公开(公告)号：WO2017078697A1

公开(公告)日：2017-05-11

申请号：PCT/US2015/058995

申请日：2015-11-04

Applicant: HEWLETT-PACKARD DEVELOPMENT COMPANY, L.P.

Inventor： WU, Kuan-Ting (KT) ,  YANG, Chien-Lung ,  LIAO, Cheng-Feng

IPC: B32B15/08 ,  B32B15/14 ,  B32B37/10

CPC classification number: B32B15/08 ,  B21D26/021 ,  B21D26/055 ,  B21D26/059 ,  B29C70/088 ,  B29C70/86 ,  B29K2705/00 ,  B32B1/02 ,  B32B3/28 ,  B32B7/12 ,  B32B15/082 ,  B32B15/088 ,  B32B15/09 ,  B32B15/14 ,  B32B15/20 ,  B32B27/286 ,  B32B27/288 ,  B32B27/302 ,  B32B27/308 ,  B32B27/34 ,  B32B27/365 ,  B32B37/10 ,  B32B37/12 ,  B32B38/1866 ,  B32B2037/1223 ,  B32B2250/02 ,  B32B2250/40 ,  B32B2255/06 ,  B32B2255/10 ,  B32B2255/26 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/106 ,  B32B2305/22 ,  B32B2307/50 ,  B32B2309/02 ,  B32B2309/12 ,  B32B2311/00 ,  B32B2311/18 ,  B32B2311/24 ,  B32B2313/04

Abstract: Examples of forming metal composites are described herein. In an example, a metal sheet is formed into a predetermined shape using superplastic thermal forming technique. Further, a carbon fiber-reinforced polymer sheet is shaped into the predetermined shape by thermal forming. The metal sheet and the carbon fiber-reinforced polymer sheet are coupled by applying an adhesive between the metal sheet and the carbon fiber-reinforced polymer sheet, to form a metal composite.

Abstract translation: 这里描述了形成金属复合材料的例子。 在一个实例中，使用超塑性热成型技术将金属片形成为预定形状。 此外，碳纤维增强聚合物片材通过热成形成形为预定形状。 金属片和碳纤维增强聚合物片通过在金属片和碳纤维增强聚合物片之间施加粘合剂而连接，以形成金属复合材料。

公开(公告)号：WO2015053955A1

公开(公告)日：2015-04-16

申请号：PCT/US2014/057500

申请日：2014-09-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LATTANZIO, Santiago

IPC: B23K20/00

CPC classification number: B23K20/02 ,  B21D26/055 ,  B21D53/78 ,  B23K20/14 ,  B23K2201/001 ,  B23K2203/14 ,  B23P15/04 ,  F04D29/388 ,  F04D29/644 ,  F05D2220/36 ,  F05D2230/236

Abstract: A method for making a metallic component includes placing a diffusion bonded airfoiled component having an initial shape into a first intermediate shaping die. The first intermediate shaping die has a cavity corresponding to a first intermediate shape different from the initial shape. The component is shaped into the first airfoil shape by applying a first elevated temperature to the first intermediate shaping die. The component is transferred into a final shaping die, which has a cavity corresponding to a target nominal shape different from the first intermediate shape and the initial shape. The component is shaped into a final nominal shape substantially equivalent to the target nominal shape by applying a final elevated temperature to the final shaping die.

Abstract translation: 制造金属部件的方法包括将具有初始形状的扩散接合的翼型部件放置在第一中间成型模具中。 第一中间成型模具具有与初始形状不同的第一中间形状的空腔。 通过将第一升高温度施加到第一中间成型模具将部件成形为第一翼型形状。 将该部件转移到最终成型模具中，该模具具有与不同于第一中间形状和初始形状的目标公称形状对应的空腔。 通过将最终升高的温度施加到最终成型模具，该部件成形为基本上等于目标标称形状的最终标称形状。

