GB2029304A - Method of making a metallic structure - Google Patents
Method of making a metallic structure Download PDFInfo
- Publication number
- GB2029304A GB2029304A GB7836128A GB7836128A GB2029304A GB 2029304 A GB2029304 A GB 2029304A GB 7836128 A GB7836128 A GB 7836128A GB 7836128 A GB7836128 A GB 7836128A GB 2029304 A GB2029304 A GB 2029304A
- Authority
- GB
- United Kingdom
- Prior art keywords
- preform
- forging
- temperature range
- superplastic forming
- shaping
- 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.)
- Granted
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
Abstract
A method for making metallic structures especially those having a complex variable thickness, utilizes superplastic forming and forging. A metal preform having superplastic characteristics is positioned relative to a shaping member which substantially defines the final configuration of the preform. The preform is superplastically expanded and forged against the shaping member to produce the final structure.
Description
SPECIFICATION
Method of making a metallic structure
The present invention relates to a process for fabricating metallic structures utilizing superplastic forming and forging. For many years it has been known that certain metals, such as titanium and many of its alloys, exhibit superplasticity. Superplasticity is the capability of a material to develop unusually high tensile elongations with reduced tendency towards necking. This capability is exhibited by only a few metals and alloys and within limited temperature and strain rate range. An example of the superplastic forming process is disclosed in U.S.
Patent No. 3,340,101, to Fields, Jr., et al.
However, superplastic forming by its very nature, (i.e. reduced tendency toward necking) produces a constant overall deformation such that the thickness of the final structure is substantially the same throughout. Accordingly, superplastic forming is not used to fabricate many variable thickness fittings and clips which typically are machined from bar, plate or forging stock at high cost and with attendant substantial waste of material.
It is, therefore, an object of the present invention to efficiently fabricate complex variable thickness structures.
It is another object of the present invention to make metallic structures in a single operation by a combination of superplastic forming and forging.
It is still another object of the present invention to fabricate deep drawn variable thickness parts.
Briefly, in accordance with the invention, there is provided a method for making metallic structures which combines superplastic forming and forging. A metal preform having superplastic characteristics and a shaping member which substantially defines the final configuration of the preform are provided. The preform is brought to within a temperature range suitable for superplastic forming. Pressure is applied to the preform to cause at least a portion thereof to expand superplastically. At least a portion of the preform is forged against the shaping member.
In a preferred embodiment, two shaping members are provided and the preform is superplastically expanded and deformed against at least one of the shaping members and forged between the shaping members. Optimally, the temperature range suitable fqr superplastic forming of the preform is also suitable for forging of the preform.
Other objects and advantages of the invention will become apparent upon reading the following detailed description and upon reference to the drawings.
Figure 1 is a cross-sectional diagrammatic illustration of a first embodiment of the present invention illustrating the initial position of the preform relative to the shaping members at A, an intermediate position upon completion of superplastic forming at B, and the final formed structure after forging at C;
Figure 2 is a cross-sectional diagrammatic
illustration of a second embodiment of the present
invention illustrating the initial position of the
preform relative to the shaping members at A, an
intermediate position upon completion of superplastic forming at B, and the final Tormed structure after completion of forging at C;;
Figure 3 is a cross-sectional diagrammatic
illustration of a third embodiment of the present
invention illustrating the initial position of the
preform relative to the shaping members at A,
intermediate positions of the preform at B shown
by the broken lines which illustrates a position of
the preform during superplastic forming and the
solid lines which illustrate the position of the
preform after completion of superplastic forming,
and the final formed structure after completion of forging at C;
Figure 4 is a cross-sectional diagrammatic
illustration of a fourth embodiment of the present
invention illustrating the initial position of the preform relative to the shaping members at A, an
intermediate position of the preform after
completion of forging at B, and the final formed
structure after completion of superplastic forming
at C.
