EP3187283A1 - Dynamic bonding of powder metallurgy materials - Google Patents
Dynamic bonding of powder metallurgy materials Download PDFInfo
- Publication number
- EP3187283A1 EP3187283A1 EP16206377.0A EP16206377A EP3187283A1 EP 3187283 A1 EP3187283 A1 EP 3187283A1 EP 16206377 A EP16206377 A EP 16206377A EP 3187283 A1 EP3187283 A1 EP 3187283A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- container
- powder metallurgy
- solid powder
- preform
- exterior
- 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
- 239000000463 material Substances 0.000 title claims abstract description 91
- 238000004663 powder metallurgy Methods 0.000 title claims abstract description 72
- 239000007787 solid Substances 0.000 claims abstract description 62
- 238000005056 compaction Methods 0.000 claims abstract description 56
- 239000000843 powder Substances 0.000 claims abstract description 48
- 238000000034 method Methods 0.000 claims abstract description 47
- 239000002243 precursor Substances 0.000 claims abstract description 28
- 238000011049 filling Methods 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims abstract description 9
- 239000007789 gas Substances 0.000 claims description 13
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 9
- 238000005520 cutting process Methods 0.000 claims description 4
- 238000007689 inspection Methods 0.000 claims description 3
- 238000011068 loading method Methods 0.000 claims description 3
- 239000000956 alloy Substances 0.000 description 38
- 229910045601 alloy Inorganic materials 0.000 description 28
- 239000012254 powdered material Substances 0.000 description 9
- 238000001513 hot isostatic pressing Methods 0.000 description 5
- 238000003466 welding Methods 0.000 description 5
- 239000002245 particle Substances 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 238000005242 forging Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000010297 mechanical methods and process Methods 0.000 description 3
- 230000005226 mechanical processes and functions Effects 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000009705 shock consolidation Methods 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000007596 consolidation process Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- -1 such as Substances 0.000 description 2
- 235000012431 wafers Nutrition 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001362 Ta alloys Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/08—Compacting only by explosive forces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/087—Compacting only using high energy impulses, e.g. magnetic field impulses
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/1208—Containers or coating used therefor
- B22F3/1258—Container manufacturing
Definitions
- the present disclosure is directed to the improved process of dynamic bonding to create hybrid powder metallurgy parts.
- disks which support turbine blades rotate at high speeds in an elevated temperature environment.
- the separate portions of the disks are exposed to different operating conditions and temperatures.
- different combinations of mechanical properties are required at different locations.
- the high temperature rim portion has fatigue crack growth resistance and creep resistance, while the highly stressed hub portion has high burst strength at relatively moderate temperatures and fatigue crack growth resistance.
- the hub portion also has high resistance to low cycle fatigue for long component life.
- a possible solution is to use a dual alloy disk with different alloys used in the different portions of the disk, depending upon the properties desired.
- the disk has a joint region in which the different alloys are joined together to form an integral article.
- Present powder-metallurgical techniques require three to four steps to produce a finished product. For example, producing tungsten requires pressing and pre-sintering, followed by a consolidation sinter and/ or several hot-working steps. Dynamic bonding eliminates the need for large presses and expensive hot-pressing dies. In many instances, actual production time and costs may be reduced.
- a dynamic compaction process that comprises forming a preform.
- the steps of forming a preform comprise providing a first container, the first container having an interior and an exterior; filling the interior of the first container with a first powder material; sealing the first container; subjecting the exterior of the first container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the first container resulting in the first container collapsing upon the first powder material; forming a solid powder metallurgy billet encased by the first container.
- the process includes removing the first container from the solid powder metallurgy billet.
- the process includes attaching a second container to at least a portion of the preform, the second container having an interior and an exterior; filling the second container with a second powder material; sealing the second container; subjecting the exterior of the second container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the second container resulting in the second container collapsing upon the second powder material; forming a second solid powder metallurgy material from the second powder material encased by the second container; bonding the second solid powder metallurgy material to the portion of the preform; and removing the second container from the preform and the second solid powder metallurgy material.
- At least a portion of the preform comprises at least one of an end having a crescent shape and an interface of the preform.
- the crescent shaped end is configured to provide at least one of a larger surface area of contact for bonding, a shear component in loading, and facilitate sonic inspection of the bond interface both radially and axially.
- the first material comprises a nickel alloy and the second material comprises a different nickel alloy.
- the process further comprises removing unwanted gases by use of a vacuum on at least one of the first container and the second container subsequent to filling each respective container.
- the process further comprises forming a component from the combination of the preform bonded to the second solid powder metallurgy material.
- the component comprises a rotor having a hub and web portion formed from the first powder material and at least a portion of a rim portion formed from the second powder material.
- the process further comprises forming a component precursor from the combination of the preform bonded to the second solid powder metallurgy material and cutting at least one disk from the component precursor.
- an aerospace component comprising a first solid powder metallurgy material and a second powder material bonded together with dynamic compaction.
- the first solid powder metallurgy material comprises a first portion and a second portion and the second powder material comprises third portion.
- first portion and the second portion comprises the first solid powder metallurgy material and the third portion comprises the second solid powder metallurgy material.
- first solid powder metallurgy material and the second solid powder metallurgy material comprise different materials.
- the aerospace component is a rotor.
- the first portion comprises a hub of the rotor.
- the second portion comprises a web of the rotor; and the third portion comprises a rim of the rotor.
- a dynamic compaction process that comprises forming a component precursor.
- Forming the component precursor comprises forming a first container, the first container having an interior and an exterior; filling the interior of the first container with a first powder material; sealing the first container; subjecting the exterior of the first container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the first container resulting in the first container collapsing upon the first powder material; forming a solid powder metallurgy billet encased by the first container; and removing the first container from the solid powder metallurgy billet; forming a second solid powder metallurgy billet from a second powder material; inserting the first solid powder metallurgy billet and the second solid powder metallurgy billet into a second container, the second container having an interior and an exterior; sealing the second container; subjecting the exterior of the second container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure
- the first material comprises a nickel alloy and the second material comprised a different nickel alloy.
- the process further comprises forming a component precursor from the combination of the first solid powder metallurgy billet and the second solid powder metallurgy billet.
- the process further comprises cutting at least one disk from the component precursor.
- At least one controlled gap is formed between the first solid powder metallurgy billet and the second solid powder metallurgy billet.
- the second container includes at least one of a crush zone and a tab.
- FIG. 1 there is illustrated a turbine engine component precursor 10, such as an annular rotor disk having a centerline 12. It is contemplated that other components can be formed with the process, such as shafts, blades, airseals and the like.
- the exemplary turbine engine component 10 when fully manufactured (as shown in dashed lines), has a hub portion 14 and a rim portion 16 connected by a web portion 18. The component 10 is partially built-up from a preform 20.
