WO2009039282A1 - Diffusion bonding - Google Patents
Diffusion bonding Download PDFInfo
- Publication number
- WO2009039282A1 WO2009039282A1 PCT/US2008/076865 US2008076865W WO2009039282A1 WO 2009039282 A1 WO2009039282 A1 WO 2009039282A1 US 2008076865 W US2008076865 W US 2008076865W WO 2009039282 A1 WO2009039282 A1 WO 2009039282A1
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- WO
- WIPO (PCT)
- Prior art keywords
- component
- diffusion bonding
- die
- components
- pressure
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/023—Thermo-compression bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
Definitions
- the present disclosure concerns improvements in or relating to diffusion bonding.
- Isostatic pressing is the application of high pressure gas (e.g. argon) at high temperature within a pressure vessel to the components to be joined. Gas pressure is applied isostatically so that there are minimal or no changes to the geometry of the components being joined.
- This diffusion bonding process requires the efficient sealing of the components, and conventionally, this has been accomplished outside the pressure vessel in a preliminary step. However, the seal between the components after this preliminary step is fragile, and great care has to be taken in moving the joined components to the apparatus where the diffusion bonding process is to be carried out.
- the present disclosure provides a process of diffusion bonding which overcomes certain difficulties with the prior art methods while providing better and more advantageous overall results.
- a method of bonding a part for use in jet engine fan blade protection is provided.
- the part for use in a jet engine fan blade includes a first component and a second component diffusion bonded to the first component.
- the first component is configured as a pressure side component and includes a first primary bond land surface.
- the second component is configured as a suction side component and includes a second mating bond land surface.
- a mandrel is provided.
- the mandrel includes a first surface having a contour that mates with at least a portion of the first component and a second surface having a contour that mates with at least a portion of the second component.
- the first and second components are positioned on the mandrel so that the first bond land surface and the second bond land surface are in mating abutment.
- the first component is releasably connected to the second component.
- the connected first and second components together with the mandrel are positioned in a die assembly.
- the die assembly including a first die, a second die and a plurality of fastening members for releasably securing the first die to the second die.
- the first and second dies are formed of a first material having a first coefficient of thermal expansion.
- the fastening members are formed of a second material having a second smaller coefficient of thermal expansion.
- the die assembly is placed in a vacuum furnace or other type of heating arrangement for a diffusion bonding cycle.
- the heating arrangement is evacuated.
- the heating arrangement is first purged with argon gas to displace any atmospheric contamination and then the heating arrangement is evacuated to a predetermined vacuum level.
- the temperature of the heating arrangement is increased to a predetermined temperature.
- Uniform pressure is applied across an interface between the first and second bond land surfaces of the first and second components.
- the vacuum level, temperature and pressure is maintained within the furnace for a predetermined period of time.
- the die assembly including the diffusion bonded first and second components is removed from the furnace.
- a diffusion bonding die assembly for diffusion bonding a first component having a nonplanar first bond land surface to a second component having a nonplanar second bond land surface.
- the diffusion bonding die assembly comprises a mandrel, an upper die and a lower die.
- the mandrel is configured to releasably hold the first and second components.
- the first bond land surface and the second bond land surface are in mating abutment when loaded on the mandrel.
- the upper die includes an upper surface and a lower surface.
- the lower surface includes a first portion configured to engage the mandrel and a second portion configured to mate with one of the first and second components.
- the lower die includes an upper surface and a lower surface.
- the upper surface includes a first portion configured to engage the mandrel and a second portion configured to mate with one of the first and second components.
- a flexible pressure container is at least partially disposed between one of the upper and lower dies and one of the first and second bond land surfaces of the first and second components.
- a plurality of fastening members secures the upper die to the lower die and holds the diffusion bonding die assembly together during a diffusion bonding cycle.
- the plurality of fasteners is configured to limit expansion of the upper and lower dies during the diffusion bonding cycle.
- a method of diffusion bonding comprises providing a first component and a second component.
- the first component includes a first bond land surface having a wave-like conformation.
- the second component includes a second bond land surface having a wave-like conformation.
- the mating first and second bond land surfaces to be diffusion bonded are prepared to a predetermined condition such that diffusion bonding across an interface between the surfaces is possible.
- the first component to the second component are connected so that the first and second bond land surfaces are in mating abutment.
