US20160158840A1 - Use of spark plasma sintering for manufacturing superalloy compound components - Google Patents

Use of spark plasma sintering for manufacturing superalloy compound components Download PDF

Info

Publication number
US20160158840A1
US20160158840A1 US14/088,791 US201314088791A US2016158840A1 US 20160158840 A1 US20160158840 A1 US 20160158840A1 US 201314088791 A US201314088791 A US 201314088791A US 2016158840 A1 US2016158840 A1 US 2016158840A1
Authority
US
United States
Prior art keywords
superalloy
component
spark plasma
plasma sintering
compound
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
Application number
US14/088,791
Inventor
Marco Cologna
Anand A. Kulkarni
Stefan Lampenscherf
Gia Khanh Pham
Cora Schillig
Steffen Walter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to US14/088,791 priority Critical patent/US20160158840A1/en
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: COLOGNA, MARCO, LAMPENSCHERF, STEFAN, WALTER, STEFFEN
Assigned to SIEMENS ENERGY, INC. reassignment SIEMENS ENERGY, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SCHILLIG, CORA
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS ENERGY, INC.
Assigned to SIEMENS CORPORATION reassignment SIEMENS CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KULKARNI, ANAND A, PHAM, GIA KHANH
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS CORPORATION
Priority to PCT/US2014/067086 priority patent/WO2015122953A2/en
Publication of US20160158840A1 publication Critical patent/US20160158840A1/en
Abandoned legal-status Critical Current

Links

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
    • B22F3/10—Sintering only
    • B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
    • B22F1/0003—
    • 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
    • B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
    • B22F1/09—Mixtures of metallic powders
    • 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
    • B22F7/062—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 involving the connection or repairing of preformed parts
    • 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
    • B22F3/10—Sintering only
    • B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
    • B22F2003/1051—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding by electric discharge
    • 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
    • B22F2201/00—Treatment under specific atmosphere
    • B22F2201/20—Use of vacuum
    • 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
    • B22F2202/00—Treatment under specific physical conditions
    • B22F2202/13—Use of plasma
    • 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
    • B22F2301/00—Metallic composition of the powder or its coating
    • B22F2301/15—Nickel or cobalt
    • 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
    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0433—Nickel- or cobalt-based alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/045—Alloys based on refractory metals

