EP2524744B1 - Procédé destiné au fabrication d'un élément d'un panneau d'isolation acoustique pour le revêtement de turbomoteur d'aeronef - Google Patents

Procédé destiné au fabrication d'un élément d'un panneau d'isolation acoustique pour le revêtement de turbomoteur d'aeronef Download PDF

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Publication number
EP2524744B1
EP2524744B1 EP12156430.6A EP12156430A EP2524744B1 EP 2524744 B1 EP2524744 B1 EP 2524744B1 EP 12156430 A EP12156430 A EP 12156430A EP 2524744 B1 EP2524744 B1 EP 2524744B1
Authority
EP
European Patent Office
Prior art keywords
surface elements
deformable
surface element
elements
layers
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP12156430.6A
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German (de)
English (en)
Other versions
EP2524744A2 (fr
EP2524744A3 (fr
Inventor
Werner Beck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FORMTECH GmbH
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FORMTECH GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by FORMTECH GmbH filed Critical FORMTECH GmbH
Publication of EP2524744A2 publication Critical patent/EP2524744A2/fr
Publication of EP2524744A3 publication Critical patent/EP2524744A3/fr
Application granted granted Critical
Publication of EP2524744B1 publication Critical patent/EP2524744B1/fr
Not-in-force legal-status Critical Current
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B21D26/027—Means for controlling fluid parameters, e.g. pressure or temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • B21D26/059—Layered blanks
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/92—Making other particular articles other parts for aircraft

