EP0502620A1 - Perfectionnement relatif aux composants formés superplastiquement - Google Patents
Perfectionnement relatif aux composants formés superplastiquement Download PDFInfo
- Publication number
- EP0502620A1 EP0502620A1 EP19920301205 EP92301205A EP0502620A1 EP 0502620 A1 EP0502620 A1 EP 0502620A1 EP 19920301205 EP19920301205 EP 19920301205 EP 92301205 A EP92301205 A EP 92301205A EP 0502620 A1 EP0502620 A1 EP 0502620A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sheet
- face
- sheets
- additional
- main
- 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.)
- Withdrawn
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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
- B21D26/053—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
- B21D26/055—Blanks having super-plastic properties
Definitions
- This invention relates to an improved method of forming components from materials having superplastic characteristics, and in particular to the use of additional sheets of material to improve the strength characteristics of formed components.
- Metals having superplastic characteristics such as titanium and many of its alloys, have a composition and microstructure such that, when heated to within an appropriate range of temperature and when deformed within an appropriate range of strain rate, they exhibit the flow characteristics of a viscous fluid.
- the condition in which these characteristics are attained is known as superplasticity, and, in this condition, the metals may be deformed so that they undergo elongations of several hundred percent without fracture or significant necking. This is due to the fine, uniform grain structures of superplastically formable metals which, when in the condition of superplasticity, allow grain boundary sliding by diffusion mechanisms so that the individual metal crystals slide relative to one another.
- Diffusion bonding is often combined with superplastic forming to enable the manufacture of multi-sheet components of complex structure.
- the diffusion bonding process concerns the metallurgical joining of surfaces by applying heat and pressure which results in the co-mingling of atoms at the joint interface, the interface as a result becoming metallurgically undetectable.
- bond inhibitors commonly known as stop-off or stopping-off materials
- Titanium in sheet form, has in its received state the characteristics needed for superplastic forming, and because it will absorb its own oxide layer at high temperature in an inert atmosphere to provide an oxide-free surface, it is also particularly amenable to diffusion bonding under pressure.
- the optimum temperature for this self-cleaning is 930°C which is also the optimum superplastic forming temperature.
- SPF superplastic forming
- DB diffusion bonding
- a method of manufacturing a component from a main sheet of superplastically formable material and at least one additional sheet of superplastically formable material having a face of smaller area than a face of said main sheet including the steps of overlaying said face of the at least one additional sheet on said face of the main sheet prior to superplastically forming the component, and superplastically forming the component such that after forming said face of the at least one additional sheets is substantially in contact with said face of said main sheet.
- said component is manufactured from a plurality of main sheets over at least one of which at least one additional sheet of material is laid; selected areas of said main and additional sheets are pretreated with a bond inhibitor or to which a stop-off material has been applied;
- main and additional sheets are laid over one another and diffusion bonded as required and superplastically formed in a mould to form a component with a cellular internal structure and having a thickened region where said additional sheet is present.
- said at least one additional sheet of material is positioned on said main sheet in a region which when the main and additional sheets are positioned on a form tool will coincide with a region on the form tool which defines a recess or protrusion, the main and additional sheets being formed into said component by placing them in the form tool and applying heat and pressure.
- said face of the at least one additional sheet is spot welded to said face of the main sheet prior to superplastic forming.
- said face of the at least one additional sheet is line bonded to said face of the main sheet prior to superplastic forming.
- said face of the at least one additional sheet is diffusion bonded to said face of the main sheet prior to superplastic forming.
- doubler is used to refer to additional sheet(s) of material.
- Fig. 1B shows a cross-section through the assembly of skin and core sheets transverse to the line bonds 5.
- the core sheets 2 and 3 of this 4-sheet "pack" are pressed together at 930°C so that diffusion bonding between the core sheets 2 and 3 takes place at the line bonds but is inhibited elsewhere wherever the stop-off material is laid.
- Fig. 1C shows how the bonded pack is clamped between the two halves of a nickel chromium steel mould 6, heated to 930°C and an inert gas introduced under pressure via suitable gas pipe connections to regions between the 4-sheets of the pack.
- the inert gas is introduced initially to the regions between the skin and core sheets, and subsequently between the core sheets, the sheets deform superplastically and bow out towards the inner mould surfaces, as shown by the dotted lines.
