing on the fibrous structure causing the agglomeration of the metal braids of the fibrous structure so as to produce a solid part.

摘要翻译： 一种制造固体部分的方法，包括编织三维纤维结构，所述编织由金属编织物执行，所述金属编织物由围绕所述编织物的纵向轴线相互绞合的多个金属丝束组成; 并对纤维结构进行热等静压，导致纤维结构的金属编织物的聚结，从而产生固体部分。

公开(公告)号：US09199301B2

公开(公告)日：2015-12-01

申请号：US13816187

申请日：2011-08-04

申请人： Damien Rajasingam ,  Richard Evans ,  Olav Davis ,  Stephen Sandercock

发明人： Damien Rajasingam ,  Richard Evans ,  Olav Davis ,  Stephen Sandercock

IPC分类号： B21K3/04 ,  B29C33/12 ,  B29C65/50 ,  B29C65/78 ,  B29C65/00 ,  B29D99/00 ,  F03D1/06 ,  B29L31/08 ,  B29C65/48

CPC分类号： B21K3/04 ,  B29C33/12 ,  B29C65/483 ,  B29C65/5057 ,  B29C65/5071 ,  B29C65/5092 ,  B29C65/7832 ,  B29C66/128 ,  B29C66/301 ,  B29C66/543 ,  B29C66/636 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/8221 ,  B29C66/8324 ,  B29C70/86 ,  B29D99/0028 ,  B29L2031/085 ,  F03D1/0683 ,  Y02E10/721 ,  Y02P70/523 ,  Y10T29/37 ,  Y10T29/49336 ,  B29K2309/08

摘要： An apparatus (60) is provided for forming a trailing edge (52) of a wind turbine blade having first and second shells (40, 42). The first and second shells define a gap therebetween, and the apparatus has a first mold component (62) that is adapted to form the first or second shell, and an engaging element (77). The engaging element is configured to securely support a trailing edge component to be coupled to the first and second shells. The engaging element is coupled to the first mold component. The apparatus may additionally include a second mold component (64) that is adapted to form the other of the first or second shells and which is coupled to the first mold component. In this embodiment, the first and second mold components have a closed position in which the first and second shells are closed over one another so as to define a generally closed profile of the wind turbine blade.

摘要翻译： 提供一种装置（60），用于形成具有第一和第二壳（40,42）的风力涡轮机叶片的后缘（52）。 第一和第二壳体之间形成间隙，并且该装置具有适于形成第一或第二壳体的第一模具部件（62）和接合元件（77）。 接合元件构造成可靠地支撑待耦合到第一和第二壳体的后缘部件。 接合元件联接到第一模具部件。 该装置还可以包括适于形成第一或第二壳体中的另一个并且联接到第一模具部件的第二模具部件（64）。 在该实施例中，第一和第二模具部件具有闭合位置，其中第一和第二壳体彼此封闭，以便限定风力涡轮机叶片的大致封闭的轮廓。

公开(公告)号：US20150275922A1

公开(公告)日：2015-10-01

申请号：US14443185

申请日：2014-05-09

申请人： LG ELECTRONICS INC.

发明人： Sang Yuk Son

IPC分类号： F04D29/62 ,  B23K11/00 ,  F04D29/28 ,  F04D17/08 ,  F04D29/42

CPC分类号： F04D29/281 ,  B21D11/20 ,  B21J5/00 ,  B21K3/04 ,  B23K11/0026 ,  B23K11/11 ,  B23K11/115 ,  B23K11/16 ,  B23K26/244 ,  B23K26/32 ,  B23K2101/001 ,  B23K2103/04 ,  F04D17/10 ,  F04D29/282 ,  F04D29/30 ,  F04D29/441 ,  F04D29/626 ,  Y10T29/49329

摘要： A centrifugal fan is provided having a blade configured by bonding two members having plasticity to each other. The centrifugal fan has high durability and permits easy formation of a positive pressure surface or a negative pressure surface of the blade having a complicated shape, which advantageously results in enhancement in performance of the fan.