- the turbine engine component 10 may be formed from a titanium-based alloy or nickel based alloy or a composite of alloys formed together to optimize the material properties of each constituent alloy.
- the hub 14 and web 18 portions can comprise a first material 22 composition of titanium alloy or nickel alloy powder such as, Ni-Co-Cr-Al alloy.
- the rim portion 16 can comprise another second material 24 such as a nickel powder alloy such as, Ni-Co-Cr-Ta alloy.
- the first material 22 can comprise properties that are best suited for a particular region of the component 10, such as, the hub 14 and web 18 region of the component 10.
- the second material 24 can comprise properties that are best suited for another region of the component 10, such as, the rim 16 region.
- the first material 22 can be a lower cost alloy and the second material 24 can be a more expensive alloy, and in exemplary embodiments capable of operating at higher operating temperatures and having superior mechanical properties such as being able to operate under higher stress levels for example creep and stress rupture.
- the preform 20 can be formed by use of dynamic consolidation or compaction of alloy powder metallurgy material(s), such as a nickel alloy powder.
- dynamic consolidation and dynamic compaction as well as dynamic bonding can be used interchangeably throughout the description.
- Dynamic compaction is characterized as momentary application of an extremely high pressure. This is contrasted with the compression characteristic of press-sintered and hot-press methods used in other processes, which are conducted at a much lower pressure and are carried out over an extended period of time.
- Dynamic compaction is best achieved by shock waves produced by, for example, contact with a shaped explosive charge, or by impact with a high-velocity projectile.
- the shock waves moving through the powder create pressures that are several times the flow stress of the binding metallic phase, typically several GPa (usually about 2 to 7 GPa.).
- Consolidation occurs by deformation of the powder particles and extrusion into void spaces between the particles.
- the material at or near the surface of the particle undergoes temperature pulses that range from microseconds to milliseconds, but these are quickly quenched by heat flow into the bulk of the powder particle. Since the heating is extremely short, it cannot support chemical reaction, melting, or other phase formation processes. Thus, it is possible to essentially preserve the original microstructure of the alloy material interface, with little or no chemical reaction or alloying. Thus, the formation of undesirable phases that can compromise the physical properties of the final compacted shape is avoided.
- the preform 20 can be formed into a generally rectilinear shaped cross section with an end portion 26. It is contemplated that the preform 20 can be formed into any variety of shapes, some of which are near net shaped geometry. In an exemplary embodiment, the cross-sectional end portion 26 can be crescent shaped to allow for a larger surface area of contact for bonding, a shear component in loading, as well as to facilitate sonic inspection of the bond interface both radially and axially.
- the preform 20 can be formed by filling a cross sectional rectilinear shaped or more appropriately shaped container with the first material 22 powder. Excess air/gases can be evacuated from the container. The container is sealed by mechanical means and/or by welding. The sealed container is then subjected to instantaneous dynamic compaction (i.e., explosion) which applies very high pressure to the exterior surface of the container. The container is collapsed upon the internal powder 22 with the high pressure force to form a solid powder metallurgy billet encased by the container. The container is then removed by conventional machining.
- instantaneous dynamic compaction i.e., explosion
- another container 28 for example having a generally rectilinear cross sectional shape, can be welded or otherwise affixed to the preform 20 proximate the end portion 26. It is contemplated that the shape of the container 28 can be optimized to produce the best bond between the preform 20 and the second alloy powder 24.
- the container 28 is filled with the second alloy powder 24.
- a filling tube 30 is shown and can be substituted by a rigid cover (not shown), or an integral boss welded to the container 28 and an internally fitting plug (not shown) substituted for the filling tube 30.
- the container can be evacuated of air and other gases. In an exemplary embodiment, a vacuum of 10 -6 Torr (133 ⁇ Pa) can be applied to the container to prevent oxidation of the second powder 24.
- the second alloy powder material 24 is then dynamically compacted to bond with the preform 20 along the end portion 26.
- the dynamic compaction forms a solid powder metallurgy billet (preform) encased by the container 28.
- the container 28 can be removed from the preform 20 and rim portion 16 of the component 10.
- the newly formed component 10 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of the component 10, such as shown in dashed lines at FIG. 1 .
- FIG. 2 shows an exemplary embodiment of a turbine engine component precursor 100 formed by a powdered material 110 dynamically bonded to a preform 112.
- the exemplary embodiment of FIG. 2 shares many similarities to the exemplary embodiment of FIG. 1 .
- the preform 112 is similar to the preform 20 at FIG. 1 , since it can be a solid of virtually any shape formed by use of dynamic consolidation or compaction of alloy powder metallurgy material(s),(i.e., a first alloy 114), such as a nickel alloy powder.
- the preform 112 in this embodiment, is a rod or bar shape, having a predefined length centered around the centerline CL. In an exemplary embodiment the predefined length can be several feet.
- the diameter of the preform 112 can be on the order of inches (cm) depending on the ultimate size of the turbine engine component precursor 100.
- the preform 112 can be placed into a container 116 of appropriate size and shape.
- the container 116 can be sized, such that, a second alloy material 118, or alloy powder metallurgy material(s), can be filled around the preform 112, to a predefined dimension.
- the predefined dimension can be equal to the thickness of the second alloy material 118 to be formed around the preform 112. In an exemplary embodiment the predefined dimension can be on the order of inches (cm), also depending on the ultimate size of the turbine engine component precursor 100.
- the container 116 can be a cylindrical shape forming a cavity 120 that surrounds the preform 112 and that is configured to be filled with the second alloy material 118.
- the container 116 includes a first end or cap 122 and a second end or cap 124 opposite the first end 122.
- the first and second ends 122, 124 enclose the cavity and encapsulate the second alloy material 118.
- the first and second ends 122, 124 can include at least one crush-zone 125.
- the crush-zone 125 can be formed as a channel, slot, or other feature of reduced thickness in the cap/end.
- the crush-zone 125 can be formed as a perimeter, or circular shape depending on the shape of the ends 122, 124.
- the crush-zone 125 allows for the complete and uniform compaction of the powdered material 110 upon dynamic compaction.
- the crush-zone 125 reduces the mechanical strength of the ends 122, 124 and thus the resistance to deformation of the ends 122, 124.
- the crush-zone minimizes any negative impact the ends 122, 124 may have on the compaction and bonding of the powder material 110.
- a tube 126 can be inserted through the first end 122, allowing communication of materials/gases with the cavity 120 and outside the container 116.
- the cavity 120 of the container 116 can be filled with the alloy powder metallurgy material(s) 118 through the tube 126.