Definitions

  • the invention provides a method of manufacturing a superalloy compound component.
  • Nickel-based superalloys are commonly used for a wide range of components that have to operate under high mechanical stress while withstanding harsh operating conditions. For this reason Nickel-based superalloys are a preferred material for hot gas path components of gas turbines such as discs, casings, vane segments and turbine blades. Some of these superalloys, particularly the highly alloyed materials with a high content of Al and Ti are very difficult to weld. The same is true for refractory metals which are also very difficult to weld. In the case of the Nickel-based superalloys the high content of Al and Ti will cause a precipitation of hardened Gamma-prime phase and an increased crack susceptibility of the parts during the welding process.
  • the invention provides a method of manufacturing a superalloy compound component having a first component portion primarily consisting of a first superalloy and a second component portion primarily consisting of a second superalloy or of a refractory metal.
  • the method includes using Spark Plasma Sintering for forming the superalloy compound component.
  • Spark Plasma Sintering is a sintering process that is also known as Field Assisted Sintering Technique or Pulsed Electric Current Sintering.
  • Spark Plasma Sintering a pulsed or continuous current is led through compacted metal powder contained within a mould.
  • the heat produced by the current causes sintering of the metal powder achieving densification close to theoretical maximum density but at lower sintering temperatures compared to conventional sintering processes.
  • Spark Plasma Sintering has an advantage that the heat is generated uniformly within the compacted metal powder which allows for very high heating and cooling rates. For this reason Spark Plasma Sintering is a very fast sintering process.
  • the invention is based on the idea that Spark Plasma Sintering may be used for joining components of the same or different Nickel-based superalloys or refractory metals which may not be joined by welding due to the abovementioned difficulties.
  • the invention proposes using a sintering process for a different object, i.e. joining two components to produce a superalloy compound component rather than producing a component from metal powder as is known in the art.
  • the method of the invention further comprises providing a mould having first and second mould portions each defining an outer shape of the first component portion and the second component portion, respectively. Then a first metal powder primarily consisting of the first superalloy is arranged in the first mould portion and a second metal powder primarily consisting of the second superalloy or of the refractory metal is arranged in the second mould portion. Finally the superalloy compound component is integrally formed by Spark Plasma Sintering the first and second metal powders in the mould.
  • This is especially useful for producing superalloy compound components where different segments of the superalloy compound component are formed of different superalloy materials or refractory metals which may not be joined by welding techniques. This may be useful for manufacturing specific components such as turbine blades of a gas turbine using different superalloys for different parts of the turbine blade in accordance with the expected mechanical and chemical stress to be experienced by the respective part of the turbine blade in operation of the gas turbine.
  • the second approach is referred to herein as diffusion bonding.
  • the method of the invention may further comprise providing a first component primarily consisting of the first superalloy and a second component primarily consisting of the second superalloy or of the refractory metal.
  • the first and second components are arranged as to contact each other before using Spark Plasma Sintering for forming the superalloy compound component.
  • the first component forms the first component portion and the second component forms the second component portion of the superalloy compound component.
  • the diffusion bonding of the invention allows for firmly joining a first component to a second component which would normally be achieved by welding if it were not for the materials that cannot be welded.
  • the first and second components are provided as macroscopic components and not in the form of powders which then are solidified.
  • the Spark Plasma Sintering process known in the art may be used for an entirely different object, i.e. for joining two construction components to each other.
  • the method of the invention may further comprise providing a layer of a superalloy powder in a contact region where the first component contacs the second component.
  • This superalloy powder will solidify during the Spark Plasma Sintering thereby supporting the diffusion bonding of the two components.
  • the superalloy powder may primarily consists of either one of the first superalloy, the second superalloy or a mixture of the first superalloy and the second superalloy.
  • the Spark Plasma Sintering is carried out under vacuum.
  • the Spark Plasma Sintering may include a step of pressing the first component portion and the second component portion. Suitable pressures may be in the range of one to fourty MPa (Megapascal).
  • the Spark Plasma Sintering may include heating the first component portion and the second component portion. The components may be heated to a temperature of 1000 to 1200 degrees Celsius. Suitable heating and cooling rates may be in the range of 20 to 200 Kelvin per minute. The time required for bonding will be typically in the range of 3 to 60 minutes resulting in a total time for
  • Spark Plasma Sintering of approximately 2 to 3 hours including heating, bonding and cooling.
  • the current used for the Spark Plasma Sintering may be provided in a pulsed or continuous mode.
  • the superalloy compound component is a gas turbine component.
  • At least one of the first and the second superalloys may be a Ni-based superalloy.
  • This Ni-based superalloy may comprise at least one of Al and Ti.
  • the inventive method is especially useful for joining components consisting of different superalloys.
  • the second superalloy may be different from the first superalloy.
  • FIG. 1 a cross sectional view of an example superalloy compound component using the method of the invention.
  • FIG. 1 shows a cross sectional view of an example superalloy compound component formed using the method of the invention.
  • two buttons made from Nickel-based superalloys were joined using Spark Plasma Sintering in accordance with the invention.
  • One button was made from CM 247, the other from Rene 80.
  • the two buttons were joined firmly to each other illustrating the superior bonding of two usually unweldable parts.
  • a bond line between the two materials having a horizontal orientation is indicated. This bond line can hardly be seen thus underlining the quality of the joining of the two buttons.
  • the method of the invention can be used for joining components of the same or different superalloys or of refractory metals.
  • the method of the invention therefore allows for production of superalloy compound components from two or more components thereby reducing the cost of production and repair of components that otherwise have to be produced monolithically. This makes the invention especially useful in the field of gas turbine production and repair.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

A method of manufacturing a superalloy compound component is provided. The component includes a first component portion primarily consisting of a first superalloy and a second component portion primarily consisting of a second superalloy or of a refractory metal. The method includes using Spark Plasma Sintering for forming the superalloy compound component.