- a diffusion bonding die assembly configured to releasably secure the connected components therein is provided.
- the die assembly includes a first die, a second die and a plurality of fastening members for releasably securing the first die to the second die.
- the die assembly is coated with a release agent along with specifically identified critical areas of the first and second components.
- the first and second components with the first and second bond land surfaces in mating abutment are placed in the die assembly.
- the die assembly is placed in a vacuum furnace or other type of heating arrangement for a diffusion bonding cycle.
- the heating arrangement is evacuated and the temperature of the heating arrangement is increased to a first temperature.
- the first temperature is maintained for a predetermined period of time.
- the temperature of the heating arrangement is increased to a second temperature, which is maintained for a predetermined period of time.
- a first pressure is applied at the second temperature across the interface of the first and second components for a predetermined period of time.
- the applied pressure is increased to a second pressure.
- the second pressure is applied at the second temperature across the interface of the first and second components for a predetermined period of time.
- the applied pressure is decreased to a third pressure.
- the third pressure is applied at the second temperature across the interface of the first and second components for a predetermined period of time.
- the temperature of the heating arrangement is decreased to a third temperature.
- the die assembly including the diffusion bonded first and second components is removed from the heating arrangement.
- the first component includes a first, bond land surface, a second surface offset from the first surface via a connecting, arcuate wall, and a third surface opposite the first and second surfaces.
- the second component includes a first surface and a second surface. A section of the second surface forms a second, bond land surface which is bonded to the first, bond land surface of the first component.
- FIGURE 1 is a side elevational view of a non-limiting part including a first component and a second component bonded to the first component in accordance to the diffusion bonding process of the present disclosure.
- FIGURE 2 is a side elevational view of the first component of the part of FIGURE !
- FIGURE 3 is a top perspective view of the first component of FIGURE 2.
- FIGURE 4 is a cross-sectional view of the first component of FIGURE 2 taken generally along lines 4-4 of FIGURE 2.
- FIGURE 5 is a partially enlarged view of FIGURE 4.
- FIGURE 6 is a side elevational view of the second component of the part of FIGURE 1.
- FIGURE 7 is a cross-sectional view of the second component of FIGURE 6 taken generally along lines 7-7 of FIGURE 6.
- FIGURE 8 is a side elevational view of the first component of the part of FIGURE 1 illustrating a non-limiting bond land surface.
- FIGURE 9 is a side elevational view of the second component of the part of FIGURE 1 illustrating a non-limiting bond land surface.
- FIGURE 10 is a front perspective view of a mandrel having the first and second components positioned thereon.
- FIGURE 11 is a partially enlarged view of FIGURE 10.
- FIGURE 12 is a side cross-sectional view of FIGURE 10.
- FIGURE 13 is an exploded front perspective view of a non-limiting diffusion bonding die assembly for forming the part of FIGURE 1 including a first die, a second die, a pressure bag, and the mandrel and first and second components of FIGURE 10.
- FIGURE 14 is a front perspective view of the diffusion bonding die assembly of FIGURE 13 is an assembled condition.
- FIGURE 15 is a cross-sectionai view of the diffusion bonding die assembly of
- FIGURE 13 taken generally along lines 15-15 of FIGURE 13.
- FIGURE 16 is a partially enlarged view of FIGURE 15.
- FIGURE 17 is a cross-sectional view of the diffusion bonding die assembly of
- FIGURE 13 taken generally along lines 17-17 of FIGURE 13.
- FIGURE 18 is a partially enlarged view of FIGURE 17.
- FIGURE 19 is a front perspective view of the first and second dies and the mandrel in a post diffusion bonding inspection condition.
- FIGURE 20 is a side perspective view of the part of FIGURE 1.
- FIGURE 21 is a cross-sectional view of the part of FIGURE 20.
- FIGURE 22 is an enlarged partial view of FIGURE 21.
- FIGURE 23 is a chart summary of a non-limiting diffusion bonding process according to the present disclosure.
- component materials disclosed herein are by way of example only.
- the component materials can further include not only elementary metals but metal alloys per se and alloys of metals with ceramic material.
- the materials may be in the form of sintered powder, a casting, sheet, plate or a forging.
- FIGURE 1 illustrates a non-limiting example of a part 100 to be manufactured via a diffusion bonding process according to the present disclosure.