- the tube 126 can also facilitate evacuation of the container, removing any unwanted gases, such as, gases that may promote oxidation.
- the first end 122, second end 124 and tube 126 can be sealed, such that the container 116 filled with the preform 112 and second alloy material 118 is sealed from any invasive gases.
- the container 116 is sealed by mechanical means or by welding.
- the second alloy powder material 118 is then dynamically compacted to bond with the preform 112 along an interface 128 between the preform 112 and the second alloy material 118.
- the container 116 can be removed from the preform 112 and newly formed the component precursor 100.
- the component precursor 100 can be cut into wafers/disks as shown by the dashed lines.
- the newly formed component precursor 100 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of a component 130, such as shown in dashed lines at FIG. 2 .
- the component precursor 100 can be utilized for high volume production of components 130, such as airseals.
- the disks can have a central or inner portion 132 surrounded by an outer portion 134.
- the central portion 132 can comprise the first alloy 114 and the outer portion 134 can comprise the second alloy 118.
- FIG. 3 shows another exemplary embodiment, namely a powdered material dynamically bonded preform to be bonded to another powdered material dynamically bonded preform.
- This exemplary embodiment is similar to the other exemplary embodiments shown in FIG. 1 and FIG. 2 , with the difference being the second alloy is not a powder material but instead already formed by dynamic compaction into a preform.
- a component precursor 200 can be formed from the dynamic compaction of a first preform 210 and a second preform 212.
- Each of the first preform 210 and second preform 212 can be originally formed by dynamic compaction of a first alloy material 214 for the first preform 210 and a second alloy material 216 for the second preform 212.
- the first preform 210 can be located in a container 218 along a centerline CL.
- the second preform 212 can be located in the container 218 around the first preform 210 such that a first preform surface 220 can be bonded to a second preform surface 222.
- the first preform 210 can comprise a rod or cylinder shape.
- the second preform 212 can comprise of an open cylinder shape, wherein the open cylinder shape of the second preform 212 encircles the cylinder shape of the first preform 210.
- the container 218 also is formed by a hollow cylinder shape canister tube 224 with a first end 226 and a second end 228 coupled to the edges 227 of the cylinder shaped tube 224.
- the canister tube 224 can extend beyond the first end 226 and second end 228 with welds formed in a location, such as above the ends 226, 228, so as to avoid interfering with the dynamic compaction.
- the first and second ends 226, 228 can include at least one crush-zone 229.
- the crush-zone 229 can be formed as a channel, slot, or other feature of reduced thickness in the cap/end.
- the crush-zone 229 can be formed as a perimeter, or circular shape depending on the shape of the ends 226, 228.
- the crush-zone 229 is configured to permit controlled deformation of the canister tube 224 during dynamic compaction such that the ends 226, 228 compressively yield uniformly, allowing the canister tube 224 to compressively yield uniformly onto the external surface of second preform 212.
- the crush-zone 229 allows for the complete bonding of the first preform 210 with the second preform 212 upon dynamic compaction.
- An evacuation tube 230 can be inserted through the first end 226, allowing communication of materials/gases with a cavity 232 and outside the container 218.
- the evacuation tube 230 can facilitate evacuation of the container 218, removing any unwanted gases, such as, gases that may promote oxidation.
- the first end 226, second end 228 and evacuation tube 230 can be sealed, such that the container 218 filled with the first preform 210 and second preform 212 is sealed from any invasive gases.
- the container 218 can be sealed by mechanical means or by welding.
- the cavity 232 includes controlled gaps 234 and/or tabs 235.
- the controlled gaps 234 can be located between the first preform surface 220 and second preform surface 222 as well as between an inner surface 236 of the canister tube 224 and an external surface 238 of the second preform 212.
- the tabs 235 shown in a partial cut-away, properly space the controlled gaps 234.
- the tabs 235 can be integrally machined or mechanically installed into the ends 226, 228.
- the tabs 235 are designed to crush upon dynamic compaction, allowing intimate contact between inner surface 236 and outer external surface 238.
- the tabs 235 are of minimal dimension, so that they do not negatively impact the dynamic compaction of the first preform 210 with the second preform 212.
- the tabs 235 if needed can be machined away.
- the controlled gaps 234 and tabs 235 facilitate proper dynamic compaction between the first preform 210 and second preform 212 along the first preform surface 220 and second preform surface 222.
- the container 218 can be removed from the preform 210, 212 and newly formed the component precursor 200.
- the newly formed component precursor 200 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of a component 240, such as shown in dashed lines at FIG. 3 .
- the component precursor 200 can be utilized for high volume production of components 240, such as airseals.
- the component precursor 200 can be cut into wafers/disks as shown by the dashed lines.
- the disks can have a central or inner portion 242 surrounded by an outer portion 244.
- the central portion 242 can comprise the first alloy 214 and the outer portion 244 can comprise the second alloy 216.
- the container 218 can include an insert 246, for example made from a low cost steel material.
- the low cost steel insert 246 can be placed at the center of the first preform 210 or other location that is intended to be removed at a later time.
- the steel insert 246 allows for reduced waste of the first alloy 214 when the portion of the component precursor 200 is transformed into component 240.
- FIG. 4 shows an exemplary process embodiment, namely the formation of a powdered material dynamically compacted preform. This exemplary embodiment is similar to the other exemplary embodiments shown in FIG. 1 , FIG. 2 and FIG. 3 .
- the first step includes forming a container 300.
- the component precursor or preform can be formed by dynamic compaction 310 of a first alloy material for the preform.
- the preform is then processed into a final shape 312.
- Dynamic compaction provides an alternative method for compaction of powder metallurgy material as compared to conventional methods of compaction, such as, hot isostatic pressing or extrusion.
- the new method allows for the compaction of materials that previously may not have been capable of compaction via previously known methods.
- Dynamic compaction is achieved without the use of costly hot isostatic pressing or extrusion equipment and their associated facilities.
- the turn-around time for dynamic compaction process powder metallurgy material can be months faster that previously known method's wait times for extruded or hot isostatic pressed powder materials.
- the dynamic bonding techniques disclosed herein allow bonding of similar or dissimilar powder metallurgy material at ambient temperatures with low cost tooling and fixtures.
- a broader design space can be achieved by use of the disclosed process including hybrid powder metallurgy material combinations and configurations.
- the disclosed method enables the bonding of dissimilar materials and blend ratios, e.g., ceramic/metallic powders, insitu ceramic/metallic powders, nano insitu ceramic/metallic powders that could not previously be achieved.
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
- The present disclosure is directed to the improved process of dynamic bonding to create hybrid powder metallurgy parts.
- Advanced aerospace designs continue to challenge materials and materials technology. While powder metallurgy materials offer unique advantages for many aerospace components, they could be further optimized if dissimilar materials could be bonded into a single component.