While the invention will be described in
connection with the preferred embodiments, it will
be understood that it is not intended to limit the
invention to those embodiments. On the contrary,
it is intended to cover all alternatives,
modifications, and equivalents that may be
included within the spirit and scope of the
invention as defined by the appended claims.
In order for superplastic'forming to be successful. it is necessary to use a material that is suitable. The extent to which any material selected will exhibit superplastic properties is predictable in general terms from a determination of its strain rate sensitivity and a design determination of the permissible variation of wall thickness. Strain rate sensitivity can be defined as m where d in a m= d in E and a is stress in pounds per square inch and E is strain rate in reciprocal minutes. Strain rate sensitivity may be determined by a simple and now well recognized torsion test described in the article "Determination of Strain-Hardening Characteristics by Torsion Testing," by D. S.
Fields, Jn, and W. A. Backofen, published in the proceedings of the ASTM, 1 957, Volume 57, pages 1259-1272. A strain rate sensitivity of about 0.5 or greater can be expected to produce satisfactory results with the larger the value (to a maximum of 1) the greater the superplastic properties. Maximum strain rate sensitivity in metals is seen to occur, if at all, as metals are deformed near the phase transformation temperature. Accordingly, the temperature immediately below the phase transformation temperature can be expected to produce the
greatest strain rate sensitivity. For titanium and its
alloys the temperature range within which superplasticity can be observed is about 14500F to about 1 8500F depending upon the specific alloy used.
Other variables have been found to affect strain rate sensitivity and therefore should be considered in selecting a suitable metal material. Decreasing grain size results in correspondingly higher values for strain rate sensitivity. It has been found that the m-value reaches a peak at an intermediate value of strain rate (approximately 10-4 in./in./sec.). For maximum stable deformation, superplastic forming should be done at this strain rate. Too great a variance from the optimum strain rate may result in a loss of superplastic properties.
Turning first to Figure 1, there is shown a first embodiment of the present invention. Preform 10 is preferably a metal blank in the form of a sheet having upper and lower opposed principal surfaces 12 and 14. Any metal that exhibits suitable superplastic properties can be used, but the present invention is particularly concerned with titanium or an alloy thereof, such as Ti-SAI4V. Aåditionally, it is preferable that the metal used for preform 10 be capable of plastic deformation under compressive pressure at obtainable economical temperature (titanium and the aforementioned alloy meet this qualification).
The initial thickness of preform 10 is determined bythe dimensions of the part to be formed.
Preform 10 is supported on shaping member 20. Shaping member 20 defines a chamber 22 and female die surface 24. Die surface 24 has a projecting portion 25 thereon. A hold-down ring 30 acts as a clamping means for the preform# 10.
A single continuous edge of preform 10 is effectively constrained between hold-down ring 30 and shaping member 20. A punch or shaping member 40 has a male die surface 42 which preferably is in mating relationship with die surface 24.
The dimensions of shaping members 20 and 40 are such that they are complementary to the shape desired to be formed, i.e., the unconstrained portion of preform 10 would conform to die surface 24 on surface 14 and to die surface 42 of punch 40 on surface 12. A primary consideration in selection of a suitable shaping member alloy is reactivity with the metal to be formed at forming temperatures. When the metal to be formed is titanium or an alloy thereof, iron base alloys with low nickel content and modest carbon content (as 0.2-0.5% carbon) have been successful. Since forming loads are relatively low, creep strength and mechanical properties are fairly unimportant
Figure 1 B illustrates the superplastic forming of preform 10. While in this embodiment superplastic forming occurs before forging, the sequencing is not critical.Either operation could be conducted initially followed by the other, or in some cases both operations could be conducted concurrently. When the steps of superplastic forming and forging are conducted concurrently, it is to different portions of this preform.