- the example should not be construed as limiting as the example is useful in understanding and practicing the diffusion bonding process described herein.
- a general overview of the diffusion bonding process is first provided.
- the part 100 is manufactured in two separate components, to wit, a first, pressure side component 102 that is bonded to a second, suction side component 104 at a bond joint 110.
- part 100 can be formed of more than two components; however, this is not required.
- the first component 102 can be manufactured from AMS 4911 plate stock (approximately .375 in. thick) that is rough machined, hot formed and then machine finished in preparation for diffusion bonding.
- the second component 104 can be manufactured from AMS 4911 sheet stock (approximately .040 in. thick) that is machine finished as a flat pattern and then hot formed.
- AMS 4911 plate stock approximately .375 in. thick
- AMS 4911 sheet stock approximately .040 in. thick
- one or both of the components can be formed of different materials and/or have different thicknesses.
- AMS 4911 is a titanium alloy which is heat treatable and combines excellent strength and corrosion resistance. AMS 4911 is widely used in the aircraft industry in a variety of turbine (i.e., turbine discs) and "hot" structural applications. It is generally employed in applications up to 750 0 F (400 0 C). [0038] In preparation for the diffusion bonding process, the two components 102, 104 are typically cleaned, connected together and then loaded into a diffusion bonding die assembly 106 according to the present disclosure (FIGURES 13 and 14). The diffusion bonding die assembly 106 is then placed in a heating arrangement such as a vacuum furnace and a diffusion bonding cycle is run at preset parameters.
- a heating arrangement such as a vacuum furnace
- the part 100 can also, or alternatively, be ultrasonically inspected; however, this is not required. After ultrasonic inspection, the part is typically finished machined and manually dressed to meet predetermined visual requirements. Again, the part 100 is by way of example only. It should be appreciated that parts having alternative materials, shapes and/or sizes can be manufactured via the diffusion bonding process described herein.
- the first component 102 comprises a first elongated member 112 having a wave-like or ribbon-like conformation. Particularly, as shown in FIGURE 3, as the elongated member twists from a first end portion 114 to a second end portion 116, the elongated member curving along two opposed diameters.
- the elongated member includes a first or primary bond land surface 120, a second surface 122 offset from the bond land surface via a wall 126, and a third surface 128 opposite the first and second surfaces.
- a plurality of spaced apart tabs 130 can extend from the first surface.
- the first and third surfaces together 120, 128 define a first section 134 of the elongated member and the second and third surfaces together 122, 128 define a second section 136 of the elongated member.
- the first section 134 increases in thickness as it transitions into the second section 136; however, this is not required.
- the second section decreases in thickness as it extends at an acute angle from the first section.
- the first component 102 has a varying thickness.
- the wall 126 connects the first surface 120 and the second surface 122.
- the wall includes an arcuate surface 140 having a first end 142 that connects to the second surface and a second end 144 that connects to a ramp 150.
- the ramp has a generally triangular shape, an end portion of the ramp being slightly offset from the first surface.
- the second component 104 comprises a second elongated member 160 having a wave-like or ribbon-like conformation, which twists from a first end portion 166 to a second end portion 168.
- the second elongated member includes a first surface 162 and a second surface 164.
- a section 170 of the second surface at least partially defines a second mating bond land surface that is bonded to the first, bond land surface 120.
- a plurality of spaced apart tabs 172 can extend from the bonding surface section 170.
- the second component 104 includes a first section 174 having a constant thickness and a second, transitioning section having a decreasing thickness; however, this is not required.
- the first and second components 102, 104 are cleaned and the mating surfaces of the first and second components are prepared to a predetermined smoothness (e.g., a smoothness of about 1 micron or better).
- the components 102, 104 are then connected and loaded into the diffusion bonding die assembly 106.
- the first and second components include at least one hole 180, 182 which allows the first and second components to be hung to avoid contact with foreign surfaces. As can be appreciated, this inclusion of one or more holes in the components is not required.
- a mandrel 200 is provided to ensure the proper connecting of the first component 102 to the second component 104.
- the mandrel includes a base 202 and an arm 204 extending from the base.
- the arm is generally triangular in shape and includes a first surface 205, a second surface 206 and an arcuate end portion 208.
- the arm 204 can have other shapes.