- For example, in gas turbine engines, disks which support turbine blades rotate at high speeds in an elevated temperature environment. The separate portions of the disks are exposed to different operating conditions and temperatures. Thus, different combinations of mechanical properties are required at different locations. The high temperature rim portion has fatigue crack growth resistance and creep resistance, while the highly stressed hub portion has high burst strength at relatively moderate temperatures and fatigue crack growth resistance. The hub portion also has high resistance to low cycle fatigue for long component life.
- Because of these differing requirements for the mechanical properties of the separate disk portions, and the extreme temperature gradients along the radius of a turbine disk, a single alloy is not well suited to satisfy the requirements of both the hub and the rim area of a modern turbine disk.
- A possible solution is to use a dual alloy disk with different alloys used in the different portions of the disk, depending upon the properties desired. The disk has a joint region in which the different alloys are joined together to form an integral article.
- Numerous techniques for fabricating dual alloy disks have been considered, such as fusion welding, inertia welding, diffusion bonding, bi-casting, and hot isostatic pressing which may be employed to consolidate powder used for one portion of a disk, such as the hub, and also to join it to the other portion. Many of these processes have drawbacks, for example, the disadvantage of hot isostatic pressing is that any impurities present at the joint prior to hot isostatic pressing will remain, and may be exacerbated by the lengthy time at elevated temperature and pressure.
- Present powder-metallurgical techniques require three to four steps to produce a finished product. For example, producing tungsten requires pressing and pre-sintering, followed by a consolidation sinter and/ or several hot-working steps. Dynamic bonding eliminates the need for large presses and expensive hot-pressing dies. In many instances, actual production time and costs may be reduced.
- In accordance with the present disclosure, there is provided a dynamic compaction process that comprises forming a preform. The steps of forming a preform comprise providing a first container, the first container having an interior and an exterior; filling the interior of the first container with a first powder material; sealing the first container; subjecting the exterior of the first container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the first container resulting in the first container collapsing upon the first powder material; forming a solid powder metallurgy billet encased by the first container. The process includes removing the first container from the solid powder metallurgy billet. The process includes attaching a second container to at least a portion of the preform, the second container having an interior and an exterior; filling the second container with a second powder material; sealing the second container; subjecting the exterior of the second container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the second container resulting in the second container collapsing upon the second powder material; forming a second solid powder metallurgy material from the second powder material encased by the second container; bonding the second solid powder metallurgy material to the portion of the preform; and removing the second container from the preform and the second solid powder metallurgy material.
- In an exemplary embodiment, at least a portion of the preform comprises at least one of an end having a crescent shape and an interface of the preform.
- In an exemplary embodiment the crescent shaped end is configured to provide at least one of a larger surface area of contact for bonding, a shear component in loading, and facilitate sonic inspection of the bond interface both radially and axially.
- In an exemplary embodiment the first material comprises a nickel alloy and the second material comprises a different nickel alloy.
- In an exemplary embodiment the process further comprises removing unwanted gases by use of a vacuum on at least one of the first container and the second container subsequent to filling each respective container.
- In an exemplary embodiment the process further comprises forming a component from the combination of the preform bonded to the second solid powder metallurgy material.
- In an exemplary embodiment the component comprises a rotor having a hub and web portion formed from the first powder material and at least a portion of a rim portion formed from the second powder material.
- In an exemplary embodiment the process further comprises forming a component precursor from the combination of the preform bonded to the second solid powder metallurgy material and cutting at least one disk from the component precursor.
- In accordance with the present disclosure, there is provided an aerospace component comprising a first solid powder metallurgy material and a second powder material bonded together with dynamic compaction.
- In an exemplary embodiment the first solid powder metallurgy material comprises a first portion and a second portion and the second powder material comprises third portion.
- In an exemplary embodiment the first portion and the second portion comprises the first solid powder metallurgy material and the third portion comprises the second solid powder metallurgy material.
- In an exemplary embodiment the first solid powder metallurgy material and the second solid powder metallurgy material comprise different materials.
- In an exemplary embodiment the aerospace component is a rotor.
- In an exemplary embodiment the first portion comprises a hub of the rotor. The second portion comprises a web of the rotor; and the third portion comprises a rim of the rotor.
- In accordance with the present disclosure, there is provided a dynamic compaction process that comprises forming a component precursor. Forming the component precursor comprises forming a first container, the first container having an interior and an exterior; filling the interior of the first container with a first powder material; sealing the first container; subjecting the exterior of the first container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the first container resulting in the first container collapsing upon the first powder material; forming a solid powder metallurgy billet encased by the first container; and removing the first container from the solid powder metallurgy billet; forming a second solid powder metallurgy billet from a second powder material; inserting the first solid powder metallurgy billet and the second solid powder metallurgy billet into a second container, the second container having an interior and an exterior; sealing the second container; subjecting the exterior of the second container to an instantaneous dynamic compaction, wherein the instantaneous dynamic compaction applies pressure to the exterior of the second container resulting in the second container collapsing upon the second solid powder metallurgy billet and the second solid powder metallurgy billet collapsing upon the first solid powder metallurgy billet; bonding the second solid powder metallurgy billet to the first solid powder metallurgy billet; and removing the second container from the first solid powder metallurgy billet and the second solid powder metallurgy billet.
- In an exemplary embodiment the first material comprises a nickel alloy and the second material comprised a different nickel alloy.
- In an exemplary embodiment the process further comprises forming a component precursor from the combination of the first solid powder metallurgy billet and the second solid powder metallurgy billet.
- In an exemplary embodiment the process further comprises cutting at least one disk from the component precursor.
- In an exemplary embodiment at least one controlled gap is formed between the first solid powder metallurgy billet and the second solid powder metallurgy billet.
- In an exemplary embodiment the second container includes at least one of a crush zone and a tab.