Description

    FIELD OF TECHNOLOGY
  • The invention provides a method of manufacturing a superalloy compound component.
    • TECHNICAL BACKGROUND
  • Due to their superior properties, high temperature Nickel-based superalloys are commonly used for a wide range of components that have to operate under high mechanical stress while withstanding harsh operating conditions. For this reason Nickel-based superalloys are a preferred material for hot gas path components of gas turbines such as discs, casings, vane segments and turbine blades. Some of these superalloys, particularly the highly alloyed materials with a high content of Al and Ti are very difficult to weld. The same is true for refractory metals which are also very difficult to weld. In the case of the Nickel-based superalloys the high content of Al and Ti will cause a precipitation of hardened Gamma-prime phase and an increased crack susceptibility of the parts during the welding process. The three main types of cracking and defects are solidification cracking, grain boundary liquation cracking and strain age cracking Hence, welding of highly strengthened Nickel-based superalloys like PWA 1483, Rene 80, CM 247, IN 738 and IN 939 shows many quality problems. In view of the aforegoing it is an object of the invention to provide a method of manufacturing a superalloy compound component.
    • SUMMARY OF THE INVENTION
  • In order to solve the abovementioned object, the invention provides a method of manufacturing a superalloy compound component having a first component portion primarily consisting of a first superalloy and a second component portion primarily consisting of a second superalloy or of a refractory metal. According to the invention the method includes using Spark Plasma Sintering for forming the superalloy compound component.
  • Spark Plasma Sintering is a sintering process that is also known as Field Assisted Sintering Technique or Pulsed Electric Current Sintering. In Spark Plasma Sintering a pulsed or continuous current is led through compacted metal powder contained within a mould. The heat produced by the current causes sintering of the metal powder achieving densification close to theoretical maximum density but at lower sintering temperatures compared to conventional sintering processes. Spark Plasma Sintering has an advantage that the heat is generated uniformly within the compacted metal powder which allows for very high heating and cooling rates. For this reason Spark Plasma Sintering is a very fast sintering process.
  • The invention is based on the idea that Spark Plasma Sintering may be used for joining components of the same or different Nickel-based superalloys or refractory metals which may not be joined by welding due to the abovementioned difficulties. Thus, the invention proposes using a sintering process for a different object, i.e. joining two components to produce a superalloy compound component rather than producing a component from metal powder as is known in the art.
  • This idea encloses two main approaches the first of which will be referred to herein as powder metallurgy. According to this approach the method of the invention further comprises providing a mould having first and second mould portions each defining an outer shape of the first component portion and the second component portion, respectively. Then a first metal powder primarily consisting of the first superalloy is arranged in the first mould portion and a second metal powder primarily consisting of the second superalloy or of the refractory metal is arranged in the second mould portion. Finally the superalloy compound component is integrally formed by Spark Plasma Sintering the first and second metal powders in the mould. This is especially useful for producing superalloy compound components where different segments of the superalloy compound component are formed of different superalloy materials or refractory metals which may not be joined by welding techniques. This may be useful for manufacturing specific components such as turbine blades of a gas turbine using different superalloys for different parts of the turbine blade in accordance with the expected mechanical and chemical stress to be experienced by the respective part of the turbine blade in operation of the gas turbine.
