WO2019245563A1 - Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées - Google Patents

Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées Download PDF

Info

Publication number
WO2019245563A1
WO2019245563A1 PCT/US2018/038747 US2018038747W WO2019245563A1 WO 2019245563 A1 WO2019245563 A1 WO 2019245563A1 US 2018038747 W US2018038747 W US 2018038747W WO 2019245563 A1 WO2019245563 A1 WO 2019245563A1
Authority
WO
WIPO (PCT)
Prior art keywords
hole
preform
oversized
additive manufacturing
manufacturing process
Prior art date
Application number
PCT/US2018/038747
Other languages
English (en)
Inventor
Russell B. JONES
Original Assignee
Florida Turbine Technologies, Inc.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Florida Turbine Technologies, Inc. filed Critical Florida Turbine Technologies, Inc.
Priority to PCT/US2018/038747 priority Critical patent/WO2019245563A1/fr
Publication of WO2019245563A1 publication Critical patent/WO2019245563A1/fr

Links

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
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • 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
    • B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
    • B22F2005/103—Cavity made by removal of insert
    • 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
    • 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
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • 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
    • B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
    • 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
    • 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/234—Laser welding
    • 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the present invention relates generally to additive manufactured metal parts
  • Turbine airfoils exposed to the highest gas stream flow must be cooled to prevent damage.
  • Turbine airfoils that require cooling air flow are typically formed using an investment casting process with a ceramic core that represents the
  • the new metal additive manufacturing process is being used to form complex parts such as turbine airfoils with internal cooling features where the entire part is printed by a metal printing process such as direct metal laser sintering (DMLS).
  • a metal printing process such as direct metal laser sintering (DMLS).
  • FIG. 1 shows a side view of a small film cooling hole printed using the metal additive manufacturing process of the prior art.
  • FIG. 2 shows a front view of the printed film cooling hole of FIG. 1 with a wide variation in tolerance or relatively large surface defects.
  • a part such as an air cooled turbine airfoil with a film cooling hole, where the part is formed by a metal additive manufacturing process with an oversized feature such as a hole, and where the oversized feature is formed with a normal size by inserting a preform having the normal size to the part and secured to the part, and where the preform is removed such that the normal size feature is left in the part.
  • the part can be an air cooled turbine airfoil and the feature is a film cooling hole.
  • the airfoil is formed from the metal additive manufacturing process with an oversized hole.
  • a preform made from a refractory material is secured in the oversized hole using a braze or weld material that also fills the gap between the oversized hole and the preform.
  • the preform has a shape of the normal size film cooling hole.
  • the refractory alloy preform is removed, such as by exposure to oxygen at temperatures where the refractory alloy sublimates, and the normal sized film cooling hole is thus formed in the wall.
  • the hole can be a spiral or helical shaped hole, a curved hole, a hole with a diffusion opening, a slot for a seal, and even a threaded hole for a fastener.
  • FIG. 1 shows a cross-section side view of a film cooling hole formed using a metal additive manufacturing process of the prior art
  • FIG. 2 shows a front view of the printed film cooling hole of FIG. 1 with a large variation in the hole surface
  • FIG. 3 shows a cross-section side view of a film cooling hole formed using the metal additive manufacturing process of the present invention with a refractory alloy hole replica in place
  • FIG. 4 shows a cross-section side view of the film cooling hole of the present invention with the refractory hole replica removed;
  • FIG. 5 shows an embodiment of the present invention in which a double conical shaped preform is used
  • FIG. 6 shows an embodiment of the present invention in which a diffusion hole shaped preform is used
  • FIG. 7 shows an embodiment of the present invention in which a helical shaped preform is used
  • FIG. 8 shows an embodiment of the present invention in which a curved shaped preform is used
  • FIG. 9 shows an embodiment of the present invention in which a slot shaped preform is used.
  • FIG. 10 shows an embodiment of the present invention in which a threaded shaped preform is used.
