US20140093384A1 - Method of Manufacturing Complex Shaped Component - Google Patents
Method of Manufacturing Complex Shaped Component Download PDFInfo
- Publication number
- US20140093384A1 US20140093384A1 US13/718,134 US201213718134A US2014093384A1 US 20140093384 A1 US20140093384 A1 US 20140093384A1 US 201213718134 A US201213718134 A US 201213718134A US 2014093384 A1 US2014093384 A1 US 2014093384A1
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- US
- United States
- Prior art keywords
- set forth
- hollows
- polymer core
- bladed rotor
- integrally bladed
- 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.)
- Abandoned
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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
- 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
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- 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
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D1/00—Electroforming
- C25D1/02—Tubes; Rings; Hollow bodies
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- 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
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/22—Manufacture essentially without removing material by sintering
Definitions
- This application relates to a method of making very complex shaped components in a manner that is reliable and simplified compared to the prior art.
- An integrally bladed rotor includes a hollow hub with a plurality of complex airfoil shapes extending radially outwardly of the hub.
- integrally bladed rotors are often manufactured using hot forging technologies and then other technologies, such as milling, super abrasive machining, electro-chemical machining or other types of machining.
- joining technologies such as linear friction welding, may be utilized to secure the airfoils to the hub.
- a method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process, plating a metal about surfaces of the polymer core, removing the polymer core leaving hollows within a plating core, and depositing metal powder within the hollows.
- a consolidation step occurs after the depositing of the metal powder into the hollows.
- the consolidation process is a hot isostatic pressurization process.
- the plating metal is a nickel based material.
- the metal powder is also a nickel based material.
- the complex shaped component is an integrally bladed rotor.
- the integrally bladed rotor has a hub and radially outwardly extending airfoils with the hollows that are formed in both the hub and the airfoils.
- the plating occurs utilizing electroplating.
- the polymer core is removed in a furnace.
- the polymer core is melted, disintegrated or evaporated in the furnace.
- the additive manufacturing process includes one of selective lithography analysis, selective laser sintering, fusion deposition of material or laminated object manufacturing.
- a computer model of the complex shaped component is utilized to control the additive manufacturing process to form the polymer core.
- dimensions of the polymer core are selected to be slightly smaller than dimensions of a desired final complex shaped part.
- an integrally bladed rotor has a hub with an inner bore and an outer surface.
- a plurality of airfoils extend radially outwardly of the outer surface.
- the airfoils and hub have radially outer surfaces and axially outer surfaces formed of a relatively thin metal plate layer.
- the plate layer is a nickel based material.
- the metal powder is a nickel based material.
- FIG. 1 illustrates an integrally bladed rotor
- FIG. 2A schematically illustrates an example additive manufacturing machine, and further shows a first step in forming the integrally bladed rotor.
- FIG. 2B shows an intermediate step
- FIG. 2C shows another intermediate step.
- FIG. 2D shows yet another intermediate step.
- FIG. 2E shows yet another intermediate step.
- FIG. 2F shows yet another manufacturing step.
- FIG. 2G shows yet another step.
- FIG. 1 An integrally bladed rotor 20 is illustrated in FIG. 1 .
- a hub 22 has an outer surface 24 , and a plurality of airfoils 26 extend radially outwardly of the outer surface 24 .
- the integrally bladed rotor 20 has a very complex shape and raises challenges to manufacture.
- This application is directed to a method of making such an integrally bladed rotor in a reliable and relatively simple manner compared to the prior art. While an integrally bladed rotor is specifically disclosed, any number of other complex shaped parts will benefit from the teachings of this application.
- FIG. 2A shows an initial step.
- a core 120 for forming an integrally bladed rotor is illustrated being only partially formed.
- a rapid prototyping process which utilizes additive manufacturing techniques is preferably utilized to form the core 120 from an appropriate polymer.
- a system 30 is shown schematically forming the core 120 from a polymer in such a rapid manufacturing process. Examples of such additive manufacturing processes include stereolithography (SLA), selective laser sintering, fused deposition modeling, laminated object manufacturing, or any other rapid manufacturing.
- SLA stereolithography
- selective laser sintering fused deposition modeling
- laminated object manufacturing laminated object manufacturing
- FIG. 2B shows the final core 220 .
- Core 220 is manufactured to be of the general exact shape of the final integrally bladed rotor 20 and has outer surface 224 , inner surface 222 , and airfoils 226 .
- FIG. 2C shows a subsequent step.
- a plating process (shown schematically at 34 ) is utilized to plate an appropriate metal for forming the integrally bladed rotor onto a polymer.
- the process deposits a plating 326 , 328 and 329 on the core 220 .
- FIG. 2C is an oversimplification, in that the plating 328 would typically only be found in the portions of the outer surface 224 intermediate blades 226 on the core.
- a blade 226 is illustrated in FIG. 2C , in fact, the area 327 would also receive the plating to form a lateral outer wall of the airfoils for the final integrally bladed rotor.
- the thickness of the plating may be exaggerated to show the plating layers.
- the purpose of FIG. 2C is to make clear that the plating would cover the core 220 , and that there would be plated metal on outer surfaces of the core 220 after the step 2 C.
- One metal which may be plated is an appropriate nickel or nickel alloy for forming the integrally bladed rotor 20 .
- One possible process 34 would be electroplating. The plating thickness should be controlled and selected to achieve a structurally sound configuration after the step 2 D.
- step 2 E hollows are illustrated at areas 500 and 501 .
- the core 120 has been removed, as shown in FIG. 2D .
- the combined core and plating as shown at 601 , may be placed in a furnace 600 as shown schematically in FIG. 2D .
- the polymer forming the core 220 may be melted, disintegrated, or evaporated in any known manner.
- a hollow structure 320 incorporates plating portions 326 , 327 , 328 and 329 . Within this hollow structure 320 are hollows 500 within each of the airfoils and hollows 501 within the portions 328 and between the sides 329 .
- FIG. 2F shows a subsequent step.
- a metal powder fills the hollows.
- the metal powder is shown at 400 and 401 , and may be deposited within the hollows in any known manner.
- a tool 610 is illustrated schematically delivering the metal powder into the hollows.
- the metal powder may be a nickel based powder that may be similar to the plating material.
- a feeder spruce system may be included.
- an integrally bladed rotor 520 may be subjected to some finishing operation.
- a hot isostatic pressure operation 601 is illustrated in FIG. 2G and provides very high pressure to the integrally bladed rotor 520 .
- a container is typically filled with a fluid, and the fluid is pressurized to, in turn, pressurize the enclosed part 520 . Powder out gassing may be utilized prior to the hot isostatic pressure operation.
- finishing techniques such as quasi-isostatic pressing or dynamic compaction can be utilized in place of the hot isostatic pressure.
- CAD model initially utilized to form the core at step 2 A may be adjusted to account for material shrinkage which might occur due to the consolidation operation.
- An integrally bladed rotor 520 has a hub with an inner bore 54 and an outer surface 522 , and a plurality of airfoils 523 extending outwardly of the outer surface.
- the airfoils 523 and hub have radially outer surfaces and axially outer surfaces formed of a relatively thin metal plate layer. There is metal powder within hollows defined axially and radially inwardly of the plated layer.
- the plate layer may be a nickel based material, and the metal powder may be a nickel based material.
Abstract
A method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process. A metal is plated about surfaces of the polymer core, and the polymer core is removed, leaving hollows within a plate core. Metal powder is deposited within the hollows. An integral blade rotor is also disclosed.
Description
- This application claims priority to U.S. Provisional Application No. 61/706,839 filed Sep. 28, 2012.
- This application relates to a method of making very complex shaped components in a manner that is reliable and simplified compared to the prior art.
- Modern technology is called upon to make increasingly complex shaped components. As one example, gas turbine engines are often provided with an integrally bladed rotor. An integrally bladed rotor includes a hollow hub with a plurality of complex airfoil shapes extending radially outwardly of the hub.
- Currently, integrally bladed rotors are often manufactured using hot forging technologies and then other technologies, such as milling, super abrasive machining, electro-chemical machining or other types of machining.
- In addition, joining technologies, such as linear friction welding, may be utilized to secure the airfoils to the hub.
- All of these processes are expensive and raise various challenges.
- In addition, laser powder deposition has been utilized for deposing material on outer surfaces of the integrally bladed rotor. However, these techniques have not always provided an acceptable finished component.
- In a featured embodiment, a method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process, plating a metal about surfaces of the polymer core, removing the polymer core leaving hollows within a plating core, and depositing metal powder within the hollows.
- In another embodiment according to the previous embodiment, a consolidation step occurs after the depositing of the metal powder into the hollows.
- In another embodiment according to any of the previous embodiments, the consolidation process is a hot isostatic pressurization process.
- In another embodiment according to any of the previous embodiments, the plating metal is a nickel based material.
- In another embodiment according to any of the previous embodiments, the metal powder is also a nickel based material.
- In another embodiment according to any of the previous embodiments, the complex shaped component is an integrally bladed rotor. The integrally bladed rotor has a hub and radially outwardly extending airfoils with the hollows that are formed in both the hub and the airfoils.
- In another embodiment according to any of the previous embodiments, the plating occurs utilizing electroplating.
- In another embodiment according to any of the previous embodiments, the polymer core is removed in a furnace.
- In another embodiment according to any of the previous embodiments, the polymer core is melted, disintegrated or evaporated in the furnace.
- In another embodiment according to any of the previous embodiments, the additive manufacturing process includes one of selective lithography analysis, selective laser sintering, fusion deposition of material or laminated object manufacturing.
- In another embodiment according to any of the previous embodiments, a computer model of the complex shaped component is utilized to control the additive manufacturing process to form the polymer core.
- In another embodiment according to any of the previous embodiments, dimensions of the polymer core are selected to be slightly smaller than dimensions of a desired final complex shaped part.
- In another featured embodiment, an integrally bladed rotor has a hub with an inner bore and an outer surface. A plurality of airfoils extend radially outwardly of the outer surface. The airfoils and hub have radially outer surfaces and axially outer surfaces formed of a relatively thin metal plate layer. There is metal powder within hollows defined axially and radially inwardly of the plate layer.
- In another embodiment according to the previous embodiment, the plate layer is a nickel based material.
- In another embodiment according to any of the previous embodiments, the metal powder is a nickel based material.
-
FIG. 1 illustrates an integrally bladed rotor. -
FIG. 2A schematically illustrates an example additive manufacturing machine, and further shows a first step in forming the integrally bladed rotor. -
FIG. 2B shows an intermediate step. -
FIG. 2C shows another intermediate step. -
FIG. 2D shows yet another intermediate step. -
FIG. 2E shows yet another intermediate step. -
FIG. 2F shows yet another manufacturing step. -
FIG. 2G shows yet another step. - An integrally
bladed rotor 20 is illustrated inFIG. 1 . As known, ahub 22 has anouter surface 24, and a plurality ofairfoils 26 extend radially outwardly of theouter surface 24. The integrally bladedrotor 20 has a very complex shape and raises challenges to manufacture. - This application is directed to a method of making such an integrally bladed rotor in a reliable and relatively simple manner compared to the prior art. While an integrally bladed rotor is specifically disclosed, any number of other complex shaped parts will benefit from the teachings of this application.
-
FIG. 2A shows an initial step. Acore 120 for forming an integrally bladed rotor is illustrated being only partially formed. A rapid prototyping process which utilizes additive manufacturing techniques is preferably utilized to form thecore 120 from an appropriate polymer. Asystem 30 is shown schematically forming thecore 120 from a polymer in such a rapid manufacturing process. Examples of such additive manufacturing processes include stereolithography (SLA), selective laser sintering, fused deposition modeling, laminated object manufacturing, or any other rapid manufacturing. As known,core 120 is being built up from layers. A CAD model of the desired integrally bladedrotor 20 can be utilized to drive these processes. -
FIG. 2B shows thefinal core 220. Core 220 is manufactured to be of the general exact shape of the final integrally bladedrotor 20 and hasouter surface 224,inner surface 222, andairfoils 226. -
FIG. 2C shows a subsequent step. A plating process (shown schematically at 34) is utilized to plate an appropriate metal for forming the integrally bladed rotor onto a polymer. The process deposits aplating core 220. In fact,FIG. 2C is an oversimplification, in that theplating 328 would typically only be found in the portions of theouter surface 224intermediate blades 226 on the core. Further, while ablade 226 is illustrated inFIG. 2C , in fact, thearea 327 would also receive the plating to form a lateral outer wall of the airfoils for the final integrally bladed rotor. The thickness of the plating may be exaggerated to show the plating layers. However, the purpose ofFIG. 2C is to make clear that the plating would cover thecore 220, and that there would be plated metal on outer surfaces of thecore 220 after the step 2C. - One metal which may be plated is an appropriate nickel or nickel alloy for forming the integrally bladed
rotor 20. Onepossible process 34 would be electroplating. The plating thickness should be controlled and selected to achieve a structurally sound configuration after the step 2D. - In step 2E, hollows are illustrated at
areas core 120 has been removed, as shown inFIG. 2D . In one example, the combined core and plating, as shown at 601, may be placed in afurnace 600 as shown schematically inFIG. 2D . The polymer forming thecore 220 may be melted, disintegrated, or evaporated in any known manner. - What is left is a
hollow configuration 320 as shown inFIG. 2E . Ahollow structure 320 incorporates platingportions hollow structure 320 arehollows 500 within each of the airfoils andhollows 501 within theportions 328 and between thesides 329. -
FIG. 2F shows a subsequent step. A metal powder fills the hollows. The metal powder is shown at 400 and 401, and may be deposited within the hollows in any known manner. Atool 610 is illustrated schematically delivering the metal powder into the hollows. The metal powder may be a nickel based powder that may be similar to the plating material. To ensure that powder fills in all areas of a hollow plated shell with complex shape configuration, a feeder spruce system may be included. - After step 2F, an integrally
bladed rotor 520 may be subjected to some finishing operation. As an example, a hotisostatic pressure operation 601 is illustrated inFIG. 2G and provides very high pressure to the integrallybladed rotor 520. As known, in theoperation 601, a container is typically filled with a fluid, and the fluid is pressurized to, in turn, pressurize theenclosed part 520. Powder out gassing may be utilized prior to the hot isostatic pressure operation. - Other finishing techniques, such as quasi-isostatic pressing or dynamic compaction can be utilized in place of the hot isostatic pressure.
- A worker on this art may recognize that the CAD model initially utilized to form the core at step 2A may be adjusted to account for material shrinkage which might occur due to the consolidation operation.
- An integrally
bladed rotor 520 has a hub with an inner bore 54 and anouter surface 522, and a plurality ofairfoils 523 extending outwardly of the outer surface. Theairfoils 523 and hub have radially outer surfaces and axially outer surfaces formed of a relatively thin metal plate layer. There is metal powder within hollows defined axially and radially inwardly of the plated layer. - The plate layer may be a nickel based material, and the metal powder may be a nickel based material.
- Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (15)
1. A method of forming a complex shaped part including the steps of:
(a) forming a polymer core by an additive manufacturing process;
(b) plating a metal about surfaces of said polymer core;
(c) removing said polymer core leaving hollows within a plating core; and
(d) depositing metal powder within said hollows.
2. The method as set forth in claim 1 , wherein a consolidation step occurs after the depositing of the metal powder into the hollows.
3. The method as set forth in claim 2 , wherein the consolidation process is a hot isostatic pressurization process.
4. The method as set forth in claim 1 , wherein said plating metal is a nickel based material.
5. The method as set forth in claim 4 , wherein said metal powder is also a nickel based material.
6. The method as set forth in claim 1 , wherein said complex shaped component is an integrally bladed rotor, and said integrally bladed rotor having a hub and radially outwardly extending airfoils with said hollows being formed in both said hub and said airfoils.
7. The method as set forth in claim 1 , wherein said plating occurs utilizing electroplating.
8. The method as set forth in claim 1 , wherein said polymer core is removed in a furnace.
9. The method of claim 8 , wherein said polymer core is melted, disintegrated or evaporated in said furnace.
10. The method as set forth in claim 1 , wherein said additive manufacturing process includes one of selective lithography analysis, selective laser sintering, fusion deposition of material or laminated object manufacturing.
11. The method of claim 1 wherein a computer model of the complex shaped component is utilized to control the additive manufacturing process to form the polymer core.
12. The method as set forth in claim 11 wherein dimensions of the polymer core are selected to be slightly smaller than dimensions of a desired final complex shaped part.
13. An integrally bladed rotor comprising:
a hub having an inner bore and an outer surface, and a plurality of airfoils extending radially outwardly of said outer surface, said airfoils and said hub having radially outer surfaces and axially outer surfaces formed of a relatively thin metal plate layer, and there being metal powder within hollows defined axially and radially inwardly of said plate layer.
14. The integrally bladed rotor as set forth in claim 13 wherein said plate layer is a nickel based material.
15. The integrally bladed rotor as set forth in claim 14 , wherein said metal powder is a nickel based material.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US13/718,134 US20140093384A1 (en) | 2012-09-28 | 2012-12-18 | Method of Manufacturing Complex Shaped Component |
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US201261706839P | 2012-09-28 | 2012-09-28 | |
US13/718,134 US20140093384A1 (en) | 2012-09-28 | 2012-12-18 | Method of Manufacturing Complex Shaped Component |
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US20140093384A1 true US20140093384A1 (en) | 2014-04-03 |
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US13/718,134 Abandoned US20140093384A1 (en) | 2012-09-28 | 2012-12-18 | Method of Manufacturing Complex Shaped Component |
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Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140003951A1 (en) * | 2012-07-02 | 2014-01-02 | Ronald R. Soucy | Super polish masking of integrally bladed rotor |
EP3187281A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
EP3187283A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
EP3187284A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
US9802288B2 (en) | 2014-06-16 | 2017-10-31 | United Technologies Corporation | Machining system having a tool for finishing airfoils |
US9857002B2 (en) | 2014-05-09 | 2018-01-02 | United Technologies Corporation | Fluid couplings and methods for additive manufacturing thereof |
US9938834B2 (en) | 2015-04-30 | 2018-04-10 | Honeywell International Inc. | Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof |
US10036254B2 (en) | 2015-11-12 | 2018-07-31 | Honeywell International Inc. | Dual alloy bladed rotors suitable for usage in gas turbine engines and methods for the manufacture thereof |
US20190024251A1 (en) * | 2017-07-18 | 2019-01-24 | Honeywell International Inc. | Additive-based electroforming manufacturing methods and metallic articles produced thereby |
US10294804B2 (en) | 2015-08-11 | 2019-05-21 | Honeywell International Inc. | Dual alloy gas turbine engine rotors and methods for the manufacture thereof |
US10328489B1 (en) | 2015-12-29 | 2019-06-25 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
US20190376199A1 (en) * | 2018-06-11 | 2019-12-12 | The Boeing Company | Rapid tooling using meltable substrate and electrodeposition |
US20200011455A1 (en) * | 2018-07-05 | 2020-01-09 | Unison Industries, Llc | Duct assembly and method of forming |
US10633731B2 (en) * | 2018-01-05 | 2020-04-28 | United Technologies Corporation | Method for producing enhanced fatigue and tensile properties in integrally bladed rotor forgings |
US10697305B2 (en) | 2016-01-08 | 2020-06-30 | General Electric Company | Method for making hybrid ceramic/metal, ceramic/ceramic body by using 3D printing process |
US10935037B2 (en) | 2018-01-05 | 2021-03-02 | Raytheon Technologies Corporation | Tool for simultaneous local stress relief of each of a multiple of linear friction welds of a rotor forging |
-
2012
- 2012-12-18 US US13/718,134 patent/US20140093384A1/en not_active Abandoned
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---|---|---|---|---|
US20140003951A1 (en) * | 2012-07-02 | 2014-01-02 | Ronald R. Soucy | Super polish masking of integrally bladed rotor |
US9193111B2 (en) * | 2012-07-02 | 2015-11-24 | United Technologies Corporation | Super polish masking of integrally bladed rotor |
US10683952B2 (en) | 2014-05-09 | 2020-06-16 | Raytheon Technologies Corporation | Fluid couplings and methods for additive manufacturing thereof |
US9857002B2 (en) | 2014-05-09 | 2018-01-02 | United Technologies Corporation | Fluid couplings and methods for additive manufacturing thereof |
US9802288B2 (en) | 2014-06-16 | 2017-10-31 | United Technologies Corporation | Machining system having a tool for finishing airfoils |
US9938834B2 (en) | 2015-04-30 | 2018-04-10 | Honeywell International Inc. | Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof |
US10294804B2 (en) | 2015-08-11 | 2019-05-21 | Honeywell International Inc. | Dual alloy gas turbine engine rotors and methods for the manufacture thereof |
US10036254B2 (en) | 2015-11-12 | 2018-07-31 | Honeywell International Inc. | Dual alloy bladed rotors suitable for usage in gas turbine engines and methods for the manufacture thereof |
US10328489B1 (en) | 2015-12-29 | 2019-06-25 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
EP3187283A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
EP3187284A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
EP3187281A1 (en) * | 2015-12-29 | 2017-07-05 | United Technologies Corporation | Dynamic bonding of powder metallurgy materials |
US10697305B2 (en) | 2016-01-08 | 2020-06-30 | General Electric Company | Method for making hybrid ceramic/metal, ceramic/ceramic body by using 3D printing process |
US20190024251A1 (en) * | 2017-07-18 | 2019-01-24 | Honeywell International Inc. | Additive-based electroforming manufacturing methods and metallic articles produced thereby |
US10900136B2 (en) * | 2017-07-18 | 2021-01-26 | Honeywell International Inc. | Additive-based electroforming manufacturing methods and metallic articles produced thereby |
US10633731B2 (en) * | 2018-01-05 | 2020-04-28 | United Technologies Corporation | Method for producing enhanced fatigue and tensile properties in integrally bladed rotor forgings |
US10935037B2 (en) | 2018-01-05 | 2021-03-02 | Raytheon Technologies Corporation | Tool for simultaneous local stress relief of each of a multiple of linear friction welds of a rotor forging |
US11448227B2 (en) | 2018-01-05 | 2022-09-20 | Raytheon Technologies Corporation | Tool for simultaneous local stress relief of each of a multiple of linear friction welds of a rotor forging |
US20190376199A1 (en) * | 2018-06-11 | 2019-12-12 | The Boeing Company | Rapid tooling using meltable substrate and electrodeposition |
US20200011455A1 (en) * | 2018-07-05 | 2020-01-09 | Unison Industries, Llc | Duct assembly and method of forming |
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