  • The second approach is referred to herein as diffusion bonding. According to this approach the method of the invention may further comprise providing a first component primarily consisting of the first superalloy and a second component primarily consisting of the second superalloy or of the refractory metal. The first and second components are arranged as to contact each other before using Spark Plasma Sintering for forming the superalloy compound component. In this way the first component forms the first component portion and the second component forms the second component portion of the superalloy compound component. Thus, the diffusion bonding of the invention allows for firmly joining a first component to a second component which would normally be achieved by welding if it were not for the materials that cannot be welded. Contrary to the first inventive approach the first and second components are provided as macroscopic components and not in the form of powders which then are solidified. Thus, the Spark Plasma Sintering process known in the art may be used for an entirely different object, i.e. for joining two construction components to each other.
  • To support diffusion bonding of the two components, the method of the invention may further comprise providing a layer of a superalloy powder in a contact region where the first component contacs the second component. This superalloy powder will solidify during the Spark Plasma Sintering thereby supporting the diffusion bonding of the two components. The superalloy powder may primarily consists of either one of the first superalloy, the second superalloy or a mixture of the first superalloy and the second superalloy.
  • Preferably the Spark Plasma Sintering is carried out under vacuum. Furthermore, the Spark Plasma Sintering may include a step of pressing the first component portion and the second component portion. Suitable pressures may be in the range of one to fourty MPa (Megapascal). The Spark Plasma Sintering may include heating the first component portion and the second component portion. The components may be heated to a temperature of 1000 to 1200 degrees Celsius. Suitable heating and cooling rates may be in the range of 20 to 200 Kelvin per minute. The time required for bonding will be typically in the range of 3 to 60 minutes resulting in a total time for
  • Spark Plasma Sintering of approximately 2 to 3 hours including heating, bonding and cooling. The current used for the Spark Plasma Sintering may be provided in a pulsed or continuous mode.
  • Preferably the superalloy compound component is a gas turbine component. At least one of the first and the second superalloys may be a Ni-based superalloy. This Ni-based superalloy may comprise at least one of Al and Ti. The inventive method is especially useful for joining components consisting of different superalloys. Thus, the second superalloy may be different from the first superalloy.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 a cross sectional view of an example superalloy compound component using the method of the invention.
    •  EXEMPLARY EMBODIMENT
  • FIG. 1 shows a cross sectional view of an example superalloy compound component formed using the method of the invention. In this example two buttons made from Nickel-based superalloys were joined using Spark Plasma Sintering in accordance with the invention. One button was made from CM 247, the other from Rene 80. The two buttons were joined firmly to each other illustrating the superior bonding of two usually unweldable parts. In the FIGURE a bond line between the two materials having a horizontal orientation is indicated. This bond line can hardly be seen thus underlining the quality of the joining of the two buttons. The method of the invention can be used for joining components of the same or different superalloys or of refractory metals. The method of the invention therefore allows for production of superalloy compound components from two or more components thereby reducing the cost of production and repair of components that otherwise have to be produced monolithically. This makes the invention especially useful in the field of gas turbine production and repair.
  • Although the invention has been shown and described with respect to exemplary embodiments thereof, various other changes, omissions, and additions in form and detail thereof may be made therein without departing from the spirit and scope of the invention.
  • While the invention has been described in connection with a preferred embodiment, it is not intended to limit the scope of the invention to the particular form set forth, but on the contrary, it is intended to cover such alternatives, modifications, and equivalents as may be included within the scope of the invention as defined by the appended claims.

