WO2015122953A2 - Use of spark plasma sintering for manufacturing superalloy compound components - Google Patents

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

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Publication number
WO2015122953A2
WO2015122953A2 PCT/US2014/067086 US2014067086W WO2015122953A2 WO 2015122953 A2 WO2015122953 A2 WO 2015122953A2 US 2014067086 W US2014067086 W US 2014067086W WO 2015122953 A2 WO2015122953 A2 WO 2015122953A2
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WO
WIPO (PCT)
Prior art keywords
superalloy
component
plasma sintering
spark plasma
compound
Prior art date
Application number
PCT/US2014/067086
Other languages
French (fr)
Other versions
WO2015122953A3 (en
Inventor
Marco Cologna
Anand A. Kulkarni
Stefan Lampenscherf
Gia Khanh Pham
Cora Schillig
Steffen Walter
Original Assignee
Siemens Energy, Inc.
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Filing date
Publication date
Application filed by Siemens Energy, Inc. filed Critical Siemens Energy, Inc.
Publication of WO2015122953A2 publication Critical patent/WO2015122953A2/en
Publication of WO2015122953A3 publication Critical patent/WO2015122953A3/en

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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
    • 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
    • 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 operate under high mechanical stress while withstanding harsh operating conditions. For this reason, nickel-based superalloys are a preferred materia! for hot gas path components of gas turbines such as discs, casings, vane segments and turbine blades. Some of these superalloys, particularly 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.
  • 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.
  • welding of highly strengthened nickel-based superalloys like PWA 1483, Rene 80, CM 247, IN 738 and IN 939 shows many quality problems.
  • aspects of the invention provide a method of manufacturing a superalloy compound component having a first component portion comprising a first superalloy and a second component portion comprising a second superalloy or a refractor ⁇ ' metal.
  • the method includes using Spark Plasma Sintering for forming the superallov 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.
  • aspects of the present invention are based on the idea that Spark Plasma Sintering may be used for joining components of the same or different nickel-based superalioys or refractory metals, which may not be joined by welding due to the above-mentioned difficulties.
  • aspects of the invention propose using a sintering process for a different objective, 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 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 comprising the first superalloy is arranged in the first mould portion and a second metal powder comprising 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 method is especially useful for producing superalloy compound components where different segments of the superalloy compound component are formed from different superalloy materials or refractory metals which may not be joined by welding techniques.
  • this method may be useful for manufacturing specific components such as turbine blades of a gas turbine using different superalioys for different parts of the turbine blade in accordance with the expected mechanical and chemical stresses to be experienced by the respective part of the turbine blade in the operation of the gas turbine.
  • the method may further comprise providing a first component comprising a first superallov and a second component comprising a second superallov or a refractory metal.
  • the first and second components are arranged to contact each other before using Spark Plasma Sintering to form 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.
  • the diffusion bonding 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 objecti ve, i.e. for joining two formed components to each other.
  • the method may further comprise providing a layer of a superalloy powder in a contact region where the first component contacts the second component.
  • This superalloy powder will solidify during the Spark Plasma Sintering, thereby supporting the diffusion bonding of the two components.
  • the superal loy powder may comprise 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 superalioy compound component is a gas turbine component.
  • At least one of the first and the second superalloys may be a Ni-based superalioy.
  • This Ni-based superalioy may comprise at least one of Al and Ti.
  • the inventive methods are especially useful for joining components consisting of different superalloys.
  • the second superalioy may be different from the first superalioy.
  • Fig 1 is a cross sectional view of an exemplary superalioy compound component using a method in accordance with an aspect of the invention.
  • Figure 1 shows a cross sectional view of an exemplary superalioy compound component formed using the method of the invention.
  • two buttons made from Nickel-based superalloys were joined using Spark Plasma
  • buttons were 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 uiiweldable 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 methods described herein may be used for joining components of the same or different superalloys or of refractor ⁇ ' metals.
  • the methods described herein therefore allow for production of superalioy compound components from two or more components, thereby reducing the cost of production and repair of components that otherwise have to be produced monolithicaliy, This makes the methods described herein especially useful in the field of gas turbine production and repair,

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  • 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)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Turbine Rotor Nozzle Sealing (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