公开(公告)号：WO2005065858A1

公开(公告)日：2005-07-21

申请号：PCT/DE2004/002779

申请日：2004-12-21

Applicant: MTU AERO ENGINES GMBH ,  KNOTT, Ulrich ,  KRÜGER, Wolfgang

Inventor： KNOTT, Ulrich ,  KRÜGER, Wolfgang

IPC: B21D26/02

CPC classification number: B21D53/78 ,  B21D26/055 ,  B23K20/02 ,  B23K2201/001 ,  B23P15/04 ,  Y10T29/49339

Abstract: Die Erfindung betrifft ein Verfahren zur Herstellung von Hohlschaufeln, insbesondere for Gasturbinen wie Flugtriebwerke. Mindestens drei Elemente (20, 21, 22) werden sandwichartig übereinander angeordnet, durch Diffusionsschweissen zumindest abschnittsweise miteinander verbunden und im Anschluss durch Aufblähen superplastisch umgeformt, sodass ein erstes Element (20) eine erste Aussenwand der herzustellenden Hohlschaufel, ein zweites Element (22) eine zweite Aussenwand der herzustellenden Hohlschaufel und ein drittes Element (21) ein zwischen den beiden Aussenwänden verlaufendes Mittelelement der herzustellenden Hohlschaufel bildet. Erfindungsgemäss wird in das erste Element (20) und in das zweite Element (22), welche die beiden Aussenwände der herzustellenden Hohlschaufel bilden, vor dem Anordnen derselben zu einer Sandwichstruktur mit dem dritten Element (21) jeweils mindestens eine kerbminimierende Struktur eingebracht.

Abstract translation: 本发明涉及一种用于制造中空叶片，特别是用于燃气涡轮机如飞机发动机的方法。 至少三个元件（20，21，22）被夹在一个在另一个之上，通过扩散焊接至少部分连接在一起，并且超塑性变形通过溶胀，使得第一元件（20）具有所生产的空心叶片的第一外壁以下，第二构件（22） 制造的中空翼片和中心元件的两个外壁之间延伸的第三部件（21）的形成第二外壁要制造中空翼片。 根据本发明，在所述第一元件（20）并且在第二元件（22），其形成所产生的中空翼片的两个外壁，安排他们以形成具有所述第三构件（21）的夹层结构之前每个引入的至少一个凹口最小化的结构。

公开(公告)号：WO2004033127A3

公开(公告)日：2004-05-13

申请号：PCT/US0328621

申请日：2003-09-12

Applicant: GEN MOTORS CORP

Inventor： BRINAS NELSON T ,  RYNTZ EDWARD FRANK

IPC: B21D25/02 ,  B21D26/02 ,  B21D37/16

CPC classification number: B21D26/055 ,  B21D25/02 ,  B21D37/16 ,  Y10S72/701

Abstract: A method of stretch forming an aluminum metal sheet that includes the steps of placing an aluminum metal sheet in a hot forming tool, forming a shaped part at an elevated temperature, removing the hot shaped part from the forming tool, and thereafter transferring the hot shaped part to a cooling fixture. The transfer and removal steps are performed at a speed that is variable based on a correlation of the temperature and strength of the aluminum metal sheet and the speed at which the hot shaped part may be transferred without distortion of its shape due to inertia.

Abstract translation: 一种拉伸成形铝金属片的方法，其包括以下步骤：将铝金属片放置在热成型工具中，在升高的温度下形成成形部件，从成形工具移除热成型部件，然后将热成形 部分到冷却夹具。 转移和去除步骤以基于铝金属片的温度和强度的相关性以及热形状部分可能被转移的速度可变的速度进行，而不会由于惯性而形状变形。