- the core sheets 2 and 3 do not separate at the diffusion bonded line bonds 5.
- the structure superplastically deforms to correspond to the inner shape of the mould but, because of the line bonding, vertical walls of titanium alloy are formed at regular intervals throughout the structure as shown in Fig. 1D.
- Fig. 2a is shown a plan view of a core sheet 7 of superplastically formable and diffusion bondable material having an inner area X bounded by a border 8 which is to be superplastically deformed and an outer area Y bounded by a border 9 which is to cooperate with the clamping surfaces of a forming tool, such as that shown at 6 in Fig. 1C, and via which inflating gas will be introduced to the inner surface 8 by means of breakthrough areas (not shown).
- a bond line 10 defines an area of the area X which during subsequent diffusion bonding bonds to an adjacent identical core sheet.
- a stop-off material, or bond inhibitor is applied by any known method, for example silk screen printing, to all areas of the inner area X except the bond line and a rectangular area Z bounded by a border 11 (shown dotted) in the centre of the area X.
- the area Z is that part of the finished cellular structure where thickening is required.
- a rectangular doubler 12 of identical superplastically deformable diffusion bondable material to that of the core sheet 7 and having chamfered edges and dimensions identical to the area Z is laid over the area Z.
- the bond line 10 is continued over the surface of the doubler 12 which is otherwise treated with stop-off.
- the sheet 7 and its overlaid doubler will be assembled into a bond pack in the manner shown in Fig. 1B.
- the sheet and doubler will be positioned as one of the core sheets, say 2 in Fig. 1B.
- An identical combination of core sheet and doubler will form the other core sheet, in this case 3 in Fig. 1B, and so that the two doublers will be in contact.
- the core sheets 2 and 3 Prior to the skin sheets 1 and 4 being overlaid onto the core sheets 2 and 3, the core sheets 2 and 3 are subjected to diffusion bonding pressure at 930 degrees C.
- the doublers diffusion bond to their respective core sheets 7 in the regions Z.
- Each pair of core sheets and doublers also diffusion bond to each other along the bond line 10.
- the pack is then assembled as shown in Figure 1B.
- the bond pack is placed in a steel mould tool, for example 6 in Fig. 1C, being clamped by the mould faces at the area Y.
- the temperature of the tool is raised to 930 degrees C in a suitable furnace and Argon gas is initially introduced to the regions between the skin and core sheets 1, 2 and 3, 4 to blow them under uniform pressure to the designed shape, for example as shown in Fig. 1D.
- Argon gas is initially introduced to the regions between the skin and core sheets 1, 2 and 3, 4 to blow them under uniform pressure to the designed shape, for example as shown in Fig. 1D.
- the regions between the core sheets 2 and 3 are similarly blown under pressure, and form the vertical walls of the component.
- the application of pressure may also result in the diffusion bonding of surfaces as they come into contact with one another.
- Fig. 2B is a view then on section A-A in Fig. 2A and shows the formed thickened support wall 13.
- the thickness of the skin at 14 is thin and corresponds approximately to the thickness of the skins 1 and 4 in Fig. 1B before DB/SPF.
- Regions 15, where the support wall joins the outer skin 14 are also thickened due to the doubler and the dimensions of this region 15 are clearly determined by the width of the doubler in relation to the height of the SPF mould tool.
- Fig. 2C is a section on B-B in Fig. 2A after SPF/DB and shows the formed structure in the region of a non-thickened support wall 16.
- Fig. 3 shows a cross-section through a formed cellular structure in which doublers had been applied to both upper and lower skins (1 and 4 in Fig. 1B) in the region of a support wall formed by the core sheets (2 and 3 in Fig. 1B).
- the skin reinforcing doublers have resulted in thickened areas 17 which due to the constraints of the mould tool have resulted in uniformly flat outer skins but humped inner surfaces in the region of the support walls 18.
- skin doublers may now be employed in structures made from any plurality of SPF sheets not just 4-sheet cellular structures.
- the doublers When used to reinforce outer skins in 4-sheet structures, the doublers need not reinforce regions adjacent inner support walls formed from core sheets, but may thicken any area of the outer skin.
- Doublers may also be employed in the manufacture of surfaces which require large recesses or protrusions to avoid localised weakening in these areas due to the excessive localised elongation.
- Such a surface is shown in Figure 4 at 50 and forms part of the leading edge of a wing 52.