Definitions

  • the invention relates to a method for processing at least one surface element, in particular a surface element having openings, as well as a soundproofing insulation, in particular produced by the method, for lining an aircraft engine.
  • a material to be machined such as a titanium alloy is heated to a certain forming temperature and has at extremely low forming speeds an extremely low yield stress and a very large deformation capacity.
  • the deformability is a few hundred percent to over a thousand percent.
  • the US 2006/0210821 A1 discloses a superplastic forming process for making workpieces with complex contours having a cellular core between two outer fluid-tight surface elements.
  • an external pressure is applied to one of the outer surface elements and, on the other hand, fluid is introduced between the outer surface elements in order to form the cellular core of the component.
  • the individual parts of the workpiece, outer surface elements and cellular core, were previously bonded together by means of diffusion bonding.
  • apertures having surface elements can not be reshaped, since they are not medium-tight, that is, it can be constructed with the medium no forming pressure.
  • the components produced therewith disadvantageously have only simple workpiece geometries and are merely cylindrical or conical in shape.
  • the surface elements of nickel base materials, high strength steels or pure titanium, with nickel base materials and steel materials with a high specific gravity and pure titanium with a low strength each have a significant disadvantage over titanium alloys. Aerodynamically favorable and space-saving workpiece geometries with high strength, in which the known disadvantages are avoided, have not been possible.
  • the invention is based on the object to develop a method for processing at least two surface elements to the effect that with the inclusion of breakthroughs of the surface elements certain surface structures with complex curved workpiece geometries can be generated with which, inter alia, spatially curved soundproofing for aircraft engines can be.
  • At least one layer of a deformable, medium-tight material is applied to the surface elements on both sides, the surface elements are inserted together with the deformable layers between at least two mold parts, the clamped deformable layers with a peripherally extending around the surface element edge region between the mold parts, is applied to at least a portion of a surface portion of the inlaid surface elements at a predetermined forming temperature by introducing a medium between one of the deformable layers and a first mold part pressure, the pressure directly against the deformable layer acts, and the surface element by the pressure generated together with the deformable layers hineing in at least one adjacent cavity of a second mold part is formed is provided according to the invention that at least two of the surface elements are joined together by diffusion bonding, that with at least one a perforated, a mesh or mesh structure having surface area a structured surface is produced, and that the surface element after forming from the deformable Layers is taken out.
  • the deformable layers applied to the surface element on both sides it is also possible to work materials which are not or only superficially reshaped with the known, conventional methods.
  • perforations having surface elements and on the other hand medium-density surface elements made of materials that have only limited forming properties can be pressed in a simple manner and with high precision in complex, spatially curved workpiece geometries without a low-maintenance function the deformable layers are not possible.
  • the surface element which is actually to be shaped is held between the deformable layers, wherein this can move relatively during the deformation in a space bounded by the distance between the deformable layers.
  • the introduced medium presses directly against a first of the two deformable layers, indirectly via the first deformable layer against the surface element from which the workpiece or component is formed, and via the surface element also against a second deformable layer.
  • the flow behavior of the actual workpiece is thus given a direction by the deformable layers.
  • the forming process is completed.
  • the surface element can then be taken out of the mold parts together with the deformed layers. After cooling, the surface element is then removed from the envelope of the deformable layers.
  • the deformed, medium-density material layers formed together with the workpiece are only an aid to forming and, in most cases, to be discarded. Multiple use is not or at least not economically possible due to the preferred material to be used of the deformable layers.
  • the deformable layer is to be seen as a "lost part" or consumable material.
  • the deformable layers used for forming consist of a material with a low value and a satisfactory hot forming behavior.
  • sheet metal in particular of micro-duplex steel alloys, is suitable.
  • other high-temperature resistant, deformable, medium-density materials can be used.
  • magnesium at temperatures up to about 380 ° C, aluminum to about 480 ° C, titanium to 700 ° C and 900 ° C, steel to about 1100 ° C.
  • the surface element to be processed does not necessarily have to have superplastic forming properties since it is "positively guided" due to the deformation of the adjacent layers.
  • the surface element to be processed can have openings, so that surface elements with grid, sieve, perforated or network structures can be formed.
  • the surface element is made of a metallic material, such as steel or titanium alloys, with a particular interest in the transformation of titanium aluminides. These can be inserted as a foil or thin sheet metal as well as a thicker plate between the deformable layers.
  • the surface element to be formed for example, but also made of CFRP or other composite materials, if they have a thermoplastic matrix.
  • the blank of the planar element can, if this is fixed between the deformable layers, be smaller, since no edge is needed to clamp the surface element between the mold parts.
  • the deformable layers advantageously have the peripheral area projecting circumferentially around the blank of the planar element. Only the edge regions of the deformable layers are then held in a clamping region between the mold parts, so that the surface element fixed between the layers is optimally positioned for the deformation, that is to say without material losses. Due to the smaller blank of the surface element, the costs can be reduced both in the conversion of surface elements with breakthroughs as well as medium-density surface elements, since the material of the surface element exceeds the value of the deformable layers usually significantly and thus significantly for the costs incurred in carrying out the process is.
  • a gas is usually used as a pressure-generating medium.
  • the medium used is an inert inert gas, such as argon or nitrogen, to avoid undesirable reactions.
  • the surface element Prior to insertion between the mold parts, the surface element can be preheated together with the deformable layers in order to shorten the time required for the actual forming process.
  • the mold parts with the surface element to be formed and the deformable layers to the predetermined forming temperature they are preferably placed in a heating press. The deformation of the surface elements arranged between the mold parts then takes place in the heating press.
  • a release agent must be applied at least between at least one surface section of the planar element and a respectively associated deformable layer. This causes the surface element and the deformable layer after cooling are easily separable.
  • release agents are mainly graphite and boron nitride and yttrium in question.
  • release agents are also applied in the areas where the workpiece or the deformable layers lie against the mold parts, in particular the wall of the cavity, to prevent a "welding" here.
  • the release agent can for example be sprayed liquid onto the surfaces or be inserted as a graphite foil or graphite plate.
  • Layer could also be applied between the surface elements layer of release agent.
  • the at least two surface elements can be connected to one another by diffusion welding.