公开(公告)号：WO2003055618A1

公开(公告)日：2003-07-10

申请号：PCT/GB2002/005877

申请日：2002-12-20

Applicant: BAE SYSTEMS PLC ,  PRICE, Howard, James

Inventor： PRICE, Howard, James

IPC: B21D26/02

CPC classification number: B21D26/055 ,  Y10T29/49805 ,  Y10T156/10

Abstract: A process is described of forming a structure by diffusion bonding and superplastic forming at least one skin sheet (16,18) and at least one core sheet (10, 12), the process comprising: a) forming a pack from the at least one skin sheet (16,18) and the at least one core sheet (10,12); b) placing the pack in a mould (20) and heating the pack to a temperature at which the sheets are capable of superplastic deformation; c) injecting a gas between the skin sheet (16,18) and the core sheet (10,12) to urge the skin sheet against an internal face of the mould (20) thereby forming a cavity (30) between the skin sheet (16,18) and the core sheet (10,12); d) injecting gas on the side of the core sheet (10,12) remote from the skin sheet (16,18) to urge the core sheet (10,12) against the skin sheet (16,18), e) maintaining gas pressure on the said side of the core sheet (10, 12), thereby forming a diffusion bond between the skin sheet (16,18) and the core sheet (10,12); and f) maintaining a regulated pressure of helium in the cavity (30) between the skin sheet (16,18) and the core sheet (10,12) during at least part of step d). The use of helium in the cavity allows such gas trapped in a pocket gas between the skin sheet (16,18) and the core sheet (10,12) to diffuse through the core sheet to eliminate such pockets, which obstruct the formation of diffusion bonds in step e).

Abstract translation: 描述了通过扩散粘合和超塑性成形至少一个表皮片（16,18）和至少一个芯片（10,12）形成结构的方法，该方法包括：a）从至少一个 皮肤片（16,18）和所述至少一个芯片（10,12）; b）将包装件放置在模具（20）中并将包装件加热到片材能够超塑性变形的温度; c）在皮肤片（16,18）和芯片（10,12）之间注入气体以将皮肤片材压靠在模具（20）的内表面上，从而在皮肤片材（30） 16,18）和所述芯片（10,12）; d）在远离皮肤片（16,18）的芯片（10,12）侧注入气体以将芯片（10,12）推压在皮肤片（16,18）上，e）保持气体 在芯片（10,12）的所述侧面上施加压力，从而在表皮片（16,18）和芯片（10,12）之间形成扩散结合。 以及f）在步骤d）的至少一部分期间，在皮肤片（16,18）和芯片（10,12）之间的空腔（30）中保持氦的调节压力。 在空腔中使用氦使得捕获在皮肤片（16,18）和芯片（10,12）之间的袋状气体中的这种气体能够扩散通过芯片以消除阻碍扩散形成的这种口袋 步骤e）中的键。

公开(公告)号：WO99062653A1

公开(公告)日：1999-12-09

申请号：PCT/US1999/009585

申请日：1999-04-30

IPC: B21D26/055 ,  B21D26/02

CPC classification number: B21D26/055 ,  Y10T29/49805

Abstract: A method is disclosed for stretching sheet blanks (60), especially superplastic sheets, by differential gas pressure into conformity with a female die surface (38, 40, 42, 44) without encountering excessive thinning or tearing of the sheet (60). The warned SPF sheet is draped over a preformed surface (50) to draw more of the sheet material into the die cavity (46) before the edges (62) of the sheet (60) are fixedly clamped whereby the additional formable material is used in forming the product, thereby reducing thinning and tears.

Abstract translation: 公开了一种用于通过差分气体压力拉伸板坯（60），特别是超塑性片材而与母模表面（38,40,42,44）一致的方法，而不会遇到片材（60）的过度变薄或撕裂。 警告的SPF片材覆盖在预成型的表面（50）上，以在片材（60）的边缘（62）被固定夹紧之前将更多的片材材料吸入模腔（46），由此使用另外的可成形材料 形成产品，从而减少变薄和撕裂。

公开(公告)号：WO1998007547A1

公开(公告)日：1998-02-26

申请号：PCT/US1997014587

申请日：1997-08-19

Applicant: McDONNELL DOUGLAS CORPORATION ,  PRUITT, Mark, O. ,  ROSS, Christopher, A.