- Other details of the dynamic bonding process are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
-
-
FIG. 1 is a cross-sectional schematic representation of a powdered material dynamically bonded to a turbine engine component; -
FIG. 2 is a cross-sectional schematic representation of an exemplary embodiment of a powdered material dynamically bonded to a turbine engine component precursor; -
FIG. 3 is a cross-sectional schematic representation of an exemplary embodiment of a powdered material dynamically bonded preform to be bonded to another powdered material dynamically bonded preform; -
FIG. 4 is a process flow diagram of an exemplary dynamic compaction process. - Referring now to
FIG. 1 , there is illustrated a turbineengine component precursor 10, such as an annular rotor disk having acenterline 12. It is contemplated that other components can be formed with the process, such as shafts, blades, airseals and the like. The exemplaryturbine engine component 10, when fully manufactured (as shown in dashed lines), has ahub portion 14 and arim portion 16 connected by aweb portion 18. Thecomponent 10 is partially built-up from apreform 20. - The
turbine engine component 10 may be formed from a titanium-based alloy or nickel based alloy or a composite of alloys formed together to optimize the material properties of each constituent alloy. In an exemplary embodiment, thehub 14 andweb 18 portions can comprise afirst material 22 composition of titanium alloy or nickel alloy powder such as, Ni-Co-Cr-Al alloy. Therim portion 16 can comprise anothersecond material 24 such as a nickel powder alloy such as, Ni-Co-Cr-Ta alloy. Thefirst material 22 can comprise properties that are best suited for a particular region of thecomponent 10, such as, thehub 14 andweb 18 region of thecomponent 10. Thesecond material 24 can comprise properties that are best suited for another region of thecomponent 10, such as, therim 16 region. In an exemplary embodiment, thefirst material 22 can be a lower cost alloy and thesecond material 24 can be a more expensive alloy, and in exemplary embodiments capable of operating at higher operating temperatures and having superior mechanical properties such as being able to operate under higher stress levels for example creep and stress rupture. - In one alternative, the
preform 20 can be formed by use of dynamic consolidation or compaction of alloy powder metallurgy material(s), such as a nickel alloy powder. The terms dynamic consolidation and dynamic compaction as well as dynamic bonding can be used interchangeably throughout the description. - The alloy powder is subjected to dynamic compaction. Dynamic compaction is characterized as momentary application of an extremely high pressure. This is contrasted with the compression characteristic of press-sintered and hot-press methods used in other processes, which are conducted at a much lower pressure and are carried out over an extended period of time.
- Dynamic compaction is best achieved by shock waves produced by, for example, contact with a shaped explosive charge, or by impact with a high-velocity projectile. The shock waves moving through the powder create pressures that are several times the flow stress of the binding metallic phase, typically several GPa (usually about 2 to 7 GPa.). Consolidation occurs by deformation of the powder particles and extrusion into void spaces between the particles. The material at or near the surface of the particle undergoes temperature pulses that range from microseconds to milliseconds, but these are quickly quenched by heat flow into the bulk of the powder particle. Since the heating is extremely short, it cannot support chemical reaction, melting, or other phase formation processes. Thus, it is possible to essentially preserve the original microstructure of the alloy material interface, with little or no chemical reaction or alloying. Thus, the formation of undesirable phases that can compromise the physical properties of the final compacted shape is avoided.
- The
preform 20 can be formed into a generally rectilinear shaped cross section with anend portion 26. It is contemplated that thepreform 20 can be formed into any variety of shapes, some of which are near net shaped geometry. In an exemplary embodiment, thecross-sectional end portion 26 can be crescent shaped to allow for a larger surface area of contact for bonding, a shear component in loading, as well as to facilitate sonic inspection of the bond interface both radially and axially. - The
preform 20 can be formed by filling a cross sectional rectilinear shaped or more appropriately shaped container with thefirst material 22 powder. Excess air/gases can be evacuated from the container. The container is sealed by mechanical means and/or by welding. The sealed container is then subjected to instantaneous dynamic compaction (i.e., explosion) which applies very high pressure to the exterior surface of the container. The container is collapsed upon theinternal powder 22 with the high pressure force to form a solid powder metallurgy billet encased by the container. The container is then removed by conventional machining. - In an exemplary embodiment, another
container 28, for example having a generally rectilinear cross sectional shape, can be welded or otherwise affixed to thepreform 20 proximate theend portion 26. It is contemplated that the shape of thecontainer 28 can be optimized to produce the best bond between thepreform 20 and thesecond alloy powder 24. - The
container 28 is filled with thesecond alloy powder 24. A fillingtube 30 is shown and can be substituted by a rigid cover (not shown), or an integral boss welded to thecontainer 28 and an internally fitting plug (not shown) substituted for the fillingtube 30. The container can be evacuated of air and other gases. In an exemplary embodiment, a vacuum of 10-6 Torr (133 µPa) can be applied to the container to prevent oxidation of thesecond powder 24. The secondalloy powder material 24 is then dynamically compacted to bond with thepreform 20 along theend portion 26. The dynamic compaction forms a solid powder metallurgy billet (preform) encased by thecontainer 28. Thecontainer 28 can be removed from thepreform 20 andrim portion 16 of thecomponent 10. - The newly formed
component 10 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of thecomponent 10, such as shown in dashed lines atFIG. 1 . -
FIG. 2 shows an exemplary embodiment of a turbineengine component precursor 100 formed by apowdered material 110 dynamically bonded to apreform 112. The exemplary embodiment ofFIG. 2 shares many similarities to the exemplary embodiment ofFIG. 1 . Thepreform 112 is similar to thepreform 20 atFIG. 1 , since it can be a solid of virtually any shape formed by use of dynamic consolidation or compaction of alloy powder metallurgy material(s),(i.e., a first alloy 114), such as a nickel alloy powder. Thepreform 112 in this embodiment, is a rod or bar shape, having a predefined length centered around the centerline CL. In an exemplary embodiment the predefined length can be several feet. The diameter of thepreform 112 can be on the order of inches (cm) depending on the ultimate size of the turbineengine component precursor 100. - The
preform 112 can be placed into acontainer 116 of appropriate size and shape. Thecontainer 116 can be sized, such that, asecond alloy material 118, or alloy powder metallurgy material(s), can be filled around thepreform 112, to a predefined dimension. The predefined dimension can be equal to the thickness of thesecond alloy material 118 to be formed around thepreform 112. In an exemplary embodiment the predefined dimension can be on the order of inches (cm), also depending on the ultimate size of the turbineengine component precursor 100. - The
container 116 can be a cylindrical shape forming acavity 120 that surrounds thepreform 112 and that is configured to be filled with thesecond alloy material 118. Thecontainer 116 includes a first end orcap 122 and a second end or cap 124 opposite thefirst end 122. The first and second ends 122, 124 enclose the cavity and encapsulate thesecond alloy material 118. The first and second ends 122, 124 can include at least one crush-zone 125. The crush-zone 125 can be formed as a channel, slot, or other feature of reduced thickness in the cap/end. The crush-zone 125 can be formed as a perimeter, or circular shape depending on the shape of theends zone 125 allows for the complete and uniform compaction of thepowdered material 110 upon dynamic compaction. The crush-zone 125 reduces the mechanical strength of theends ends ends powder material 110. - A