  • the present invention is an apparatus and a process to form a metal additive manufactured (3D printed) part with a feature having a detail that cannot be formed by the metal printing process alone.
  • FIGS. 1 and 2 show a part with a hole, such as that in a turbine airfoil having a film cooling air hole in which the part and the hole are formed as a single piece using the metal printing process.
  • the hole varies widely in the tolerance and surface finish due to limitations in the metal additive manufacturing process.
  • the features such as the film cooling hole can be formed with fine details like that produced in the prior art metal casting process. Defects such as splatter can adhere unwanted particles to the desired printed geometry such as a smooth wall surface or hole.
  • FIG. 3 shows a first embodiment of the present invention in which a film cooling hole is formed in a part such as a turbine airfoil wall.
  • the part in which the hole is to be formed can be cast or printed in which the hole is formed oversized.
  • the manufactured part (for example, a turbine airfoil wall) 11 is formed with an oversized hole.
  • a preform 12 having a finished shape of the feature to be formed, such as in this case the film cooling hole, is secured in place within the oversized hole such as by a braze or a weld material 13.
  • the preform 12 is formed from a refractory material that can be easily removed after the braze or weld material 13 has been formed around the preform 12.
  • the braze or welding would be performed in a reducing gas (reactive gas that removes free oxygen), an inert gas, or vacuum environment so as to prevent the oxidation of the refractory alloy.
  • the refractory material can be alloys of molybdenum, tungsten, niobium, or other materials that can be easily removed by methods such as by sublimation to leave a hole having the desired shape.
  • the material may include non-refractory material, but the object of the preform material is that substantially all of the perform material can be removed by rapid oxidation/sublimation at moderate elevated temperatures so that a refined hole is left in the part of wall 11 without any surface defects like those found in the metal additive manufacturing process alone.
  • the film cooling hole 14 has a much lower tolerance than the prior art film cooling hole of figures 1 and 2 because of the use of the preform 12.
  • the resulting hole is referred to as being a normal sized hole.
  • FIG. 5 shows an embodiment of the present invention where a double conical shaped hole can be formed using a preform 21 having this finished shape that is secured into the oversized hole by a braze or weld material 13 formed in the wall or part 11.
  • Figure 6 shows an embodiment of the present invention where the perform 22, and therefore the hole formed, has a diffusion cooling hole shape.
  • Figure 7 shows an embodiment of the present invention where the perform 23, and therefore the hole formed, has a helical cooling hole shape.
  • Figure 8 shows an embodiment of the present invention where the perform 24, and therefore the hole formed, has a curved cooling hole shape.
  • Figure 9 shows an embodiment of the present invention where the wall of the manufactured part 11 defines a slot shape and the perform 25 has a shape matching the slot shape (that is, the perform 25 is sized and configured to be at least partially received within the slot shape) such that the hole formed has a slot shape.
  • Figure 10 shows an embodiment of the present invention where the perform 26, and therefore the hole formed, has a threaded shape such that a screw or bolt can be inserted and rotated therein.
  • the apparatus and process of the present invention utilizes an additive manufactured part 11 created with an oversized hole in which a refractory material having a desired finished shape (the preform 22) is inserted and the gap(s) between the preform 22 and the manufactured part 11 filled by welding or braze filler material.
  • the braze alloy is used to create the refined hole feature.
  • a refractory material 22 sized to the desired shape of the final hole is inserted into the oversized hole in the part 11 and the gap filled with the braze alloy or weld material.
  • the refractory hole preform 22 could have the braze alloy pre-applied to the replica or preform before it is inserted into the part 11.
  • the brazing thermal cycle would be performed in an insert gas environment, vacuum, or reducing gas environment, each to prevent the oxidation of the refractory alloy.
  • the braze furnace could be backfilled with air to allow the refractory alloy to oxidize (sublimate) leaving the clear hole as the result interface of the removed refractory and the braze filler.
  • the apparatus and process of the present invention can be used to produce a variety of features such as slots, channels, recesses, cooling holes, or other features that cannot be printed with the desired low tolerance.
  • the surface finish within the final refined part with the hole refinement process applied would be reflective or the initial refractory form.
  • tapered cooling holes could be produced to allow for acceleration, diffusion, or metering of the cooling air flow through the axial length of the hole.
  • Curved holes or helical shaped holes can also be produced with the high tolerance finish.
  • the apparatus and process of the present invention is applicable to additive manufactured parts and additionally to conventional manufactured parts such as machined from bar or plate stock, casting (investment cast, sand cast, centrifugal cast), and machined forgings.
  • a part can be formed unfinished using a casting process (for example) and then finished using the metal printing process with the preform of the present invention. Refurbishment of the parts such as gas turbine parts, hot gas path parts, blades, vanes, heat shields could be restored and improved by the use of this process.
  • Features could include slots, holes, threads, and recesses.
  • the preform can be made from a ceramic material instead of a refractory material, and where the ceramic preform can be removed by chemical leaching to produce the desired feature such as a hole.
  • the desired feature such as a hole.
  • an oversized feature such as a hole is still formed, but the preform is not a refractory material but a ceramic material.
  • a process for forming a hole in a part formed by a metal additive manufacturing process comprises the steps of: forming a part with an oversized hole using a metal additive manufacturing process; inserting a preform having a shape of a normal sized hole into the oversized hole of the part; securing the preform in the oversized hole with a material that fills a gap between the oversized hole and the preform; and removing the preform so that the normal sized hole is formed in the part.
  • the part is a turbine airfoil; and the normal sized hole is a film cooling hole.
  • the preform is formed of a refractory material that can be removed by exposure to oxygen.
  • the process further comprises the step of: securing the preform to the oversized hole with a braze material or a weld material.
  • the normal sized hole is one of a helical shaped hole, a curved hole, a slot for a seal, and a threaded hole for a fastener.
  • the part is a turbine airfoil; and the normal sized hole is a film cooling hole with a diffusion opening.
  • the metal additive manufacturing process is a direct metal laser sintering process or an electron beam melting process.
  • the preform is formed substantially from at least one of Molybdenum, Tungsten, and Niobium.
  • an air cooled turbine airfoil that comprises a plurality of film cooling holes.
  • a part is formed by a metal additive manufacturing process, the part including a hole having a surface with a low tolerance that cannot be formed from the metal additive manufacturing process by itself, the part comprising: a wall having an oversized hole formed from a metal additive manufacturing process; a preform having a shape of a normal sized hole; the preform being formed from a refractory material that can be removed by exposure to oxygen; and at least one of a braze material and a weld material filling a gap between the oversized hole and the preform to secure the preform to the oversized hole, exposure of the preform to oxygen removing the preform from the oversized hole and leaving the normal sized hole within the wall.
  • the part after exposure of the preform to oxygen such that the preform is removed, the part is an air cooled turbine airfoil; and the hole is a film cooling hole.
  • the normal sized hole is one of a helical shaped hole, a curved hole, a slot for a seal, and a threaded hole for a fastener.
  • the preform is formed substantially from at least one of Molybdenum, Tungsten, and Niobium.
  • the part is a turbine airfoil; and the normal sized hole is a film cooling hole with a diffusion opening.
  • the preform is removable by exposure to oxygen.
  • a process of forming an air cooled turbine airfoil from a metal additive manufacturing process comprising the steps of: forming an air cooled turbine airfoil with a plurality of film cooling holes from an additive manufacturing process in which the film cooling holes are formed oversized; inserting a preform having a shape of a non-oversized film cooling hole into each of the oversized film cooling holes; securing the preform to each of the oversized film cooling holes with a material having a melting temperature of at least as high as the material of which the air cooled turbine airfoil is made from; and removing the preform from each of the oversize film cooling holes to leave non-oversized film cooling holes in the air cooled turbine airfoil.
  • the process further comprises the step of: securing the preform to the oversized hole with at least one of a braze material and a weld material.
  • the preform is formed of a refractory material that can be removed by exposure to oxygen.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)