Inventor： McDONNELL DOUGLAS CORPORATION

IPC: B23P15/00

CPC classification number: B21D26/055 ,  Y10T29/49339 ,  Y10T29/49622 ,  Y10T29/49623

Abstract: A method of forming a hollow structure having a predetermined shape from a sheet of superplastic material. The sheet is initially formed into a preform configuration (10). A reusable fluid inlet tube is placed in the preform configuration (10) to define a port in fluid communication with the interior portion of the preform configuration (10). The preform configuration (10) is disposed in a containment die, which defines a cavity having the predetermined desired shape. Force is applied to the containment die to temporarily seal the edges of the preform configuration without the use of welding or diffusion bonding. Once its edges are sealed, the preform configuration becomes a gas-tight envelope capable of holding fluid that is introduced through the fluid inlet tube. Fluid is fed through the tube to apply internal pressure to the gas-tight preform configuration under superplastic conditions while it is still being held in the containment die.

Abstract translation: 从超塑性材料片形成具有预定形状的中空结构的方法。 片材最初形成预成型件构型（10）。 可重复使用的流体入口管被放置在预成型件构型（10）中以限定与预成型件构型（10）的内部流体连通的端口。 预成型件构造（10）设置在容纳模具中，其限定具有预定所需形状的空腔。 将力施加到容纳模具上以临时密封预成型件构造的边缘，而不使用焊接或扩散粘合。 一旦其边缘被密封，则预成型件构型变成能够保持通过流体入口管引入的流体的气密外壳。 流体通过管进料，在超塑性条件下将内部压力施加到气密预制件构型上，同时它仍然保持在容纳模具中。

公开(公告)号：WO1997027045A2

公开(公告)日：1997-07-31

申请号：PCT/US1996020115

申请日：1996-12-20

Applicant: THE BOEING COMPANY ,  BULDHAUPT, Frederick, W. ,  FISCHER, John, R. ,  KISTNER, Matthew, G. ,  WILL, Jeffrey, D.

Inventor： THE BOEING COMPANY

IPC: B32B00/00

CPC classification number: B64C1/12 ,  B21D26/055 ,  B21D47/00 ,  B23K26/037 ,  B23K26/123 ,  B23K26/206 ,  B23K26/244 ,  B23K26/26 ,  B23K26/28 ,  B23K26/38 ,  B23K2101/02 ,  B64C2001/0081 ,  Y10T29/18 ,  Y10T29/49371 ,  Y10T428/1234 ,  Y10T428/12347 ,  Y10T428/12361 ,  Y10T428/12375

Abstract: A superplastically formed, diffusion bonded sandwich structure having integral metal hardpoints, made by joining two superplastic metal core sheets together into a core pack by welding or diffusion bonding along a pattern of lines which form junction lines between the core sheets when the pack is inflated by gas pressure at superplastic temperatures. Face sheets are laid under and over the core pack and metal inserts are interposed between the face sheets and the core. All of the sheets in the pack are sealed together around an outside peripheral edge to create a gas tight envelope. The pack is heated to superplastic temperatures in a cavity in a die, and the top and bottom face sheets are diffusion bonded to top and bottom surfaces of the metal insert by application of heat and pressure from top and bottom inner surfaces of the die cavity. While at superplastic temperatures, the pack is inflated by gas pressure against inside surfaces of a die to form an expanded metal sandwich structure having integral webs and integral hardpoints formed by the metal insert. After forming, the gas pressure is reduced to near atmospheric, the die is opened and the part is removed from the die.

Abstract translation: 一种具有整体金属硬点的超塑性扩散粘结夹层结构，其通过沿着线形图案通过焊接或扩散接合将两个超塑性金属芯片连接在一起，制成芯组件，该芯线在芯片片材之间形成连接线 在超塑性温度下的气体压力。 将面片放置在芯组件的下面和后面，金属插入件插入在面片和芯之间。 包装中的所有片材围绕外围边缘密封在一起以形成气密封壳。 将包装件加热到模具中的空腔中的超塑性温度，并且通过从模腔的顶部和底部内表面施加热和压力将顶部和底部面板扩散结合到金属插入件的顶部和底部表面。 当在超塑性温度下，该组件通过气压对模具的内表面进行充气，以形成具有整体网状物和由该金属插入件形成的整体硬点的多孔金属夹层结构。 成型后，将气体压力降低至接近大气压，打开模具，将模具从模具中取出。