tube 126 can be inserted through thefirst end 122, allowing communication of materials/gases with thecavity 120 and outside thecontainer 116. Thecavity 120 of thecontainer 116 can be filled with the alloy powder metallurgy material(s) 118 through thetube 126. In exemplary embodiments, thetube 126 can also facilitate evacuation of the container, removing any unwanted gases, such as, gases that may promote oxidation. - The
first end 122,second end 124 andtube 126 can be sealed, such that thecontainer 116 filled with thepreform 112 andsecond alloy material 118 is sealed from any invasive gases. Thecontainer 116 is sealed by mechanical means or by welding. - The second
alloy powder material 118 is then dynamically compacted to bond with thepreform 112 along aninterface 128 between thepreform 112 and thesecond alloy material 118. Thecontainer 116 can be removed from thepreform 112 and newly formed thecomponent precursor 100. - The
component precursor 100 can be cut into wafers/disks as shown by the dashed lines. The newly formedcomponent precursor 100 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of acomponent 130, such as shown in dashed lines atFIG. 2 . - In an exemplary embodiment, the
component precursor 100 can be utilized for high volume production ofcomponents 130, such as airseals. In this form, the disks can have a central orinner portion 132 surrounded by anouter portion 134. Thecentral portion 132 can comprise thefirst alloy 114 and theouter portion 134 can comprise thesecond alloy 118. -
FIG. 3 shows another exemplary embodiment, namely a powdered material dynamically bonded preform to be bonded to another powdered material dynamically bonded preform. This exemplary embodiment is similar to the other exemplary embodiments shown inFIG. 1 andFIG. 2 , with the difference being the second alloy is not a powder material but instead already formed by dynamic compaction into a preform. - A
component precursor 200 can be formed from the dynamic compaction of afirst preform 210 and asecond preform 212. Each of thefirst preform 210 andsecond preform 212 can be originally formed by dynamic compaction of afirst alloy material 214 for thefirst preform 210 and asecond alloy material 216 for thesecond preform 212. - The
first preform 210 can be located in acontainer 218 along a centerline CL. Thesecond preform 212 can be located in thecontainer 218 around thefirst preform 210 such that afirst preform surface 220 can be bonded to asecond preform surface 222. In an exemplary embodiment, thefirst preform 210 can comprise a rod or cylinder shape. Thesecond preform 212 can comprise of an open cylinder shape, wherein the open cylinder shape of thesecond preform 212 encircles the cylinder shape of thefirst preform 210. Thecontainer 218 also is formed by a hollow cylindershape canister tube 224 with afirst end 226 and asecond end 228 coupled to theedges 227 of the cylinder shapedtube 224. Thecanister tube 224 can extend beyond thefirst end 226 andsecond end 228 with welds formed in a location, such as above theends - The first and second ends 226, 228 can include at least one crush-
zone 229. The crush-zone 229 can be formed as a channel, slot, or other feature of reduced thickness in the cap/end. The crush-zone 229 can be formed as a perimeter, or circular shape depending on the shape of theends zone 229 is configured to permit controlled deformation of thecanister tube 224 during dynamic compaction such that the ends 226, 228 compressively yield uniformly, allowing thecanister tube 224 to compressively yield uniformly onto the external surface ofsecond preform 212. The crush-zone 229 allows for the complete bonding of thefirst preform 210 with thesecond preform 212 upon dynamic compaction. - An
evacuation tube 230 can be inserted through thefirst end 226, allowing communication of materials/gases with acavity 232 and outside thecontainer 218. In exemplary embodiments, theevacuation tube 230 can facilitate evacuation of thecontainer 218, removing any unwanted gases, such as, gases that may promote oxidation. - The
first end 226,second end 228 andevacuation tube 230 can be sealed, such that thecontainer 218 filled with thefirst preform 210 andsecond preform 212 is sealed from any invasive gases. Thecontainer 218 can be sealed by mechanical means or by welding. - The
cavity 232 includes controlledgaps 234 and/ortabs 235. The controlledgaps 234 can be located between thefirst preform surface 220 andsecond preform surface 222 as well as between aninner surface 236 of thecanister tube 224 and anexternal surface 238 of thesecond preform 212. Thetabs 235, shown in a partial cut-away, properly space the controlledgaps 234. Thetabs 235 can be integrally machined or mechanically installed into theends tabs 235 are designed to crush upon dynamic compaction, allowing intimate contact betweeninner surface 236 and outerexternal surface 238. Thetabs 235 are of minimal dimension, so that they do not negatively impact the dynamic compaction of thefirst preform 210 with thesecond preform 212. Thetabs 235, if needed can be machined away. The controlledgaps 234 andtabs 235 facilitate proper dynamic compaction between thefirst preform 210 andsecond preform 212 along thefirst preform surface 220 andsecond preform surface 222. - The
container 218 can be removed from thepreform component precursor 200. The newly formedcomponent precursor 200 is now ready for subsequent processing, such as, forging and thermal mechanical processes as required to form the final shape of acomponent 240, such as shown in dashed lines atFIG. 3 . - In an exemplary embodiment, the
component precursor 200 can be utilized for high volume production ofcomponents 240, such as airseals. Thecomponent precursor 200 can be cut into wafers/disks as shown by the dashed lines. In this form, the disks can have a central orinner portion 242 surrounded by anouter portion 244. Thecentral portion 242 can comprise thefirst alloy 214 and theouter portion 244 can comprise thesecond alloy 216. - In another exemplary embodiment, the
container 218 can include aninsert 246, for example made from a low cost steel material. The lowcost steel insert 246 can be placed at the center of thefirst preform 210 or other location that is intended to be removed at a later time. Thesteel insert 246 allows for reduced waste of thefirst alloy 214 when the portion of thecomponent precursor 200 is transformed intocomponent 240. -
FIG. 4 shows an exemplary process embodiment, namely the formation of a powdered material dynamically compacted preform. This exemplary embodiment is similar to the other exemplary embodiments shown inFIG. 1 ,FIG. 2 andFIG. 3 . - The first step includes forming a
container 300. The component precursor or preform can be formed bydynamic compaction 310 of a first alloy material for the preform. The preform is then processed into afinal shape 312. - Dynamic compaction provides an alternative method for compaction of powder metallurgy material as compared to conventional methods of compaction, such as, hot isostatic pressing or extrusion. The new method allows for the compaction of materials that previously may not have been capable of compaction via previously known methods. Dynamic compaction is achieved without the use of costly hot isostatic pressing or extrusion equipment and their associated facilities. Thus, the turn-around time for dynamic compaction process powder metallurgy material can be months faster that previously known method's wait times for extruded or hot isostatic pressed powder materials. The dynamic bonding techniques disclosed herein allow bonding of similar or dissimilar powder metallurgy material at ambient temperatures with low cost tooling and fixtures. A broader design space can be achieved by use of the disclosed process including hybrid powder metallurgy material combinations and configurations. The disclosed method enables the bonding of dissimilar materials and blend ratios, e.g., ceramic/metallic powders, insitu ceramic/metallic powders, nano insitu ceramic/metallic powders that could not previously be achieved.