- Figure 5 shows the main sheet 54 from which the surface is to be formed, and onto which three additional sheets (doublers) 56, 58 and 60 have been laid.
- the additional sheets 56, 58 and 60 are positioned in the region where the recess is required in the finished component.
- the sheets 56, 58 and 60 are attached to the main sheet and to one another by spot welding, line bonding or diffusion bonding.
- spot welding and line bonding for example at opposing sides of the mound formed by the additional sheets, allow all the sheets to move relative to one another where they are not bonded during subsequent superplastic forming. If the sheets are diffusion bonded in their contacting areas then this relative movement will not be possible.
- the lower tool of a form tool for the manufacture of the surface 50 is shown at 62 in Figure 6.
- the region 64 will define the recess in the wing leading edge.
- Figure 7 shows the assembly of Figure 5, positioned between the two members of a form tool 66.
- the assembly is heated to a temperature at which the sheets of material become superplastic (930°C for example).
- Gas pressure is applied to the sheets via a gas feed line (not shown). This forces the sheets into the cavity of the lower tool 62, and hence forms the leading edge for the wing 52 - as illustrated in Figure 4.
- the doublers are positioned so that they coincide with the region 64 of the lower tool 62 (which forms the recess in the wing leading edge). It will be apparent that where the sheets 54 - 60 are forced against region 64, they undergo a greater degree of elongation than in other areas (which can result in localised thinning). The presence of the doublers compensates for this and result in the finished component having an approximately uniform thickness.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9103804 | 1991-02-23 | ||
GB919103804A GB9103804D0 (en) | 1991-02-23 | 1991-02-23 | Improvements relating to diffusion bonded/superplastically formed cellular structures |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0502620A1 true EP0502620A1 (fr) | 1992-09-09 |
Family
ID=10690458
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19920301205 Withdrawn EP0502620A1 (fr) | 1991-02-23 | 1992-02-13 | Perfectionnement relatif aux composants formés superplastiquement |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0502620A1 (fr) |
GB (1) | GB9103804D0 (fr) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2263081A (en) * | 1992-01-10 | 1993-07-14 | Mitsubishi Heavy Ind Ltd | Superplastic forming of sandwich panel |
EP0601773A1 (fr) * | 1992-12-09 | 1994-06-15 | British Aerospace Public Limited Company | Façonnage de joints soudés par diffusion sur des structures métalliques réalisées par formage superplastique |
WO1995027575A1 (fr) * | 1994-04-07 | 1995-10-19 | The Boeing Company | Preetirage pour formage de materiaux superplastiques |
GB2295981A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Method of manufacturing structural parts, particularly for use in aircraft |
GB2295980A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Superplastically formed panel |
WO2000016925A1 (fr) * | 1998-09-18 | 2000-03-30 | Rolls-Laval Heat Exchangers Limited | Procede de fabrication d'un article par formage a chaud |
WO2003055618A1 (fr) * | 2001-12-21 | 2003-07-10 | Bae Systems Plc | Procede de formage superplastique et de liaison par diffusion |
US6736919B1 (en) | 1997-05-28 | 2004-05-18 | Structural Laminates Company | Method for making a laminate and laminate obtainable by said method |
DE102007056837A1 (de) * | 2007-11-26 | 2009-05-28 | Michael Hamberger | Vorrichtung und Herstellungsverfahren für ein Vakuum-Isolier-Element besthend aus einem mehrere Kammern definierendes Dämmmaterial |
US8844796B1 (en) | 2013-03-05 | 2014-09-30 | The Boeing Company | Superplastically formed ultrasonically welded metallic structure |
EP3446804A1 (fr) | 2017-08-22 | 2019-02-27 | BAE SYSTEMS plc | Formage superplastique et procédé de liaison par diffusion |
EP3446805A1 (fr) | 2017-08-22 | 2019-02-27 | BAE SYSTEMS plc | Formage superplastique et procédé de liaison par diffusion |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4304821A (en) * | 1978-04-18 | 1981-12-08 | Mcdonnell Douglas Corporation | Method of fabricating metallic sandwich structure |