  • Both the forming and the diffusion welding are preferably combined with each other in a manufacturing cycle of a workpiece, either first being diffusion-welded and then reshaped or first formed and then diffusion-welded.
  • the connection by means of diffusion bonding is achieved by interfacial diffusion of the respective boundary surfaces with each other and offers the possibility of forming a full-surface connection of the surface elements.
  • temperatures of over 900 ° C a specific contact pressure and a certain residence time are required for diffusion bonding.
  • the diffusion welding of the surface elements is carried out in particular under protective gas to prevent adverse effects caused by ambient air or other gas entering, such as oxygen.
  • protective gas to prevent adverse effects caused by ambient air or other gas entering, such as oxygen.
  • multilayer surface elements of which at least one section has openings, they can be formed into complex geometries.
  • Several openings having surface elements can advantageously be connected to each other over the entire surface and thus meet the highest strength requirements.
  • a field of application for such a full-surface welded composite could be a combination of perforated plate and grid or screen or network structures, as they are researched and used to reduce the noise emissions of aircraft engines.
  • a surface structure is impressed to ensure secure bonding with other workpieces.
  • the embossed patterns are largely freely designable and can be incorporated into one of the deformable layers or the wall of the cavity into which the surface element is formed. As with diffusion welding, there are no residual stresses in the material of the workpiece.
  • the invention comprises a device for processing at least one perforations surface element having at least two mold parts, between which at least one receiving area for at least one surface element is arranged, wherein at least a first mold part has a leading to the receiving area medium line with an inlet opening for a pressurizable medium and at least one cavity adjacent to the receiving area is formed at least in a second mold part.
  • This device is characterized in that the first mold part and the second mold part each at least one layer of deformable, medium-density material is assigned, which limit the receiving area for the surface element to the first mold part and to the second mold part out and between the at least one to be formed surface element can be inserted.
  • a first of the deformable layers is preferably arranged such that the region into which the medium is introduced via the inlet opening is sealed off towards a surface element inserted in the receiving region.
  • the inner wall of the cavity is assigned at least one degassing opening.
  • both the degassing opening and the medium line are advantageously assigned to a sealed environment to system to exclude undesirable gases in the process and to allow an economical use of the protective gas.
  • the molds a are assigned and are heated in this to the forming temperature.
  • at least one of the mold parts can advantageously have at least one heating element.
  • both mold parts should have one or more heating elements in order to create a correspondingly optimized arrangement of the heating elements.
  • the aforementioned method or the device can then, inter alia, sound insulation for lining aircraft engines, etc. are made.
  • These have at least two adjoining surface elements, of which at least one has openings, wherein the surface elements have a spatially curved, non-developable geometry and are formed of high-strength, heat-resistant material, and are inventively characterized in that the surface elements a combination of at least form a perforated plate and at least one grid structure, wherein the perforated plate and the grid structure are connected to each other over the entire abutting interface.
  • the surface element Under the spatially curved, non-developable geometry of the surface element is here, for example, a vault structure to understand that is designed in the embodiment as sound insulation for an aircraft, for example, as a half pipe.
  • the half tube has an approximately cylindrical portion and a second portion attached to a slightly widened end portion of the cylindrical portion, which is bulged outward from the cylindrical portion.
  • Two of these half tubes preferably form the sound insulation of an engine, wherein the noise emissions causing air currents or exhaust gases flow to the sound insulation.
  • the noise emissions could be reduced by more than 4db.
  • the surface elements may be arranged with the perforated plates and / or grid structures on the concave inner wall and / or on the convex outer wall. With only one surface element with perforated plate / grid structure, the second wall is to be formed as a closed surface.
  • the individual layers of the surface element of perforated plate and / or grid structure over the entire adjacent interface by means of diffusion welding are connected to each other.
  • the high-strength, heat-resistant material of the surface element is a titanium alloy or Titanaluminidleg réelle. This has a high strength at the same time good weight properties and high heat resistance.
  • Fig. 1 and Fig. 2 each show a process step of forming a perforations having surface element 1 with a device 2.
  • This device 2 comprises a first mold part 3 and a second mold part 4. Between the mold parts 3, 4, a receiving area 5 for a surface element 1 is arranged. Around the receiving area 5 around is a clamping area 6 between the Mold tool parts 3, 4 arranged.
  • the first mold part 3 has a medium line 7 which ends in an inlet opening 8 directed towards the receiving area 5.
  • a cavity 9 is formed, whose wall 10 has the contour of the workpiece to be molded from the surface element 1.
  • the cavity 9 are also associated with degassing 11, 11.
  • Fig. 1 is in the receiving area 5, a surface element 1 between two deformable layers 12, 12 'held, wherein the deformable layers 12, 12' have a larger blank than the surface element 1 and project with its outer edge at respectively opposite sections in the clamping area 6.
  • the surface element 1 corresponds in its dimensions to those of the cavity 9.
  • Fig. 2 is the surface element 1 held between the forming tools 3, 4 Fig. 1 deformed together with the deformable layers 12, 12 'and is enclosed by the deformable layers on the wall 10 of the cavity 9 at.
  • the two mold parts 3, 4 are pressed sealingly outwards against one another and medium is pressed between the first mold part 3 and the deformable layer 12 via the medium line 7 and the inlet opening 8.
  • the pressurized deformable layer 12 is thereby deformed so that it is molded into the cavity 9 together with the surface element 1 and the deformable layer 12 'until the deformable layer 12' completely rests against the wall 10 and a further deformation is not possible is. Gas contained in the cavity 9 can escape completely via the degassing openings 11, 11 '.
  • the surface element 1 can be removed from the mold parts 3, 4 together with the deformed layers 12, 12 'after forming. After the surface element 1 and the deformable layers 12, 12 'are cooled, the surface element 1 and the deformable layers 12, 12' from each other separated. The finished surface element 1 can then be supplied for further processing.
  • a cross-section through a multilayer sheet element 1 is shown. This consists of a layer of perforated plate 13 and three layers with a lattice structure 14, 14 ', 14 ", which are connected to each other by diffusion bonding at the interfaces between the adjacent layers 13, 14, 14', 14" over the entire surface.
  • Fig. 4 shows a manufactured with the inventive method sound insulation 15 for an aircraft engine, which a corresponding Fig. 3 constructed surface element 1 and a further surface element 16 made of sheet metal, wherein the surface element 1 or 16 would be arranged with openings on the inner wall or the outer wall.
  • the sound insulation 15 has a geometry which is formed as a half-tube and has an approximately cylindrical first portion and an attached to a wider end portion of the first portion, bulged outward second portion.
  • the surface elements 1 and 16 are spaced over the entire geometry at substantially the same distance from each other. This distance is predetermined by stiffening structures 17 arranged between the surface elements 1 and 16.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Moulds For Moulding Plastics Or The Like (AREA)