摘要翻译： 提供了一种离心式风扇，其具有通过将具有可塑性的两个构件彼此结合而构成的叶片。 离心风扇具有高耐久性，容易形成具有复杂形状的叶片的正压表面或负压表面，这有利于提高风扇的性能。

公开(公告)号：US09139297B1

公开(公告)日：2015-09-22

申请号：US13317750

申请日：2011-10-27

申请人： Robert Owen White

发明人： Robert Owen White

IPC分类号： B64C11/24 ,  B64C27/473 ,  B21D53/78 ,  B21K3/00 ,  B21K3/04 ,  B64C11/06 ,  B64C27/18 ,  B64C11/20 ,  B64C27/82 ,  B64C27/22 ,  B64C27/24 ,  B64C27/26 ,  B64C15/14

CPC分类号： B64C27/18 ,  B21D53/78 ,  B21K3/00 ,  B21K3/04 ,  B64C11/06 ,  B64C11/20 ,  B64C11/24 ,  B64C15/14 ,  B64C27/22 ,  B64C27/24 ,  B64C27/26 ,  B64C27/473 ,  B64C27/56 ,  B64C27/82 ,  B64C2027/8245 ,  B64D31/04 ,  Y10T74/20612

摘要： A rotor blade having conduits for supporting control lines is disclosed. The control lines extend from a rotor hub to a tip jet mounted near a distal end of the rotor blade. The conduits mount within leading and trailing edge fairings mounted to a blade spar. The conduits may be supported by bulkheads secured at discrete locations along the blade spar and secured to the leading and trailing edge fairings. The conduits may also be secured to support webs secured to the leading or trailing edge fairing and extending longitudinally therealong. The conduit may have a tapered inner surface and a tapered fitting may secure to the control line to engage the tapered inner surface.

摘要翻译： 公开了一种具有用于支撑控制线的导管的转子叶片。 控制线从转子毂延伸到安装在转子叶片远端附近的尖端喷射器。 导管安装在安装在叶片翼梁上的前缘和后缘整流罩内。 导管可以被固定在沿着叶片翼梁的离散位置处并固定到前缘和后缘整流罩上的隔板支撑。 导管还可以固定到固定到前缘或后缘整流罩上并沿其纵向延伸的支撑腹板。 导管可以具有锥形内表面，并且锥形配件可以固定到控制线以接合锥形内表面。

公开(公告)号：US20150190855A1

公开(公告)日：2015-07-09

申请号：US14577430

申请日：2014-12-19

申请人： ROLLS-ROYCE PLC

发明人： John McBAIN

IPC分类号： B21C23/01 ,  B21J9/02 ,  B21K3/00 ,  B21C23/21

CPC分类号： B21K3/00 ,  B21C23/183 ,  B21J5/025 ,  B21J9/027 ,  B21K3/04

摘要： A forging apparatus and method is disclosed in which an extrusion punch 260 is held between an upper press 210 and a lower press 220 and propelled towards a billet 250 by a ram 240 to form an extruded shaped component 255. The extrusion punch 260 has a striking face 267 in which a recess 268 is formed. During the extrusion process, material 258 from the billet 250 enters the recess so as to lock the extrusion punch 260 and the shaped component 255 together. Accordingly the shaped component 255 is not lifted up with the upper press 210 when it is separated from the lower press 220, and so the position of the shaped component 255 after the forging/extrusion operation is known accurately and reliably.

摘要翻译： 公开了一种锻造设备和方法，其中挤压冲头260保持在上压机210和下压机220之间，并通过冲头240朝向坯料250推进，以形成挤出成型部件255.挤压冲头260具有醒目的 其中形成有凹部268的面267。 在挤出过程中，来自坯料250的材料258进入凹部，以将挤压冲头260和成形部件255锁定在一起。 因此，当与下压机220分离时，成形部件255不会与上压机210一起被提升，因此在锻造/挤压操作之后的成形部件255的位置被准确可靠地公知。

公开(公告)号：US08950070B2

公开(公告)日：2015-02-10

申请号：US13544151

申请日：2012-07-09

申请人： Koji Kimura ,  Takuma Okajima

发明人： Koji Kimura ,  Takuma Okajima

IPC分类号： B21D53/78 ,  B21K3/04

CPC分类号： B21K3/04 ,  Y10T29/49336

摘要： The present invention relates to a method of forging turbine blade, which comprises forging a plurality of turbine blades as an integrally connected body in a longitudinal direction, and then separating the integrally connected body into said respective turbine blades. According to the method of the invention, a yield of material can be improved as compared with the conventional art and the number of processes for forging work can be reduced. In addition, the turbine blades cab be forged into a favorable shape without occurring cracks. Further, it is possible to effectively reduce the cost for the die required for the forging work.

摘要翻译： 涡轮叶片的锻造方法技术领域本发明涉及涡轮叶片的锻造方法，该方法包括沿纵向锻造多个涡轮叶片作为整体连接的主体，然后将整体连接的主体分离成所述各个涡轮叶片。 根据本发明的方法，与传统技术相比，可以提高材料的产量，并且可以减少锻造工序的数量。 此外，涡轮叶片驾驶室锻造成有利的形状而不产生裂缝。 此外，可以有效地降低锻造所需的模具的成本。