- There has been provided a dynamic compaction process. While the dynamic compaction process has been described in the context of specific embodiments thereof, other unforeseen alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.
Claims (15)
- A dynamic compaction process comprising:forming a preform (20; 112) comprising:providing a first container (28), said first container (28) having an interior and an exterior;filling said interior of said first container (28) with a first powder material (22);sealing said first container (28);subjecting said exterior of said first container (28) to an instantaneous dynamic compaction, wherein said instantaneous dynamic compaction applies pressure to the exterior of said first container (28) resulting in said first container (28) collapsing upon said first powder material (22);forming a solid powder metallurgy material encased by said first container (28); andremoving said first container (28) from said solid powder metallurgy material (22);attaching a second container (116) to at least a portion of said preform (20; 112), said second container (116) having an interior and an exterior;filling said second container (116) with a second powder material (24; 110, 118);sealing said second container (116);subjecting said exterior of said second container (116) to an instantaneous dynamic compaction, wherein said instantaneous dynamic compaction applies pressure to the exterior of said second container (116) resulting in said second container (116) collapsing upon said second powder material (24; 110, 118);forming a second solid powder metallurgy material (24; 110, 118) from said second powder material (24; 110, 118) encased by said second container (116);bonding said second solid powder metallurgy material (24; 110, 118) to said portion of said preform (20; 112); andremoving said second container (116) from said preform (20; 112) and said second solid powder metallurgy material (24; 110, 118).
- The process according to claim 1, wherein said at least a portion of said preform (20; 112) comprises at least one of an end (26) having a crescent shape and an interface (128) of said preform (20; 112).
- The process according to claim 2, wherein said crescent shaped end (26) is configured to provide at least one of a larger surface area of contact for bonding, a shear component in loading, and facilitate sonic inspection of the bond interface (128) both radially and axially.
- The process according to any preceding claim, further comprising:removing unwanted gases by use of a vacuum on at least one of said first container (28) and said second container (116) subsequent to filling each respective container (28, 116).
- The process according to any preceding claim, further comprising:forming a component (10; 130) from the combination of said preform (20; 112) bonded to said second solid powder metallurgy material (24; 110, 118).
- The process according to claim 5, wherein said component (10) comprises a rotor (10) having a hub and web portion (14, 18) formed from said first powder material (22) and at least a portion of a rim portion (16) formed from said second powder material (24).
- The process according to any preceding claim, further comprising:forming a component precursor (110) from the combination of said preform (20; 112) bonded to said second solid powder metallurgy material (24; 110, 118); andcutting at least one disk (130) from said component precursor (110).
- A dynamic compaction process comprising:forming a component precursor (200) comprising:forming a first container, said first container having an interior and an exterior;filling said interior of said first container with a first powder material (214);sealing said first container;subjecting said exterior of said first container to an instantaneous dynamic compaction, wherein said instantaneous dynamic compaction applies pressure to the exterior of said first container resulting in said first container collapsing upon said first powder material (214);forming a solid powder metallurgy billet (210) encased by said first container; andremoving said first container from said solid powder metallurgy billet (210);forming a second solid powder metallurgy billet (212) from a second powder material (216);
inserting said first solid powder metallurgy billet (210) and said second solid powder metallurgy billet (212) into a second container (218), said second container (218) having an interior and an exterior;
sealing said second container (218);
subjecting said exterior of said second container (218) to an instantaneous dynamic compaction, wherein said instantaneous dynamic compaction applies pressure to the exterior of said second container (218) resulting in said second container (218) collapsing upon said second solid powder metallurgy billet (212) and said second solid powder metallurgy billet (212) collapsing upon said first solid powder metallurgy billet (210);
bonding said second solid powder metallurgy billet (212) to said first solid powder metallurgy billet (210); and
removing said second container (218) from said first solid powder metallurgy billet (210) and said second solid powder metallurgy billet (212). - The process according to claim 8, further comprising:forming a component precursor (200) from the combination of said first solid powder metallurgy billet (210) and said second solid powder metallurgy billet (212), optionally further comprising:cutting at least one disk (240) from said component precursor (200).
- The process according to claim 8 or 9, wherein a least one controlled gap (234) is formed between said first solid powder metallurgy billet (210) and said second solid powder metallurgy billet (212).
- The process according to any of claims 8 to 10 wherein said second container (218) includes at least one of a crush zone (229) and a tab (235).
- The process according to any preceding claim, wherein said first material (214) comprises a nickel alloy and said second material (216) comprised a different nickel alloy.
- An aerospace component (10; 130) comprising a first solid powder metallurgy material (22; 114) and a second powder material (24; 110, 118) bonded together with dynamic compaction.
- The aerospace component (10) according to claim 13, wherein said first solid powder metallurgy material (22) comprises a first portion (14) and a second portion (18) and said second powder material (24) comprises third portion (16),wherein, optionally, said first solid powder metallurgy material (22; 114) and said second solid powder metallurgy material (24; 110; 118) comprise different materials.