Claims (11)

We claim:
1. A method of manufacturing a superalloy compound component, comprising:
providing a first component portion primarily consisting of a first superalloy and a second component portion primarily consisting of a second superalloy or of a refractory metal; and
using Spark Plasma Sintering for forming the superalloy compound component.
2. The method of claim 1, further comprising:
providing a mould having first and second mould portions each defining an outer shape of the first component portion and the second component portion, respectively, arranging a first metal powder primarily consisting of the first superalloy in the first mould portion, arranging a second metal powder primarily consisting of the second superalloy or of the refractory metal in the second mould portion, and integrally forming the superalloy compound component by Spark Plasma Sintering the first and second metal powders in the mould.
3. The method of claim 1, further comprising:
providing a first component primarily consisting of the first superalloy and a second component primarily consisting of the second superalloy or of the refractory metal, arranging the first and second components to contact each other before using Spark Plasma Sintering for forming the superalloy compound component,
wherein the first component forms the first component portion, and
wherein the second component forms the second component portion of the superalloy compound component.
4. The method of claim 3, further comprising:
providing a layer of a superalloy powder in a contact region where the first component contacts the second component.
5. The method of claim 4, wherein the superalloy powder primarily consists of either one of the first superalloy, the second superalloy or a mixture of the first superalloy and the second superalloy.
6. The method of claim 1, wherein the Spark Plasma Sintering is carried out under vacuum.
7. The method of claim 1, wherein the Spark Plasma Sintering includes pressing the first component portion and the second component portion.
8. The method of claim 1, wherein the superalloy compound component is a gas turbine component.
9. The method of claim 1, wherein at least one of the first and the second superalloys is a Ni-based superalloy.
10. The method of claim 9, wherein the Ni-based superalloy comprises at least one of Al and Ti.
11. The method of claim 1, wherein the second superalloy is different from the first superalloy.
US14/088,791 2013-11-25 2013-11-25 Use of spark plasma sintering for manufacturing superalloy compound components Abandoned US20160158840A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US14/088,791 US20160158840A1 (en) 2013-11-25 2013-11-25 Use of spark plasma sintering for manufacturing superalloy compound components
PCT/US2014/067086 WO2015122953A2 (en) 2013-11-25 2014-11-24 Use of spark plasma sintering for manufacturing superalloy compound components

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/088,791 US20160158840A1 (en) 2013-11-25 2013-11-25 Use of spark plasma sintering for manufacturing superalloy compound components

Publications (1)

Publication Number Publication Date
US20160158840A1 true US20160158840A1 (en) 2016-06-09

Family

ID=53298582

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/088,791 Abandoned US20160158840A1 (en) 2013-11-25 2013-11-25 Use of spark plasma sintering for manufacturing superalloy compound components

Country Status (2)

Country Link
US (1) US20160158840A1 (en)
WO (1) WO2015122953A2 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11167348B2 (en) 2017-06-28 2021-11-09 Rolls-Royce Corporation Joining metal or alloy components using electric current
US11318553B2 (en) 2019-01-04 2022-05-03 Raytheon Technologies Corporation Additive manufacturing of laminated superalloys
CN114829062A (en) * 2019-12-20 2022-07-29 赛峰集团 Solution for manufacturing integral bladed disk
US20230151738A1 (en) * 2021-06-18 2023-05-18 Raytheon Technologies Corporation Hybrid bonded configuration for blade outer air seal (boas)
US20230323784A1 (en) * 2021-06-18 2023-10-12 Raytheon Technologies Corporation Advanced passive clearance control (apcc) control ring produced by field assisted sintering technology (fast)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3575016A1 (en) * 2018-06-01 2019-12-04 Siemens Aktiengesellschaft Improvements relating to the manufacture of superalloy components
US20220403742A1 (en) * 2021-06-18 2022-12-22 Raytheon Technologies Corporation Hybrid superalloy article and method of manufacture thereof
EP4105444A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Joining individual turbine vanes with field assisted sintering technology (fast)
EP4105438A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Bonding method for the repair of a superalloy article

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6384365B1 (en) * 2000-04-14 2002-05-07 Siemens Westinghouse Power Corporation Repair and fabrication of combustion turbine components by spark plasma sintering
US20120000072A9 (en) * 2008-09-26 2012-01-05 Morrison Jay A Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components
FR2972379B1 (en) * 2011-03-07 2014-01-17 Snecma METHOD FOR LOCALLY RECHARGING DAMAGED THERMOMECHANICAL PIECE AND PART THEREFORE PRODUCED, IN PARTICULAR TURBINE PIECE
FR2981590B1 (en) * 2011-10-21 2014-06-06 Snecma METHOD OF MAKING A SINTERED PREFORM AND ASSEMBLING THE PREFORM ON A WORKPIECE