USE OF SPARK PLASMA SINTERING FOR MANUFACTURING SUPERALLOY COMPOUND COMPONENTS
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of United States Patent Application No, 14/088,791 , filed November 25, 2013.
FIELD
[0002] The invention provides a method of manufacturing a superalloy compound component.
BACKGROUND
[0003] Due to their superior properties, high temperature nickel-based superalloys are commonly used for a wide range of components that operate under high mechanical stress while withstanding harsh operating conditions. For this reason, nickel-based superalloys are a preferred materia! for hot gas path components of gas turbines such as discs, casings, vane segments and turbine blades. Some of these superalloys, particularly 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.
SUMMARY
[0004] In order to address the above-mentioned object, aspects of the invention provide a method of manufacturing a superalloy compound component having a first component portion comprising a first superalloy and a second component portion comprising a second superalloy or a refractor}' metal. According to an aspect of the invention, the method includes using Spark Plasma Sintering for forming the superallov compound component,
[0005] 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.
[0006] Aspects of the present invention are based on the idea that Spark Plasma Sintering may be used for joining components of the same or different nickel-based superalioys or refractory metals, which may not be joined by welding due to the above-mentioned difficulties. Thus, aspects of the invention propose using a sintering process for a different objective, 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,
[0007] This idea includes two main approaches - the first of which will be referred to herein as "powder metallurgy." According to this approach, the method 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 comprising the first superalloy is arranged in the first mould portion and a second metal powder comprising 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 method is especially useful for producing superalloy compound components where different segments of the superalloy compound component are formed from different superalloy materials or refractory metals which may not be joined by welding techniques. Thus, this method may be useful for manufacturing specific components such as turbine blades of a gas turbine using different superalioys for different parts of the turbine blade in accordance with the expected mechanical and chemical stresses to be experienced by the respective part of the turbine blade in the operation of the gas turbine.
[0008] The second approach is referred to herein as "diffusion bonding."
According to this approach, the method may further comprise providing a first component comprising a first superallov and a second component comprising a second superallov or a refractory metal. The first and second components are arranged to contact each other before using Spark Plasma Sintering to form 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 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 objecti ve, i.e. for joining two formed components to each other.
[0009] To support diffusion bonding of the two components, the method may further comprise providing a layer of a superalloy powder in a contact region where the first component contacts the second component. This superalloy powder will solidify during the Spark Plasma Sintering, thereby supporting the diffusion bonding of the two components. The superal loy powder may comprise the first superalloy, the second superalloy, or a mixture of the first superalloy and the second superalloy.
[0010] 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.
[0011] Preferably, the superalioy compound component is a gas turbine component. At least one of the first and the second superalloys may be a Ni-based superalioy. This Ni-based superalioy may comprise at least one of Al and Ti. The inventive methods are especially useful for joining components consisting of different superalloys. Thus, the second superalioy may be different from the first superalioy.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Fig 1 is a cross sectional view of an exemplary superalioy compound component using a method in accordance with an aspect of the invention.
DETAILED DESCRIPTION
[0013] Figure 1 shows a cross sectional view of an exemplary superalioy 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 uiiweldable 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 methods described herein may be used for joining components of the same or different superalloys or of refractor}' metals. The methods described herein therefore allow for production of superalioy compound components from two or more components, thereby reducing the cost of production and repair of components that otherwise have to be produced monolithicaliy, This makes the methods described herein especially useful in the field of gas turbine production and repair,
[0014] Although the invention has been shown and described with respect to exemplar}' 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 , [0015] 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 alternati ves, modifications, and equivalents as may be included within the scope of the invention as defined by the appended claims.

Claims

[0016] What is claimed is:
1. A method of manufa cturing a superalloy compound component, comprising:
providing a first component portion comprising a first superalloy and a second component portion comprising a second superalloy or of a refractory metal; and
using Spark Plasma Sintering to join the first component portion to the second component portion and form the superalloy compound component.
2. The method of claim 1, wherein the providing is done by:
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 comprising a first superalloy in the first mould portion to provide the first component portion,
arranging a second metal powder comprising a second superalloy or a refractory metal in the second mould portion to provide the second component portion, and
wherein the using Spark Plasma Sintering comprises integrally forming the superalloy compound component by Spark Plasma Sintering the first and second component portions in the mould.
3. The method of claims 1 to 2, further comprising:
providing a first component comprising the first superalloy and a second component comprising the second superall oy 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.
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 comprises the first superalloy, the second superalloy, or a mixture of the first superalloy and the second superalloy,
6. The method of claims 1 to 5, wherein the Spark Plasma Sintering is carried out under vacuum.
7. The method of claims 1 to 6, wherein the Spark Plasma Sintering includes pressing the first component portion and the second component portion.
8. The method of claims 1 to 7, wherein the superalloy compound component is a gas turbine component.
9. The method of claims 1 to 8, 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.
1 1. The method of claims 1 to 10, wherein the second superalloy is different from the first superalloy.
PCT/US2014/067086 2013-11-25 2014-11-24 Use of spark plasma sintering for manufacturing superalloy compound components WO2015122953A2 (en)

Applications Claiming Priority (2)

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

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EP3575016A1 (en) * 2018-06-01 2019-12-04 Siemens Aktiengesellschaft Improvements relating to the manufacture of superalloy components
EP4105450A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Passive clearance control (apcc) system produced by field assisted sintering technology (fast)
EP4105443A1 (en) * 2021-06-18 2022-12-21 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
EP4105449A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Hybrid bonded configuration for blade outer airseal (boas)
US12055056B2 (en) 2021-06-18 2024-08-06 Rtx Corporation Hybrid superalloy article and method of manufacture thereof

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Cited By (8)

* 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
EP4105450A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Passive clearance control (apcc) system produced by field assisted sintering technology (fast)
EP4105443A1 (en) * 2021-06-18 2022-12-21 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
EP4105449A1 (en) * 2021-06-18 2022-12-21 Raytheon Technologies Corporation Hybrid bonded configuration for blade outer airseal (boas)
US12037912B2 (en) 2021-06-18 2024-07-16 Rtx Corporation Advanced passive clearance control (APCC) control ring produced by field assisted sintering technology (FAST)
US12055056B2 (en) 2021-06-18 2024-08-06 Rtx Corporation Hybrid superalloy article and method of manufacture thereof

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WO2015122953A3 (en) 2015-10-29

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