公开(公告)号：WO1997013683A1

公开(公告)日：1997-04-17

申请号：PCT/FR1996001594

申请日：1996-10-11

Applicant: AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE ,  DONAL, Valérie ,  ANDRE, Joël, René ,  BOURIQUET, Jacques

Inventor： AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE

IPC: B64C01/00

CPC classification number: B21D26/055 ,  B21D26/021 ,  B23K20/023 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43

Abstract: A hollow, integral asymmetrical metal structure, e.g. an aircraft wing slat trailing edge, including two gradually diverging outer skins (16, 18) with differing curvatures joined together at one edge (20). The structure further includes internal reinforcements defining pairs of cells (26, 28) separated by an intermediate partition. The structure is produced by diffusion welding and superplastic moulding without opening the die. To take into account the dissymmetry, portions (40, 42) are cut out of the skin (18) that is elongated the most during forming and the cut portions (44, 46) are attached to the other skin (16).

Abstract translation: 中空的整体不对称金属结构，例如 飞机翼板后缘，包括在一个边缘（20）处连接在一起的不同曲率的两个逐渐发散的外表皮（16,18）。 该结构进一步包括限定由中间隔板隔开的单元格对（26,28）的内部增强件。 该结构通过扩散焊接和超塑性成型而不打开模具而产生。 为了考虑不对称性，从成形期间最细长的皮肤（18）切出部分（40,42），并且切割部分（44,46）附接到另一个皮肤（16）。

公开(公告)号：WO2012163840A1

公开(公告)日：2012-12-06

申请号：PCT/EP2012/059856

申请日：2012-05-25

Applicant: AIRBUS OPERATIONS GMBH ,  FREERK, Syassen

Inventor： FREERK, Syassen

IPC: B21D26/055 ,  B21D26/031

CPC classification number: B21D26/031 ,  B21D26/055

Abstract: The invention concerns a device (10) for the superplastic forming of a blank (16) in a mould (20) with a lower mould (14) and an upper mould (12) into a component, in particular a suction component (46, 54), with a three-dimensional geometry, wherein the blank (16) in the mould can be subjected for purposes of forming to pressure and temperature, and the blank (16) has perforations (18), at least in some regions. In accordance with the invention the lower mould (14) is formed at least partly with a permeable, in particular a gas permeable drainage layer (28). As a consequence of the gas permeable drainage layer (28) a blank (16) designed with perforations (18) in at least some regions can be formed directly, i.e. without further aids such as e.g. a means of sealing, etc and/or supplementary production operations, in the course of a superplastic forming process into a component, in particular into a suction component (46, 54) for an active aerodynamic surface of an aircraft, with a complex three-dimensional spatial shape and perforations (56) in at least some regions.In particular the device (10) enables production using a simple, cost-effective and reliable process that is suitable for large production runs of such components, spherically curved in at least some regions.

Abstract translation: 本发明涉及一种用于在具有下模具（14）和上模具（12）的模具（20）中超塑性成型坯料（16）的装置（10），该模具（14）和上模具（12）特别是吸入部件 54），其具有三维几何形状，其中模具中的坯料（16）可以经受形成压力和温度的目的，并且坯料（16）至少在一些区域具有穿孔（18）。 根据本发明，下模具（14）至少部分地形成有可渗透的，特别是气体可渗透的排水层（28）。 作为气体可渗透排水层（28）的结果，可以直接形成在至少一些区域中设计有穿孔（18）的坯料（16），即没有其它辅助材料，例如， 在超塑性成型过程中，特别是用于飞行器的主动空气动力学表面的抽吸部件（46,54）中的密封等和/或补充生产操作的方法， 至少一些区域中的三维空间形状和穿孔（56）。特别地，装置（10）能够使用简单，成本有效和可靠的方法进行生产，其适用于大量生产运行的这些部件，其至少在一些 区域。