- the first and second surfaces have contours which mate with the ribbon-like contours of the respective first and second components 102, 104.
- the end portion 208 has a contour which mates with the arcuate surface 140 of the wall 126. This allows the first component 102 to be releasably positioned on the mandrel.
- At least one pin 210 extends outwardly from a lower portion of the second surface 206 of the arm 204.
- the at least one pin allows the second component to be releasably placed on the mandrel.
- two pins are provided; however, a greater or lesser number of pins can be used.
- the pins are located a predetermined distance from the end portion 208 so that once the second component 104 is positioned on the pins 210, the tabs 172 can be aligned with the tabs 130 (see FIGURE 11 ). Once aligned, the tabs 130, 172 are held together by suitable fastening means, such as, but not limited to, small C-clamps (not shown).
- first and second components 102, 104 are then placed in an argon chamber (not shown) wherein the tabs 130, 172 can be tack welded together.
- first and second components can be connected via additional or alternative means. In that instance, the tabs 130, 172 are not required.
- the mandrel and connected first and second components are then quickly placed in the diffusion bonding die assembly 106 to ensure that the bonding surfaces remain clean.
- the diffusion bonding die assembly 106 comprises a first die 220 and a second die 222.
- the second die includes a surface 230 having a configuration which can mate with one of the first and second components 102, 104.
- the first die includes a surface 232 which can conform to the other of the first and second components.
- the surfaces 230, 232 can have a wave-like or ribbon-like conformation; however, surfaces 230, 232 can have other or additional shapes.
- surface 230 protrudes at least partially from the second die and engages the second component 104.
- Surface 232 protrudes at least partially from the first die and engages the first component 102.
- the first die 220 includes a plurality of spaced apart cutouts 250 located on opposed sides 252, 254 of the die.
- a wall 256 of the first die includes a plurality of spaced apart shelves 258 which extend outwardly from the wall 256.
- the cutouts 250 extend through the shelves 258.
- the second die 222 includes a plurality of spaced apart cutouts 260 located on opposed sides 262, 264 of the die.
- a wall 270 of the second die 222 includes a plurality of spaced apart shelves 272 which extend outwardly from the wall 270.
- the cutouts 260 extend through the shelves 272. In an assembled position (FIGURE 14), the wall 256 is parallel to the wall 270; however, this is not required.
- the first and second dies 220, 222 can be formed of a HH2 casting, which is a 309 stainless steel that has a high carbon content; however, other materials can be used.
- the mandrel 200 in an assembled position, is securely positioned between the first and second dies 220, 222.
- the mandrel 200 includes first and second opposed grooves 274 and 276, respectively. Each groove extends the length of the mandrel base 202; although, this is not required.
- the first and second grooves 274, 276 are configured to receive first and second projections 280, 282 located on the respective first and second dies 220, 222. Spacing is provided between portions of the base 202 and the first and second dies.
- the mandrel 200 further includes first and second recesses 288, 290, respectively.
- the recesses are located in an offset region 292 of the mandrel base and are generally normal to the first and second grooves 274, 276.
- the first and second recesses 288, 290 are configured to receive first and second tabs 294, 296 located on the respective first and second dies 220, 222.
- Each tab extends inwardly from a respective offset region 300, 302 of each die 220, 222.
- the surface 232 of the first die 220 includes an offset portion 304. At least a portion of the pressure bag 340 is disposed in the offset portion for bond transition.
- each pin can be generally dumbbell-shaped; although, this is not required.
- the pin includes and a shaft 322 and caps 324, 326 located on ends of the shaft.
- the shaft is cylindrically shaped and the caps are rectangularly shaped; although, this is not required.
- sixteen pins are provided, eight for each side of each first and second die 220, 222.
- each pin can be stamped with its own unique number and correlates with a cutout location stamped on the die assembly 106. Additionally, the pins can be marked with a letter of the alphabet that associates them with a specific die. Each pin has a predetermined length, the length of the pin being dependent on it location on the die.
- the pins can be formed from a Haynes 230 alloy; however, other materials can be used.
- Haynes 230 alloy is a nickel-chromium-tungsten- molybdenum alloy that combines excellent high temperature strength, outstanding resistance to oxidizing environments up to 2100 0 F (1149°C) for prolonged exposures, premier resistance to nitriding environments, and excellent long-term thermal stability. It is readily fabricated and formed, and is castable. Other attractive features include lower thermal expansion characteristics than most high-temperature alloys, and a pronounced resistance to grain coarsening with prolonged exposure to high-temperatures.