- The aerospace component according to claim 14, wherein said aerospace component (10) is a rotor (10), wherein, optionally, said first portion (14) comprises a hub (14) of said rotor (10);
said second portion (18) comprises a web (18) of said rotor (10); and
said third portion (16) comprises a rim (16) of said rotor (10).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201514982627A | 2015-12-29 | 2015-12-29 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3187283A1 true EP3187283A1 (en) | 2017-07-05 |
EP3187283B1 EP3187283B1 (en) | 2020-03-11 |
Family
ID=57799486
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16206377.0A Active EP3187283B1 (en) | 2015-12-29 | 2016-12-22 | Dynamic bonding of powder metallurgy materials |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP3187283B1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114829062A (en) * | 2019-12-20 | 2022-07-29 | 赛峰集团 | Solution for manufacturing integral bladed disk |
CN115070040A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4065A same-species and different-species material multi-stage rotor assembly and preparation method thereof |
CN115070041A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4169 and TC17 same-material and different-material multistage rotor assembly and preparation method thereof |
CN115070039A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4169 homogeneous and heterogeneous material multi-stage rotor assembly and preparation method thereof |
CN115070044A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4169 and TA19 same-material and different-material multistage rotor assembly and preparation method thereof |
CN115070043A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4065A and GH4169 same-material and different-material multistage rotor assembly and preparation method thereof |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3220103A (en) * | 1962-09-27 | 1965-11-30 | Battelle Development Corp | Method of explosively compacting powders to form a dense body |
GB2228217A (en) * | 1989-02-07 | 1990-08-22 | Mtu Muenchen Gmbh | A method for connecting turbine wheel discs |
US20090317653A1 (en) * | 2008-06-24 | 2009-12-24 | Gm Global Technology Operations, Inc. | Method of compacting a first powder material and a second powder material |
US20140093384A1 (en) * | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Method of Manufacturing Complex Shaped Component |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5161950A (en) * | 1989-10-04 | 1992-11-10 | General Electric Company | Dual alloy turbine disk |
-
2016
- 2016-12-22 EP EP16206377.0A patent/EP3187283B1/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3220103A (en) * | 1962-09-27 | 1965-11-30 | Battelle Development Corp | Method of explosively compacting powders to form a dense body |
GB2228217A (en) * | 1989-02-07 | 1990-08-22 | Mtu Muenchen Gmbh | A method for connecting turbine wheel discs |
US20090317653A1 (en) * | 2008-06-24 | 2009-12-24 | Gm Global Technology Operations, Inc. | Method of compacting a first powder material and a second powder material |
US20140093384A1 (en) * | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Method of Manufacturing Complex Shaped Component |
Non-Patent Citations (2)
Title |
---|
"EXPLOSIVE WELDING, FORMING AND COMPACTION", 1 January 1983, APPLIED SCIENCE PUBLISHERS, ISBN: 978-94-011-9751-9, article T Z BLAZYNSKI: "Chapter 8 - Welding of tubular, rod and special assemblies", pages: 289 - 345, XP055368793, DOI: 10.1007/978-94-011-9751-9 * |
"EXPLOSIVE WELDING, FORMING AND COMPACTION", 27 April 2012, APPLIED SCIENCE PUBLISHERS, ISBN: 978-94-011-9751-9, article R PRÜMMER: "Chapter 10 - Powder Compaction", pages: 369 - 395, XP055366027, DOI: 10.1007/978-94-011-9751-9 * |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114829062A (en) * | 2019-12-20 | 2022-07-29 | 赛峰集团 | Solution for manufacturing integral bladed disk |
CN115070040A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4065A same-species and different-species material multi-stage rotor assembly and preparation method thereof |
CN115070041A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4169 and TC17 same-material and different-material multistage rotor assembly and preparation method thereof |
CN115070039A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4169 homogeneous and heterogeneous material multi-stage rotor assembly and preparation method thereof |
CN115070044A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4169 and TA19 same-material and different-material multistage rotor assembly and preparation method thereof |
CN115070043A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4065A and GH4169 same-material and different-material multistage rotor assembly and preparation method thereof |
CN115070041B (en) * | 2021-03-10 | 2024-04-19 | 中国航发商用航空发动机有限责任公司 | GH4169 and TC17 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof |
CN115070044B (en) * | 2021-03-10 | 2024-04-19 | 中国航发商用航空发动机有限责任公司 | GH4169 and TA19 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof |
CN115070043B (en) * | 2021-03-10 | 2024-06-18 | 中国航发商用航空发动机有限责任公司 | GH4065A and GH4169 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof |
CN115070039B (en) * | 2021-03-10 | 2024-06-21 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4169 homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof |
CN115070040B (en) * | 2021-03-10 | 2024-07-12 | 中国航发商用航空发动机有限责任公司 | FGH96 and GH4065A homogeneous and heterogeneous material multistage rotor assembly and preparation method thereof |
Also Published As
Publication number | Publication date |
---|---|
EP3187283B1 (en) | 2020-03-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3187283B1 (en) | Dynamic bonding of powder metallurgy materials | |
EP0202735B1 (en) | Process for making a composite powder metallurgical billet | |
US4327154A (en) | High-strength components of complex geometric shape and method for their manufacture | |
EP0171344B1 (en) | Method for fabricating an integrally bladed rotor | |
US7261855B2 (en) | Method and system for manufacturing of complex shape parts from powder materials by hot isostatic pressing with controlled pressure inside the tooling and providing the shape of the part by multi-layer inserts | |
US4526747A (en) | Process for fabricating parts such as gas turbine compressors | |
JP5777306B2 (en) | Apparatus and method for hot isostatic pressure container | |
CN106457399A (en) | A method for manufacture a metallic component by pre-manufactured bodies | |
EP2282858A1 (en) | Composite preform having a controlled fraction of porosity in at least one layer and methods for manufacture and use | |
EP1527842B1 (en) | A method of manufacturing a fibre reinforced metal matrix composite article | |
EP1533066B1 (en) | A method of manufacturing an article by applying heat and pressure, a method of connecting a pipe to a sealed assembly and a connector for use therein | |
US20070081912A1 (en) | Method of producing multiple microstructure components | |
EP1779946B1 (en) | Supersolvus hot isostatic pressing and ring rolling of hollow powder forms | |
EP2340905B1 (en) | A method of manufacturing a component | |
JPS5842703A (en) | Manufacture of preform of one body powder alloy part from more than two kinds of powder alloy | |
WO2008085189A9 (en) | Co-sintered multi-system tungsten alloy composite | |
KR102203134B1 (en) | Penetrator including a core surrounded by a flexible sheath and a method of manufacturing the penetrator | |
EP3187281B1 (en) | Dynamic bonding of powder metallurgy materials | |
EP3187282B1 (en) | Dynamic bonding of powder metallurgy materials | |
EP3187284B1 (en) | Dynamic bonding of powder metallurgy materials | |
JP6690288B2 (en) | Titanium-encapsulating structure and method for producing titanium multilayer material | |
US8392016B2 (en) | Adaptive method for manufacturing of complicated shape parts by hot isostatic pressing of powder materials with using irreversibly deformable capsules and inserts | |
JPH0598316A (en) | Production of superalloy composite | |
EP3639954B1 (en) | Powder metallurgy method for producing non-molybdenum-segregated article | |
JP6736777B2 (en) | Molybdenum material and manufacturing method thereof |
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 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20180105 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20181017 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20190502 |
|
GRAJ | Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted |
Free format text: ORIGINAL CODE: EPIDOSDIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTC | Intention to grant announced (deleted) | ||
INTG | Intention to grant announced |
Effective date: 20191016 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1242515 Country of ref document: AT Kind code of ref document: T Effective date: 20200315 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602016031431 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200611 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20200311 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200611 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200612 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200711 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200805 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1242515 Country of ref document: AT Kind code of ref document: T Effective date: 20200311 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602016031431 Country of ref document: DE |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
26N | No opposition filed |
Effective date: 20201214 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20201231 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201222 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201222 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200311 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 602016031431 Country of ref document: DE Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230520 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20231121 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20231122 Year of fee payment: 8 Ref country code: DE Payment date: 20231121 Year of fee payment: 8 |