Claims (9)

  1. Procédé destiné au traitement d'au moins deux éléments de surface (1) reposant l'un sur l'autre, dont au moins un présente des percées, dans lequel de chaque côté, au moins une couche (12, 12') respective d'un matériau déformable d'épaisseur moyenne est placée sur les éléments de surface (1), les éléments de surface (1) sont insérés conjointement avec les couches déformables (12, 12') entre au moins deux parties d'outil de moulage (3, 4), les couches déformables (12, 12') sont tendues entre les deux parties d'outil de moulage (3, 4) avec un bord en saillie autour de l'élément de surface (1), de la pression est exercée sur au moins une zone d'un tronçon de surface des éléments de surface (1) insérés, à une température de formage donnée, par l'introduction d'un fluide entre une des couches déformables (12) et une première partie d'outil de moulage (3), sachant que la pression agit directement contre la couche déformable (12), et les éléments de surface (1) sont formés par la pression exercée conjointement avec les couches déformables (12, 12'), dans au moins un espace creux adjacent (9) d'une deuxième partie d'outil de moulage (4), sachant qu'au moins deux des éléments de surface (1) sont reliés entre eux par un soudage par diffusion, caractérisé en ce qu'avec au moins un élément de surface (1) présentant une structure perforée, à crible ou à filet, une surface structurée est produite, et que l'élément de surface (1) est libéré des couches déformables (12, 12') après le formage.
  2. Procédé selon la revendication 1, caractérisé en ce que le fluide est du gaz protecteur.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que les éléments de surface (1) sont pré-chauffés avant le placement entre les parties d'outil de moulage (3, 4).
  4. Procédé selon l'une des revendications 1 à 3, caractérisé en ce que les parties d'outil de moulage (3, 4) sont placées avec les éléments de surface (1) et les couches déformables (12, 12') dans une presse à chaud et chauffées dans celle-ci à la température de formage prédéfinie.
  5. Procédé selon l'une des revendications 1 à 4, caractérisé en ce qu'un moyen de séparation est placé du moins entre au moins un tronçon de surface des éléments de surface (1) et une couche déformable (12, 12') respective correspondante.
  6. Procédé selon l'une des revendications 1 à 5, caractérisé en ce qu'une structure de surface est gravée dans au moins un tronçon de surface des éléments de surface (1).
  7. Panneau d'isolation acoustique pour le revêtement d'un turbomoteur d'aéronef, qui est fabriqué en particulier avec le procédé selon l'une des revendications 1 à 6, comprenant au moins deux éléments de surface reposant l'un sur l'autre, dont au moins un présente des percées, sachant que les éléments de surface (1, 16) présentent une géométrie coudée dans l'espace et ne pouvant pas être déroulée, et sont conçus dans un matériau hautes performances résistant à la chaleur, caractérisé en ce que les éléments de surface (1, 16) forment une combinaison d'au moins une tôle percée (13) et d'au moins une structure à treillis (14, 14', 14''), sachant que la tôle perforée (13) et la structure à treillis (14, 14', 14") sont reliées entre elles par la totalité des surfaces limites reposant l'une sur l'autre.
  8. Panneau d'isolation acoustique selon la revendication 7, caractérisée en ce que l'élément de surface (1, 16) est fabriqué dans un matériau réfractaire.
  9. Panneau d'isolation acoustique selon la revendication 7 ou 8, caractérisée en ce que le matériau hautes performances résistant à la chaleur de l'élément de surface (1, 16) est un alliage de titane ou un alliage d'aluminiure de titane.
EP12156430.6A 2011-05-19 2012-02-22 Procédé destiné au fabrication d'un élément d'un panneau d'isolation acoustique pour le revêtement de turbomoteur d'aeronef Not-in-force EP2524744B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011102087A DE102011102087A1 (de) 2011-05-19 2011-05-19 Verfahren zur Bearbeitung eines Flächenelements