For superplastic forming, preform 10 must be
brought to within a temperature range at which it
exhibits superplastic characteristics, if it is not
already in that range. Various heating methods
can be used for heating preform 10 to the desired temperaturs range (where the metal would be in a plastic state having a suitable strain rate sensitivity). Thus, the forming apparatus can be placed between heating platens (not shown) such as disclosed in U.S. Patent No. 3,934,441 to
Hamilton, et al. This method is advantageous as it also heats shaping members .20 and 40 so that the areas of preform 10 contacted by shaping members 20 and 40 during forming (and forging) do not have their temperatures substantially affected.
Forming of preform 10 into the basic configuration can be accomplished by pressure from punch 40 or by a pressure differential around preform 10. Such a pressure differential method is disclosed in U.S. Patent No. 3,934,441 to
Hamilton, et al. It has been found that differential pressures that can be used for superplastic forming normally vary from 15 psi to 300 psi.
When a differentiai pressure is used, the preform acts as a diaphragm. As shown in Figure 1 B, this embodiment uses male die member 40 which is forced against preform 10 at a rate such as to cause superplastic forming. This rate should be such that the superplastic strain rate is not exceeded. Forming times depend upon diaphragm thickness, material superplastic properties, and the pressure (or rate of die 40 movement) used and may vary from 10 minutes to 16 hours. As can be seen in Figure 1 B, the unconstrained portion of preform 10 is superplastically formed against die surface 42 and preferably in sufficient amount to also deform against die surface 24. The superplastically formed preform 10 has a uniform thickness.However, a part of preform 10 does not contact the lower essentially recessed portion 27 of die surface 24 due to the uniform deformation of superplastic forming, i.e. the remaining portion of die# surface 24 is in contact with preform 10 so that punch 40 cannot be moved further downward without a substantial increase of pressure which would exceed the strain rate necessary for superplastic forming.
The completion of the process is shown in
Figure 1 C. The pressure applied by punch 40 (a differential pressure could also be used to forgepreform 10 but would not be a desired approach because of the extremely large gas pressures required with consequent sealing problems and the fact that gas pressure would be uniform over the surface of preform 10) is increased and sustained allowing creep to occur as in conventional "hot die" or isothermal forging such that preform 10 is forged between shaping members 20 and 40 from the configuration of
Figure 1 B to that of Figure 1 C (this forces flow of preform 10 against recessed portion 27). This forging is similar to that disclosed in U.S. Patent
No. 3,519,523 to Moore, et al where the preform is in a condition of low strength and high ductility
when forged.The forging is in hot dies at a forging
temperature within about 3500F of but not
exceeding on a sustained basis the normal
recrystallization temperature of the alloy, while
inhibiting substantial grain growth. Optimally, the
temperature range used for superplastic forming
of preform 10 would also be suitable for forging of
the preform 10. Typically, with Ti-6AI-4V, a
temperature of about 17000F can be used for
both the forging and superplastic forming steps.
The forging pressure that can be used can vary
and it depends upon many parameters such as the
particular metal or alloy used for preform 10, how formable it is at the forming temperature,
thickness of preform 10, amount of deformation
required for preform 10, and desired time of
processing, etc. Applicants have found that for
titanium and its alloys, and particularly the Ti-6AI
4V alloy the range of pressure than can be used is 1500-10,000 psi, with the preferred range being
about 2000~6000 psi, with the lower end of the
preferred range producing better results.
Depending upon the configuration, this pressure is
normally applied for 4-5 hours, but could be as
low as one-half hour when simple shapes are to be fabricated.
While the part to be formed as shown in Figure
1 C could not be accomplished by forging alone due to the large stretching required (see Figure
1 B), a high degree of forging is possible. This is due to the typically low flow stresses of a superplastic material. Thus the forging loads can be sustained for a prolonged time period to capitalize on the available low flow stresses of the superplastic preform. The heated dies prevent undesirable cooling of the part to be forged. It should be noted that the flow stresses are lower at lower strain rates. This permits reduced pressures to cause the forging (albeit at lower strain rates) and the forging of relatively thin members.
As can be seen in Figure 1 C, the part formed has a variable thickness, having its greatest thickness along the continuous edge constrained between ring 30 and shaping member 20 (where such portion is not to be trimmed from the completed part), its thinnest section where it overlies protruding portion 25 of die surface 24, and a portion haivng an intermediate thickness which overlies the remaining portion of die surface 24 of shaping member 20.
When the preform 10 is a reactive metal such as titanium and its alloys, whose surface would be contaminated at the elevated temperatures required for superplastic forming, the present method would be accomplished in an inert atmosphere. A contamination prevention system which sould be used to provide such an inert atmosphere is disclosed in U.S. Patent No.
3,934;441 to Hamilton, et al.
After the forming operation, the part 10 is removed, trimmed, cleaned, and further processed as required for its intended application. Tooling can be heated and cooled for each part produced or it can be maintained at the processing temperature range and each part produced,
ejected, and removed and a subsequent sheet
inserted and formed immediately thereafter.
Additional embodiments of the present
invention are illustrated in Figures 2, 3 and 4. The
previous discussion of the requirements for
superplastic forming and forging such as elevated
temperatures, suitable preform material, and
necessary pressure are also as should be
understood applicable to these embodiments.
A second embodiment of the present invention
is shown in Figure 2. In this embodiment, the workpiece 10 is not clamped at its periphery such as by hold-down ring 30 in Figure 1, but allowed to pull into the die cavity during the forming operation. Figure 2A illustrates the initial position of preform 10 relative to shaping members 20 and 50. Figure 1 B illustrates the preform 10 after its
superplastic forming is completed by male
die member 50. The completely formed part 10 is
shown in Figure 2C where the forging has been
accomplished by increased pressure applied by
shaping member 50 for the necessary time
duration.
Figure 3 illustrates another embodiment of the
.present invention. In this embodiment, the initial
position of preform 10 is shown in Figure 3A.
Preform 10 has a single continuous edge thereof
constrained between shaping members 60 and a
ring-like hold-down member 62. Gas lines 64 and
66 are provided in member 60. These can form
part of the contamination prevention system as
previously discussed. A piston-like punch 70 is
provided above preform 10 in the annular area
defined by the ring-like member 62. A cavity 72 is
defined by shaping member 60. Punch 70 has a
groove 74 on its contact surface 76.
Figure 3B illustrates the superplastic forming of
preform 10 from its initial position to an
intermediate position shown by the broken lines of
Figure 3B and to the final position shown by the
unbroken lines. Such superplastic forming is
accomplished by gas pressure through lines 64
and 66 which are connected to a source (not
shown) of inert gas. Such gas pressure would
also preferably be in the range of about 1 5-300 psi. As prefrom 10 deforms, inert gas is vented from chamber 72 through vent lines 76 and 78 in shaping member 60.
The preform 10 is formed to its final shape by a forging step illustrated in Figure 3C. As shown, punch 70 moves downward and applies a forging pressure along its contact surface 76 to preform 10. Such forging pressure acts to compress the contacted portions of preform 10 forcing material flow up into groove 74. The portion of preform 10 which flows into groove 74 is shaped to conform to groove 74 by virtue of the plastic state of preform 10 due to the elevated temperature. As the remaining portion of preform 10 which contacts surface 73 ahddbes not flow into groove 74 is compressed, its thickness is less than the portion of preform 10 which contacts the side walls 73 of chamber 72. The portion of preform 10 which protrudes into groove 74 is of an increased thickness which can vary depending upon the shape of groove 74.
Figure 4 illustrates another embodiment of the present invention. As shown in Figure 4A, preform 10 in its initial position is constrained between a lower shaping member SO and an upper ring-like retaining member 82. Gas lines 84 and 86 are provided in retaining member 82 to provide an inert atmosphere over preform 10. Shaping member 80 has a cavity 90 defined therein. Cavity 90 has an upper tapered portion 92 and a lower portion 94 of uniform width. Fluid lines 96 and 98 are provided at the bottom of portion 94 of cavity 90. These lines are connected to a source of vacuum (not shown). A piston-like punch or shaping member 100 having a contact surface made up of a tapered portion 102 which mates with tapered portion 92 of cavity 90 and a level portion 104 is located in the annular area 106 defined by retaining member 82.
As shown in Figure 4B, punch 100 is moved downward and applies a compressive forging pressure to preform 10 where it contacts the walls of portion 92 of cavity 90. The remaining portion 110 of preform 10 extends into portion 94 of cavity 90.
Portion 110 of preform 10 is then superplastically formed as shown in Figure 4C by application of vacuum (positive pressure could also be applied above portion 110 by application of gas through lines, not shown, which would run through punch 100) through lines 96 and 98 and deforms to conform to portion 94 of cavity 90.
The portion of preform 10 which is contacted by the tapered sides 102 of punch 100 is retained by pressure from punch 100 and consequently does not have its thickness varied by superplastic forming, i.e. portion 110 has its thickness reduced by its expansion to conform to portion 94 of cavity 90.
Thus, it is apparent that there has been provided in accordance with the invention, a method of making metallic structures which combines superplastic forming and forging that fully satisfies the objectives, aims, and advantages set forth above. While the invention has been described in conjunction with specific embodiments thereof, it is evident that many alternatives, modifications, and variations will be apparent to those skilled in the art in light of the foregoing description. Accordingly, it is intended to embrace all such alternatives, modifications, and variations that fall within the spirit and scope of the appended claims.
Claims (16)
1. A method of making metallic structures comprising the steps of:
providing a metal preform having superprastic# properties;
providing a shaping member substantially defining the desired final configuration of said preform;
bringing said preform to within a temperature
range suitable for superplastic forming of said
preform;
inducing tensile stress in said preform by
applying pressure to said preform sufficient to
cause at least a portion of said preform to expand
superplastically; and
forging at least a portion of said preform
against said shaping member.
2. The method of Claim 1 wherein at least a
portion of said preform deforms against said
shaping member when expanded superplastically.
3. The method of Claim 2 wherein said forging
is by application of a fluid pressure loading on said
preform.
4. A method of making metallic structures
comprising the steps of:
providing a metal preform having superplastic
characteristics;
providing at least two shaping members, said
shaping members substantially defining the
desired final configuration of said preform;
bringing said preform to within a temperature
range suitable for superplastic forming of said
preform;
inducing tensile stress in said preform by
applying pressure to said preform sufficient to
cause at least a portion of said preform to expand
superplastically; and
forging at least a portion of said preform
between said shaping members.
5. The method of Claim 4 wherein at least a
portion of said preform deforms against at least
one of said shaping members when expanded superplastically.
6. The method of Claim 5 wherein said shaping
members are brought to within said temperature range in the step of bringing said preform to within
a temperature range suitable for superplastic
forming.
7. The method of claim 5 wherein said
temperature range suitable for superplastic
forming is also suitable for the forging step.
8. The method of claim 5 also including the
step of bringing said preform to within a
temperature range suitable for forging.
9. The method of claim 5 also including the
step of bringing said preform and said shaping
members to within a temperature range suitable
for forging.
10. The method of claim 6 also including the
step of bringing said preform and said shaping
members to within a temperature range suitable
for forging.
11. The method of claim 5 wherein said
shaping members are mated dies and said preform
is in sheet form.
12. The method of claim 11 wherein said
preform has two opposed principal surfaces and
the pressure applied to said preform is a fluid
pressure loading across said principal surfaces.
13. The method of claim 1 or 4 wherein said
forging is by application of pressure, greater than in said inducing step, to said preform.
14. The method of claim 1 or 4 substantially as described with reference to any of the accompanying drawings.
15. A metallic structure shaped partially by superplastic forming and partially by forging.
16. A metallic structure made by the method of any of claims 1 to 14.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB7836128A GB2029304B (en) | 1978-09-08 | 1978-09-08 | Method of making a metallic structure |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB7836128A GB2029304B (en) | 1978-09-08 | 1978-09-08 | Method of making a metallic structure |
Publications (2)
Publication Number | Publication Date |
---|---|
GB2029304A true GB2029304A (en) | 1980-03-19 |
GB2029304B GB2029304B (en) | 1982-10-27 |
Family
ID=10499537
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB7836128A Expired GB2029304B (en) | 1978-09-08 | 1978-09-08 | Method of making a metallic structure |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2029304B (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1982003577A1 (en) * | 1981-04-10 | 1982-10-28 | Metals Ltd Superform | Dual motion press |
GB2195281A (en) * | 1986-09-18 | 1988-04-07 | Edward Smethurst | Making moulds |
EP0648555A1 (en) * | 1991-10-03 | 1995-04-19 | Rockwell International Corporation | Forming of intermetallic materials with conventional sheet metal equipment |
SG166042A1 (en) * | 2009-04-08 | 2010-11-29 | Inter License Co Ltd | Method for creating pattern on a metal surface by imprinting with the aid of heating |
-
1978
- 1978-09-08 GB GB7836128A patent/GB2029304B/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1982003577A1 (en) * | 1981-04-10 | 1982-10-28 | Metals Ltd Superform | Dual motion press |
GB2195281A (en) * | 1986-09-18 | 1988-04-07 | Edward Smethurst | Making moulds |
EP0648555A1 (en) * | 1991-10-03 | 1995-04-19 | Rockwell International Corporation | Forming of intermetallic materials with conventional sheet metal equipment |
SG166042A1 (en) * | 2009-04-08 | 2010-11-29 | Inter License Co Ltd | Method for creating pattern on a metal surface by imprinting with the aid of heating |
Also Published As
Publication number | Publication date |
---|---|
GB2029304B (en) | 1982-10-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4117970A (en) | Method for fabrication of honeycomb structures | |
US4141484A (en) | Method of making a metallic structure by combined flow forming and bonding | |
EP1007240B1 (en) | Superplastic forming process | |
US3025905A (en) | Method for precision forming | |
US5118026A (en) | Method for making titanium aluminide metallic sandwich structures | |
US3934441A (en) | Controlled environment superplastic forming of metals | |
US4951491A (en) | Apparatus and method for superplastic forming | |
US4603808A (en) | Super plastic forming method with heat treated seals | |
CA1055680A (en) | Method for making metallic sandwich structures | |
US4113522A (en) | Method of making a metallic structure by combined superplastic forming and forging | |
US4811890A (en) | Method of eliminating core distortion in diffusion bonded and uperplastically formed structures | |
US6071360A (en) | Controlled strain rate forming of thick titanium plate | |
US4559797A (en) | Method for forming structural parts | |
EP0172732B1 (en) | Forming of metal articles | |
US4023389A (en) | Method of flow forming | |
US4534196A (en) | Method for manufacturing a mold | |
US6581428B1 (en) | Method and apparatus for superplastic forming | |
GB2029304A (en) | Method of making a metallic structure | |
US4460657A (en) | Thinning control in superplastic metal forming | |
US4381657A (en) | Method of removing formed parts from a die | |
US4516419A (en) | Methods of enhancing superplastic formability of aluminum alloys by alleviating cavitation | |
CA1083859A (en) | Method of making a metallic structure by combined superplastic forming and forging | |
US5215600A (en) | Thermomechanical treatment of Ti 6-2-2-2-2 | |
US4137105A (en) | Method of forming tooling for superplastic metal sheet | |
JPH02133133A (en) | Hot precision die forging method |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PE20 | Patent expired after termination of 20 years |
Effective date: 19980907 |