US4361262A (en) * | 1980-06-12 | 1982-11-30 | Rockwell International Corporation | Method of making expanded sandwich structures |
GB2109711A (en) * | 1981-11-24 | 1983-06-08 | Grumman Aerospace Corp | Method for superplastic forming and diffusion bonding complex continuous structures |
-
1991
- 1991-02-23 GB GB919103804A patent/GB9103804D0/en active Pending
-
1992
- 1992-02-13 EP EP19920301205 patent/EP0502620A1/fr not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4304821A (en) * | 1978-04-18 | 1981-12-08 | Mcdonnell Douglas Corporation | Method of fabricating metallic sandwich structure |
US4361262A (en) * | 1980-06-12 | 1982-11-30 | Rockwell International Corporation | Method of making expanded sandwich structures |
GB2109711A (en) * | 1981-11-24 | 1983-06-08 | Grumman Aerospace Corp | Method for superplastic forming and diffusion bonding complex continuous structures |
Cited By (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2263081B (en) * | 1992-01-10 | 1995-02-15 | Mitsubishi Heavy Ind Ltd | Method for making metallic sandwich panels |
GB2263081A (en) * | 1992-01-10 | 1993-07-14 | Mitsubishi Heavy Ind Ltd | Superplastic forming of sandwich panel |
EP0601773A1 (fr) * | 1992-12-09 | 1994-06-15 | British Aerospace Public Limited Company | Façonnage de joints soudés par diffusion sur des structures métalliques réalisées par formage superplastique |
US5823032A (en) * | 1994-04-07 | 1998-10-20 | The Boeing Company | Prethinning for superplastic forming |
WO1995027575A1 (fr) * | 1994-04-07 | 1995-10-19 | The Boeing Company | Preetirage pour formage de materiaux superplastiques |
US5916316A (en) * | 1994-04-07 | 1999-06-29 | The Boeing Company | Deep draw superplastically formed part using prethinning |
US5647239A (en) * | 1994-04-07 | 1997-07-15 | The Boeing Company | Die for superplastic forming |
GB2295980A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Superplastically formed panel |
US5809737A (en) * | 1994-12-16 | 1998-09-22 | British Aerospace Plc | Structural parts for use in aircraft |
GB2295981B (en) * | 1994-12-16 | 1997-07-30 | British Aerospace | Method of manufacturing structural parts, particularly for use in aircraft |
GB2295981A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Method of manufacturing structural parts, particularly for use in aircraft |
US6039239A (en) * | 1994-12-16 | 2000-03-21 | British Aerospace Plc | Method of manufacturing structural parts, particularly for use in aircraft |
GB2295980B (en) * | 1994-12-16 | 1998-02-25 | British Aerospace | Superplastically formed panel |
US6736919B1 (en) | 1997-05-28 | 2004-05-18 | Structural Laminates Company | Method for making a laminate and laminate obtainable by said method |
WO2000016925A1 (fr) * | 1998-09-18 | 2000-03-30 | Rolls-Laval Heat Exchangers Limited | Procede de fabrication d'un article par formage a chaud |
WO2003055618A1 (fr) * | 2001-12-21 | 2003-07-10 | Bae Systems Plc | Procede de formage superplastique et de liaison par diffusion |
US7134176B2 (en) | 2001-12-21 | 2006-11-14 | Bae Systems Plc | Superplastic forming and diffusion bonding process |
DE102007056837A1 (de) * | 2007-11-26 | 2009-05-28 | Michael Hamberger | Vorrichtung und Herstellungsverfahren für ein Vakuum-Isolier-Element besthend aus einem mehrere Kammern definierendes Dämmmaterial |
US8844796B1 (en) | 2013-03-05 | 2014-09-30 | The Boeing Company | Superplastically formed ultrasonically welded metallic structure |
US9527571B2 (en) | 2013-03-05 | 2016-12-27 | The Beoing Company | Superplastically formed ultrasonically welded metallic structure |
EP3446804A1 (fr) | 2017-08-22 | 2019-02-27 | BAE SYSTEMS plc | Formage superplastique et procédé de liaison par diffusion |
EP3446805A1 (fr) | 2017-08-22 | 2019-02-27 | BAE SYSTEMS plc | Formage superplastique et procédé de liaison par diffusion |
Also Published As
Publication number | Publication date |
---|---|
GB9103804D0 (en) | 1991-04-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 19920220 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE ES FR GB IT |
|
RAP3 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY |
|
17Q | First examination report despatched |
Effective date: 19940923 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 19950204 |