Publications (3)

Publication Number Publication Date
EP2524744A2 EP2524744A2 (fr) 2012-11-21
EP2524744A3 EP2524744A3 (fr) 2013-05-08
EP2524744B1 true EP2524744B1 (fr) 2015-03-25

Family

ID=45656349

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12156430.6A Not-in-force EP2524744B1 (fr) 2011-05-19 2012-02-22 Procédé destiné au fabrication d'un élément d'un panneau d'isolation acoustique pour le revêtement de turbomoteur d'aeronef

Country Status (3)

Country Link
US (1) US20120292126A1 (fr)
EP (1) EP2524744B1 (fr)
DE (1) DE102011102087A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104174752B (zh) * 2014-07-10 2016-04-06 哈尔滨工业大学（威海） 一种异种合金双层板壳复合结构件的制造方法
CN106378375A (zh) * 2016-08-30 2017-02-08 兰州空间技术物理研究所 一种离子推力器用钼栅极的液压成型装置
CN109262153B (zh) * 2018-11-15 2019-12-17 山东大学 一种脉动式高速射流冲击板材连接方法及装置

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3071853A (en) * 1955-10-17 1963-01-08 Solar Aircraft Co Method and apparatus for making brazed honeycomb
US3914969A (en) * 1973-04-18 1975-10-28 Nasa Apparatus for forming dished ion thruster grids
US4559797A (en) * 1983-08-02 1985-12-24 Delaware Method for forming structural parts
EP0192105B1 (fr) * 1985-02-21 1989-05-03 BBC Brown Boveri AG Méthode pour former à chaud au moins une feuille de métal d'une matière difficilement déformable
US4691857A (en) * 1985-11-07 1987-09-08 Trw Inc. Method of shaping a workpiece
US4748837A (en) * 1985-12-11 1988-06-07 Hitachi, Ltd. Method of forming spherical shells
US5016805A (en) * 1988-10-31 1991-05-21 Rohr Industries, Inc. Method and apparatus for dual superplastic forming of metal sheets
US5119535A (en) * 1989-09-18 1992-06-09 The Boeing Company Method of reconfiguring rigid and semirigid structures
GB2241194B (en) * 1990-02-06 1994-07-27 Honda Motor Co Ltd Method for molding fiber-reinforced resin
US5072871A (en) * 1990-06-27 1991-12-17 Compressor Components Textron Inc. Method of making hollow articles
US5118026A (en) * 1991-04-05 1992-06-02 Rockwell International Corporation Method for making titanium aluminide metallic sandwich structures
US5253796A (en) * 1991-07-01 1993-10-19 Rockwell International Corporation Retort for gas diffusion bonding of metals under vacuum
US5330092A (en) * 1991-12-17 1994-07-19 The Boeing Company Multiple density sandwich structures and method of fabrication
GB9304041D0 (en) * 1993-02-27 1993-04-14 British Aerospace Forming of metal articles
US5529480A (en) * 1994-10-28 1996-06-25 The Boeing Company Honeycomb core forming restricter
US6439340B1 (en) * 2000-11-17 2002-08-27 Astech Manufacturing, Inc. Acoustically treated structurally reinforced sound absorbing panel
US6547895B2 (en) * 2001-01-25 2003-04-15 General Motors Corporation Superplastic multi-layer forming
US7588212B2 (en) * 2003-07-08 2009-09-15 Rohr Inc. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip
US7210323B2 (en) * 2003-12-16 2007-05-01 General Motors Corporation Binder apparatus for sheet forming
US7850058B2 (en) * 2004-03-31 2010-12-14 The Boeing Company Superplastic forming of titanium assemblies
US7431196B2 (en) * 2005-03-21 2008-10-07 The Boeing Company Method and apparatus for forming complex contour structural assemblies
US7416105B2 (en) * 2005-05-06 2008-08-26 The Boeing Company Superplastically forming of friction welded structural assemblies

Also Published As

Publication number Publication date
EP2524744A2 (fr) 2012-11-21
EP2524744A3 (fr) 2013-05-08
US20120292126A1 (en) 2012-11-22
DE102011102087A1 (de) 2012-11-22

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