Abstract

La présente invention concerne une pièce formée au moyen d'un procédé de fabrication additive métallique, tel qu'un profil aérodynamique de turbine ayant une caractéristique surdimensionnée telle qu'un trou surdimensionné, le trou surdimensionné étant rempli avec une préforme ayant une forme d'un trou de taille normale et fixé à l'intérieur de la pièce au moyen d'un matériau de brasure ou de soudure, et où la préforme est retirée pour laisser dans la pièce le trou de taille normale. La préforme est constituée d'un matériau réfractaire qui peut être retiré de la pièce par exposition à l'oxygène.
PCT/US2018/038747 2018-06-21 2018-06-21 Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées WO2019245563A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2018/038747 WO2019245563A1 (fr) 2018-06-21 2018-06-21 Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2018/038747 WO2019245563A1 (fr) 2018-06-21 2018-06-21 Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées

Publications (1)

Publication Number Publication Date
WO2019245563A1 true WO2019245563A1 (fr) 2019-12-26

Family

ID=62976132

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2018/038747 WO2019245563A1 (fr) 2018-06-21 2018-06-21 Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées

Country Status (1)

Country Link
WO (1) WO2019245563A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6214248B1 (en) * 1998-11-12 2001-04-10 General Electric Company Method of forming hollow channels within a component
EP1306147A1 (fr) * 2001-10-24 2003-05-02 United Technologies Corporation Noyau destiné au moulage de précision
US20150037498A1 (en) * 2013-08-01 2015-02-05 Siemens Energy, Inc. Methods and preforms to mask holes and support open-substrate cavities during laser cladding
US10006293B1 (en) * 2015-07-22 2018-06-26 Florida Turbine Technologies, Inc. Apparatus and process for refining features in an additive manufactured part

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6214248B1 (en) * 1998-11-12 2001-04-10 General Electric Company Method of forming hollow channels within a component
EP1306147A1 (fr) * 2001-10-24 2003-05-02 United Technologies Corporation Noyau destiné au moulage de précision
US20150037498A1 (en) * 2013-08-01 2015-02-05 Siemens Energy, Inc. Methods and preforms to mask holes and support open-substrate cavities during laser cladding
US10006293B1 (en) * 2015-07-22 2018-06-26 Florida Turbine Technologies, Inc. Apparatus and process for refining features in an additive manufactured part

Similar Documents

Publication Publication Date Title
US10006293B1 (en) Apparatus and process for refining features in an additive manufactured part
EP3429778B1 (fr) Procédé de fabrication d'éléments caractéristiques perfectionnés dans un noyau pour la coulée
EP1775054B1 (fr) Procédé de fermeture d'une ouverture dans une aube de turbine creuse en super-alliage à base de nickel
US9835035B2 (en) Cast-in cooling features especially for turbine airfoils
US10357819B2 (en) Investment casting of hollow components
US20180304345A1 (en) Additively manufactured casting articles for manufacturing gas turbine engine parts
US7687021B2 (en) Method of fabricating a casing for turbine stator
US8196640B1 (en) Self supporting core-in-a-core for casting
US20170306766A1 (en) Turbine blade having an inner module and method for producing a turbine blade
US9908175B2 (en) Die casting system and method utilizing sacrificial core
JP2007314879A (ja) 金属複合材発泡体構成部品を製造する方法及び金属複合材構成部品のためのプリフォーム
JP2011509185A (ja) タービンエアフォイルの鋳造方法
US20070261811A1 (en) Process for manufacturing ceramic cores for turbomachine blades
US8757243B2 (en) Shot tube plunger for a die casting system
US20110299999A1 (en) Multi-component assembly casting
WO2019171265A1 (fr) Procédé de production en série de composants métalliques monolithiques structuraux pour moteurs à turbine
JP6918507B2 (ja) 熱間等方圧加圧法により第１の金属部品の周囲に形成された第２の金属部品を用いた鋳造
US20160245519A1 (en) Panel with cooling holes and methods for fabricating same
WO2019245563A1 (fr) Procédé d'affinage de caractéristiques dans une pièce fabriquée par fabrication additive et pièce fabriquée ayant des caractéristiques affinées
EP3360624A1 (fr) Tube d'injection à cristal unique asymétrique pour coulée sous pression à haute température
Laney et al. Evaluation of various methods for manufacturing one piece, small tip opening centrifugal compressor impellers
KR100929451B1 (ko) 주조 방법 및 주물 부품
EP3626932A1 (fr) Composant refroidi de moteur à turbine à gaz, et moule de moulage à la cire perdue et procédé de fabrication associés
US10695826B2 (en) Apparatus and method for investment casting core manufacture
EP3433036B1 (fr) Procédé de fabrication d'un noyau hybridé avec un moulage en saillie dans des caractéristiques de refroidissement pour un moulage d'investissement

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18743122

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18743122

Country of ref document: EP

Kind code of ref document: A1