- a pressure container or bag 340 is positioned between one of the first and second dies 220, 222 and one of the first and second components 102, 104 positioned on the mandrel 200 for applying a uniform pressure between the one of the first and second dies and one of the first and second components during the diffusion bonding process.
- the pressure bag is made of a flexible sheet of material, such as, but not limited to, a sheet of 309 stainless steel, so that the pressure bag can conform to the shape of one of the first and second components located on the mandrel 200. This is desirable because the twisting, ribbon- like shape of each part component 102, 104 makes it difficult for the first and second components to be simply pressed in a conventional die.
- the pressure bag is disposed between the surface 232 of the first die 220 and the second component 104 located on the mandrel 200.
- One of the first die and the mandrel can include means for proper positioning of the pressure bag thereon.
- the first die can include locating pins (not shown) which engage corresponding holes (not shown) located on the pressure bag.
- the pressure bag 340 defines a chamber (not shown) for receiving a gas from a remote source via a gas line 342 connected to the pressure bag.
- compressed argon gas is released from a storage tank at approximately 200 PSI to approximately 250 PSI; although, alternative gases and pressures are contemplated.
- the argon gas flows through a hose and into the pressure bag line 342.
- the line can be regulated by a digital pressure gage (not shown) that can be monitored by the operator.
- the argon gas dew point can be periodically monitored (e.g., monthly, etc.) to determine that moisture content generally does not to exceed about -76°F.
- the HH2 material compared to the Haynes 230 alloy provides a small but significant difference in the coefficients of thermal expansion between the two materials. It should be appreciated by one skilled in the art that alternative complementary metal or metal alloys are contemplated so long as differing coefficients of thermal expansion exists between the alternative materials.
- coefficients of thermal expansion of a material are complicated and can vary dramatically as the actual temperature varies, but defines the relationship of the change in size of a material as the temperature of the material changes.
- a coefficient of thermal expansion is the fractional increase in length per unit rise in temperature. It can be defined at a precise temperature or over a temperature range. Thermal expansion is an important considerations in design, and are often overlooked.
- the coefficient of thermal expansion for the HH2 material is slightly higher than that of Haynes 230 alloy.
- the first and second dies 220, 222 will expand slightly more than the pins 320 upon exposure to a temperature exceeding the annealing temperatures of both materials.
- the first and second dies 220, 222 will start to expand. This expansion will be limited by the pins 320, which are expanding at a slower rate. Additionally, because the pins 320 can have differing lengths, the length of the pins can further limit the expansion of the first and second dies.
- the difference in expansion between the first and second dies and pins transfers pressure to the pressure bag 340, which, in turn, provides a uniform load to the bond land surfaces 120, 170 of the first and second components 102, 104. Further, the increase of temperature in the furnace will increase the pressure within the pressure bag 340, which, in turn, increases the pressure between the first and second dies 220, 222 and the first and second components 102, 104.
- Non-expandable thermocouples 344 can be located in at least one of the first and second dies 220, 222 for monitoring temperature.
- the thermocouples are generally used for up to thirty bond cycles and can be calibrated to special limits. Usage of the thermocouples can be controlled by system accuracy tests performed at about 1500 0 F to a maximum deviation of ⁇ 4°F ( ⁇ 0.4%) to maximum ⁇ 5°F or up to the thirty bond cycles, whichever occurs first.
- the part 100 after the diffusion bonding process and the connected tabs 130 and 172 are carefully removed from the part, includes a bond area 370.
- the bond area can be ultrasonically inspected to ensure proper connection between the bond land surface 120 of first component 102 and the section 170 of the second surface 164 of second component 104.
- the external surfaces of the part can then be cleaned and finished.
- the first component 102 can be manufactured from AMS 4911 plate stock (approximately .375 in. thick) that is rough machined, hot formed and then machine finished in preparation for diffusion bonding.
- the second component 104 can be manufactured from AMS 4911 sheet stock (e.g., .040 in. thick) that is machine finished as a flat pattern and then hot formed.
- the two components 102, 104 are cleaned, connected together and loaded into the diffusion bonding die assembly 106.
- the halves can be placed on cleaning racks made of 316 stainless steel. Up to four separate processing tanks can be utilized for the cleaning, namely, an alkaline cleaner tank, a chemical clean etch tank, a city rinse tank and/or a deionize rinse tank. The parameters of each of the tanks are provided below.
- the maximum time between cleaning and diffusion bonding is generally eight (8) hours or less.
- Solution Components Solution Components at Solution Components - Solution Components - at start up: start up: 100% City Water 100% Deionized water
- Acid tanks - shall be controlled by etch rate. Process may continue if etch rate is within limits and HF is below minimum limit
- the first and second dies 220, 222 are inspected to ensure die flatness and parallelism.
- the length of each pin 320 is typically measured for accuracy.
- the contours of each die 220, 222 and the mandrel 200 can be inspected after every 10 th bond cycle; however, inspections can occur after more or less numbers of bond cycles.
- the second die can be divided into multiple sections (e.g. 3, 4, 5, 6 sections, etc.) and compared to certain die parameters. Data regarding the die can be collected and stored electronically to be monitored. This data collection can serve as a trouble shooting tool relative to part quality.
- the pressure bag 340 can be pressure tested prior to every bond cycle to confirm that the pressure bag will hold pressure (e.g., 50 psi with argon gas) and that there are no leaks.
- the diffusion bonding die assembly 106 and mandrel can be inspected after one or more cycles.
- the first and second dies 220, 222 and the mandrel 200 are generally assembled without the pressure bag 340 to verify that a gap 306 surrounding the first and second dies and mandrel does not exceed a maximum gap of approximately 0.010 inches.
- furnace burn outs can be performed weekly at about 2000 0 F for one hour.
- Furnace leak rates meeting less than or equal to about 3 microns or less per hour are performed weekly.
- Furnace temperature uniformity surveys to about ⁇ 15°F are performed quarterly.
- System accuracy tests are performed monthly to about 0.5% to maximum about +5°F (this includes control thermocouples and load thermocouples).
- Instrumentation calibrations are performed quarterly to about ⁇ 2°F readable within about 1 0 F.
- the mandrel 200, first and second dies 220, 222 and the pressure bag 340 can be coated with a release agent, such as a boron nitride spray. Specifically identified critical areas of the first and second components are also coated with the release agent.
- the release agent is typically used when diffusion bonding titanium components.
- the part 100 is loaded onto the mandrel 200 and the mandrel is placed on the second die 222 as described above making sure that the connected tabs 130, 172 of the part 100 are seated properly into the second die.
- the pressure bag 340 is placed at least partially over the part and secured on the first die.
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Abstract
Description
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Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2699952A CA2699952C (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
JP2010525974A JP5502737B2 (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
CN200880107682.9A CN101827682B (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
EP08831404.2A EP2274131A4 (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
AU2008302241A AU2008302241B2 (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
US12/716,466 US8256661B2 (en) | 2008-09-18 | 2010-03-03 | Diffusion bonding |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US99436207P | 2007-09-19 | 2007-09-19 | |
US60/994,362 | 2007-09-19 | ||
US2054808P | 2008-01-11 | 2008-01-11 | |
US61/020,548 | 2008-01-11 |
Publications (1)
Publication Number | Publication Date |
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WO2009039282A1 true WO2009039282A1 (en) | 2009-03-26 |
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ID=40468337
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/US2008/076865 WO2009039282A1 (en) | 2007-09-19 | 2008-09-18 | Diffusion bonding |
Country Status (7)
Country | Link |
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EP (1) | EP2274131A4 (en) |
JP (1) | JP5502737B2 (en) |
CN (1) | CN101827682B (en) |
AU (1) | AU2008302241B2 (en) |
CA (1) | CA2699952C (en) |
RU (1) | RU2455138C2 (en) |
WO (1) | WO2009039282A1 (en) |
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WO2012049401A1 (en) | 2010-10-05 | 2012-04-19 | Snecma | Method for manufacturing a metal part |
WO2012101356A1 (en) * | 2011-01-24 | 2012-08-02 | Snecma | Method for producing a metal reinforcement |
FR2972128A1 (en) * | 2011-03-01 | 2012-09-07 | Snecma | Method for manufacturing e.g. metal reinforcement of leading edge of composite fan blade in airplane's turbojet, involves performing hot isostatic pressing of metal structures for causing agglomeration of structures to obtain reinforcement |
FR2976204A1 (en) * | 2011-06-10 | 2012-12-14 | Snecma | Method for making metal insert for protecting leading edge or trailing edge of turbomachine blade, involves constructing outer profile of insert by final machining that is performed before separation of core of insert |
FR3114762A1 (en) * | 2020-10-06 | 2022-04-08 | Safran Aircraft Engines | Method of manufacturing a turbomachine compressor blade by compacting |
RU2787287C1 (en) * | 2022-06-23 | 2023-01-09 | Научно-производственная ассоциация "Технопарк Авиационных Технологий" | Method for diffusion welding of parts made of hard-to-weld alloys |
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BR112013022019B1 (en) * | 2011-03-01 | 2019-05-21 | Snecma | PROCESS OF MAKING A METAL PART SUCH AS A TURBOMACHINE SHOULDER BOOSTER |
JP2015227152A (en) * | 2014-05-09 | 2015-12-17 | 株式会社シマノ | Component for bicycle, shaft member for bicycle, rear sprocket assembly for bicycle, and lever member for bicycle |
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- 2008-09-18 RU RU2010115350/02A patent/RU2455138C2/en active IP Right Revival
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- 2008-09-18 JP JP2010525974A patent/JP5502737B2/en not_active Expired - Fee Related
- 2008-09-18 AU AU2008302241A patent/AU2008302241B2/en active Active
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RU2607389C2 (en) * | 2010-10-05 | 2017-01-10 | Снекма | Method of metal part producing |
WO2012049401A1 (en) | 2010-10-05 | 2012-04-19 | Snecma | Method for manufacturing a metal part |
CN103476544A (en) * | 2010-10-05 | 2013-12-25 | 斯奈克玛 | Method for manufacturing a metal part |
US9296072B2 (en) | 2010-10-05 | 2016-03-29 | Snecma | Method for manufacturing a metal part |
CN103476544B (en) * | 2010-10-05 | 2016-12-07 | 斯奈克玛 | The method making metal parts |
WO2012101356A1 (en) * | 2011-01-24 | 2012-08-02 | Snecma | Method for producing a metal reinforcement |
US9328614B2 (en) | 2011-01-24 | 2016-05-03 | Snecma | Method of making a metal reinforcing piece |
FR2972128A1 (en) * | 2011-03-01 | 2012-09-07 | Snecma | Method for manufacturing e.g. metal reinforcement of leading edge of composite fan blade in airplane's turbojet, involves performing hot isostatic pressing of metal structures for causing agglomeration of structures to obtain reinforcement |
FR2976204A1 (en) * | 2011-06-10 | 2012-12-14 | Snecma | Method for making metal insert for protecting leading edge or trailing edge of turbomachine blade, involves constructing outer profile of insert by final machining that is performed before separation of core of insert |
FR3114762A1 (en) * | 2020-10-06 | 2022-04-08 | Safran Aircraft Engines | Method of manufacturing a turbomachine compressor blade by compacting |
WO2022074314A1 (en) * | 2020-10-06 | 2022-04-14 | Safran Aircraft Engines | Method for manufacturing a turbomachine compressor blade by compacting |
US11904420B2 (en) | 2020-10-06 | 2024-02-20 | Safran Aircraft Engines | Method for manufacturing a turbomachine compressor blade by compacting |
RU2787287C1 (en) * | 2022-06-23 | 2023-01-09 | Научно-производственная ассоциация "Технопарк Авиационных Технологий" | Method for diffusion welding of parts made of hard-to-weld alloys |
Also Published As
Publication number | Publication date |
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CA2699952A1 (en) | 2009-03-26 |
CN101827682B (en) | 2014-07-02 |
JP2010538839A (en) | 2010-12-16 |
AU2008302241B2 (en) | 2012-08-16 |
EP2274131A4 (en) | 2017-02-22 |
CN101827682A (en) | 2010-09-08 |
RU2010115350A (en) | 2011-10-27 |
JP5502737B2 (en) | 2014-05-28 |
EP2274131A1 (en) | 2011-01-19 |
RU2455138C2 (en) | 2012-07-10 |
AU2008302241A1 (en) | 2009-03-26 |
CA2699952C (en) | 2013-07-09 |
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