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11167348B2 (en) 2017-06-28 2021-11-09 Rolls-Royce Corporation Joining metal or alloy components using electric current
US11179776B2 (en) 2017-06-28 2021-11-23 Rolls-Royce Corporation Joining metal or alloy components using electric current
US11318553B2 (en) 2019-01-04 2022-05-03 Raytheon Technologies Corporation Additive manufacturing of laminated superalloys
CN114829062A (en) * 2019-12-20 2022-07-29 赛峰集团 Solution for manufacturing integral bladed disk
US20230151738A1 (en) * 2021-06-18 2023-05-18 Raytheon Technologies Corporation Hybrid bonded configuration for blade outer air seal (boas)
US20230323784A1 (en) * 2021-06-18 2023-10-12 Raytheon Technologies Corporation Advanced passive clearance control (apcc) control ring produced by field assisted sintering technology (fast)

Also Published As

Publication number Publication date
WO2015122953A3 (en) 2015-10-29
WO2015122953A2 (en) 2015-08-20

Similar Documents

Publication Publication Date Title
US20160158840A1 (en) Use of spark plasma sintering for manufacturing superalloy compound components
CA2848672C (en) Configuration for joining a ceramic thermal insulating material to a metallic structure
US7722330B2 (en) Rotating apparatus disk
EP1775054B1 (en) Weld closure of through-holes in a nickel-base superalloy hollow airfoil
US6384365B1 (en) Repair and fabrication of combustion turbine components by spark plasma sintering
EP2790858B1 (en) Method for additively manufacturing an article made of a difficult-to-weld material
US9221101B2 (en) Process for local repair of a damaged thermomechanical part and part thus produced, in particular a turbine part
US7541561B2 (en) Process of microwave heating of powder materials
JP6595593B2 (en) Method for manufacturing turbine engine component
US20170021453A1 (en) Gamma prime precipitation strengthened nickel-base superalloy for use in powder based additive manufacturing process
EP2589449A1 (en) A process for the production of articles made of a gamma-prime precipitation-strengthened nickel-base superalloy by selective laser melting (SLM)
US20020197152A1 (en) Airfoils with improved oxidation resistance and manufacture and repair thereof
US10315264B2 (en) Joining process and joined article
CN106521384B (en) A kind of method that Nb Si based alloy inoxidizability is improved using electron beam remelting technology
JP2014513207A5 (en)
US20230033578A1 (en) Techniques and assemblies for joining components
RU2763528C1 (en) Replacing the turbine aerodynamic profile section with metal pre-sintered soldering billet
JP2017008929A (en) Additive manufacturing methods and hybrid articles using brazeable additive structures
CN103949639A (en) Method for preparing Nb-Si based superhigh-temperature alloy by SLM (selective laser melting) technology
KR20100091178A (en) Joining and material application method for a workpiece having a workpiece region comprising a titanium aluminide alloy
CN109562472B (en) Method for joining materials and material composite structure
US11969799B2 (en) Method for producing blades from Ni-based alloys and blades produced therefrom
US9186724B2 (en) Electroslag and electrogas repair of superalloy components
US9156086B2 (en) Multi-component assembly casting
KR20150105351A (en) Remelting during deposition welding

Legal Events

Date Code Title Description
AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:COLOGNA, MARCO;LAMPENSCHERF, STEFAN;WALTER, STEFFEN;SIGNING DATES FROM 20131129 TO 20131213;REEL/FRAME:032184/0351

AS Assignment

Owner name: SIEMENS ENERGY, INC., FLORIDA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SCHILLIG, CORA;REEL/FRAME:033473/0660

Effective date: 20131127

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIEMENS ENERGY, INC.;REEL/FRAME:033474/0243

Effective date: 20140113

Owner name: SIEMENS CORPORATION, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KULKARNI, ANAND A;PHAM, GIA KHANH;REEL/FRAME:033475/0387

Effective date: 20131202

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIEMENS CORPORATION;REEL/FRAME:033475/0409

Effective date: 20140113

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION