EP3441166A1 - Verbesserungen an aus metalllegierungen hergestellten komponenten - Google Patents

Verbesserungen an aus metalllegierungen hergestellten komponenten Download PDF

Info

Publication number
EP3441166A1
EP3441166A1 EP17185350.0A EP17185350A EP3441166A1 EP 3441166 A1 EP3441166 A1 EP 3441166A1 EP 17185350 A EP17185350 A EP 17185350A EP 3441166 A1 EP3441166 A1 EP 3441166A1
Authority
EP
European Patent Office
Prior art keywords
metal alloy
region
alloy composition
suitably
component
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.)
Withdrawn
Application number
EP17185350.0A
Other languages
English (en)
French (fr)
Inventor
Manu Mathai
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 EP17185350.0A priority Critical patent/EP3441166A1/de
Priority to PCT/EP2018/071357 priority patent/WO2019030211A1/en
Publication of EP3441166A1 publication Critical patent/EP3441166A1/de
Withdrawn legal-status Critical Current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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F3/15—Hot isostatic pressing
    • 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
    • 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
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • 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

Definitions

  • the present disclosure relates to components manufactured from metal alloys and to a method of manufacturing such components from metal alloy powders.
  • the disclosure is concerned with components, for example turbine discs, having a composition gradient across at least one dimension of the component and different grain sizes in different regions of the component.
  • Turbine discs used in the turbine end of gas turbines may be typically made of the nickel alloys IN718 or Nimonic 80.
  • IN718 is typically prone to stress assisted grain boundary oxidation also called "SAGBO" which limits its use to temperatures of less than 550 °C.
  • SAGBO stress assisted grain boundary oxidation
  • Such turbine discs may suffer from an intergranular type brittle mode of cracking caused by the SAGBO effect.
  • the rim region of the disc which is in contact with the turbine blades is typically at a higher temperature than the hub of the disc, in use. This is because the turbine blades are exposed to the high temperature combustion gases and subsequently the high temperature turbine blades heat up the rim region of the disc.
  • the higher temperature at the rim region means that the rim region should ideally have better creep resistance. This may be achieved with a coarse grain size of the nickel alloy.
  • the hub of the disc would not require as high a creep resistance as the rim but would require higher low cycle fatigue resistance due to the centrifugal loading experienced by the hub. Higher low cycle fatigue resistance at the hub may be achieved with a fine grain size of the nickel alloy.
  • a metal alloy component such as a turbine disc, having more favourable grain sizes at the appropriate regions of the component, for example at the rim and hub regions of a turbine disc, and therefore providing better mechanical properties at said regions, is highly desirable.
  • US patent 6,660,110 B1 provides a dual heat treatment process for producing a component comprising different grain sizes in different regions.
  • a dual heat treatment process may be more complicated and costly than a single temperature heat treatment process.
  • US patent 7,895,874 B2 provides a multistep forging method for obtaining a component comprising different grain sizes in different regions.
  • a multistep forging method may be more complicated and costly than a single step forming process followed by heat treatment.
  • the inventors have analysed a turbine disc made of IN718 by a standard method of hot die forging. It was observed that the grain size distribution in the disc was the opposite to the ideal distribution described above, namely that the rim region (grain size in the range of ASTM 11-12) had a finer grain size than the hub region (grain size in the range of ASTM 10-10.5). This grain size distribution is not considered to provide the ideal creep resistance at the rim region or the ideal low cycle fatigue resistance at the hub region.
  • the reason for this difference in grain size distribution may be due to the hot die forging of these turbine discs which allows greater recrystallization of grains at the outer edge of the forged disc due to the higher temperature at the rim region compared to the hub region.
  • a component comprising:
  • the component of this first aspect may be considered to have a composition gradient across at least one dimension, between the first region and the second region.
  • a composition gradient is typically considered to be a variance in composition across a component, for example the metal alloy composition of the component may vary in one or more constituents of the metal alloy along the component.
  • composition gradient is a gradual change in composition from the first region to the second region of the component.
  • a composition gradient may be distinct from a step change in composition between different regions in components formed from metal alloys of the prior art.
  • first metal alloy composition and the second metal alloy composition are similar and vary in the amount of one or more elements or compounds, suitably metallic elements, present in the compositions.
  • the first metal alloy composition and the second metal alloy composition are 80 % similar, suitably 85 % similar, suitably 90 % similar, suitably 95 % similar.
  • the different metal alloy compositions at different regions of the component are mixed with the adjacent metal alloy composition at an interface region.
  • the inventors have found that providing the component of this first aspect allows the different metal alloy compositions at different regions of the component, for example the first and second metal alloy compositions, to mix in this way at interface regions to provide a more gradual change in composition and properties from one region to the adjacent region than is possible in prior art components. This may also provide a stronger bond between adjacent regions than is possible in prior art components.
  • the component has a composition gradient along the length of the component.
  • the first metal alloy composition and the second metal alloy composition comprise respective gamma and gamma prime phases and therefore an associated gamma prime solvus temperature at which the gamma prime phase is soluble in the gamma phase.
  • the gamma prime solvus temperature may be measured by standard techniques such as differential thermal analysis (DTA).
  • the gamma prime solvus temperature of the second metal alloy composition is higher than the gamma prime solvus temperature of the first metal alloy composition.
  • the gamma prime solvus temperature of the second metal alloy composition is 15 °C higher than the gamma prime solvus temperature of the first metal alloy composition, suitably 20 °C higher, suitably 25 °C higher, suitably 30 °C higher.
  • the average grain size of the metal alloy compositions are measured according to the methods of ASTM E112-12 "Standard Test Methods for Determining Average Grain Size”.
  • the average grain size of the first metal alloy composition in the first region is larger than the average grain size of the second metal alloy composition in the second region.
  • the average grain size of the first metal alloy composition is a coarse grain size according to ASTM 9, suitably in the range of ASTM 2 to 9.
  • the average grain size of the second metal alloy composition is a fine grain size according to ASTM 10-13.
  • the component according to this first aspect has average grain sizes of the metal alloy compositions at different regions on the component, for example at the first and second regions, which may provide different mechanical properties at said regions which may be more beneficial to the function of the component than a similar component not having the composition gradient, grain size distribution and gamma prime solvus temperature relationship defined in this first aspect.
  • this grain size distribution can be obtained by using a single heat treatment process on the entire component, suitably at a single temperature, said temperature being higher than the gamma prime solvus temperature of the first metal alloy composition and lower than the gamma prime solvus temperature of the second metal alloy composition.
  • Such a single heat treatment step at a single temperature may provide significant improvements in the efficiency of a manufacturing process used to produce the component.
  • the first metal alloy composition is enriched in an element or a compound which decreases the gamma prime solvus temperature of the first metal alloy composition, compared to the second metal alloy composition.
  • the first metal alloy composition is enriched in a metallic element which decreases the gamma prime solvus temperature of the first metal alloy composition, compared to the second metal alloy composition.
  • the first metal alloy composition comprises more of the element or compound than the second metal alloy composition. Therefore in order to accommodate an increased amount of said element or compound, the amount of one or more other elements or compounds of the first metal alloy composition are lower than in the second metal alloy composition.
  • enriched we mean to include embodiments wherein the first metal alloy composition comprises an element or a compound which decreases the gamma prime solvus temperature of the first metal alloy composition, which is not present in the second metal alloy composition.
  • the metallic element which decreases the gamma prime solvus temperature of the first metal alloy composition is cobalt and/or chromium.
  • the metallic element which decreases the gamma prime solvus temperature of the first metal alloy composition is cobalt.
  • the first metal alloy composition comprises at least 3.0 wt% cobalt, suitably at least 4.0 wt%, suitably at least 5.0 wt%, suitably at least 6.0 wt%.
  • the first metal alloy composition comprises up to 11 wt% cobalt, suitably up to 10 wt%, suitably up to 9.0 wt%, suitably up to 8.0 wt%.
  • the first metal alloy composition comprises from 4.0 to 10 wt% cobalt, suitably from 4.0 to 9.0 wt%, suitably from 5.0 to 8.0 wt%, suitably from 6.0 to 8.0 wt%.
  • the first metal alloy composition comprises at least 10 wt% chromium, suitably at least 12 wt%, suitably at least 14 wt%, suitably at least 16 wt%.
  • the first metal alloy composition comprises up to 24 wt% chromium, suitably up to 22 wt%, suitably up to 20 wt%, suitably up to 18 wt%.
  • the first metal alloy composition comprises from 11 to 23 wt% chromium, suitably from 13 to 21 wt%, suitably from 15 to 19 wt%, suitably from 15 to 18 wt%.
  • the first and second metal alloy compositions comprise aluminium and titanium.
  • the ratio of aluminium to titanium in the metal alloy compositions may be associated with the creep resistance of the respective regions of the component. A higher ratio of aluminium to titanium may provide an improved creep resistance. Therefore the first metal alloy composition may be enriched in titanium compared to the second metal alloy composition to provide a higher ratio of aluminium to titanium in the first metal alloy composition compared to the second metal alloy composition, in order to provide an improved creep resistance in the first region compared to the second region.
  • the first metal alloy composition comprises at least 2.0 wt% aluminium, suitably at least 2.5 wt%, suitably at least 3.0 wt%, suitably at least 3.5 wt%.
  • the first metal alloy composition comprises up to 5.5 wt% aluminium, suitably up to 5.0 wt%, suitably up to 4.5 wt%, suitably up to 4.0 wt%.
  • the first metal alloy composition comprises from 2.8 to 5.0 wt % aluminium, suitably from 2.8 to 4.4 wt %, suitably from 3.0 to 4.2 wt %, suitably from 3.0 to 4.0 wt%.
  • the first metal alloy composition comprises at least 0.8 wt% titanium, suitably at least 1.0 wt%, suitably at least 1.2 wt%, suitably at least 1.4 wt%.
  • the first metal alloy composition comprises up to 2.2 wt% titanium, suitably up to 2.0 wt%, suitably up to 1.8 wt%, suitably up to 1.6 wt%.
  • the first metal alloy composition comprises from 0.7 to 2.3 wt % titanium, suitably from 0.9 to 2.1 wt %, suitably from 1.0 to 1.9 wt %, suitably from 1.0 to 1.7 wt%.
  • the first metal alloy composition comprises a ratio of aluminium to titanium of from 0.8 to 1.6, suitably from 1.0 to 1.4, suitably approximately 1.2.
  • the first metal alloy composition may be enriched in boron compared to the second metal alloy composition to provide an improved creep resistance in the first region compared to the second region.
  • the second metal alloy composition comprises at least 0.5 wt% cobalt, suitably at least 1.0 wt%, suitably at least 1.5 wt%, suitably approximately 2.0 wt% cobalt.
  • the second metal alloy composition comprises up to 3.0 wt% cobalt, suitably up to 2.5 wt%, suitably up to 2.0 wt%.
  • the second metal alloy composition comprises at least 10 wt% chromium, suitably at least 11 wt%, suitably at least 12 wt%, suitably at least 13 wt%.
  • the second metal alloy composition comprises up to 17 wt% chromium, suitably up to 16 wt%, suitably up to 15 wt%, suitably up to 14 wt%.
  • the second metal alloy composition comprises from 10 to 15 wt% chromium, suitably from 10 to 16 wt%, suitably from 12 to 16 wt%, suitably from 12 to 15 wt%.
  • the second metal alloy composition may be enriched in one or more of niobium, tungsten and molybdenum, compared to the first metal alloy composition, which may provide an improved strength in the second region compared to the first region.
  • the second metal alloy composition comprises at least 0.1 wt% niobium, suitably at least 0.2 wt%, suitably at least 0.5 wt%.
  • the second metal alloy composition comprises up to 2.0 wt% niobium, suitably up to 1.5 wt%, suitably up to 1.0 wt%.
  • the second metal alloy composition comprises at least 2.0 wt% tungsten, suitably at least 3.0 wt%, suitably at least 4.0 wt%.
  • the second metal alloy composition comprises up to 6.0 wt% tungsten, suitably up to 5.0 wt%, suitably up to 4.5 wt%.
  • the second metal alloy composition comprises from 3.0 to 6.0 wt% tungsten, suitably from 3.0 to 5.0 wt%, suitably from 4.0 to 6.0 wt%, suitably from 4.0 to 5.0 wt%.
  • the second metal alloy composition may comprise molybdenum, suitably from 0.5 to 2.5 wt%, suitably from 1.0 to 2.0 wt%.
  • the second metal alloy composition comprises a ratio of aluminium to titanium of from 0.4 to 0.8, suitably from 0.5 to 0.7, suitably from 0.6 to 0.7.
  • the component of this first aspect comprises an intermediate region having an intermediate metal alloy composition wherein the intermediate metal alloy composition in the intermediate region has a gamma prime solvus temperature higher than the gamma prime solvus temperature of the first metal alloy composition in the first region and lower than the gamma prime solvus temperature of the second metal alloy composition in the second region.
  • the intermediate metal alloy composition comprises the element or compound which decreases the gamma prime solvus temperature of the first metal alloy composition in the first region compared to the second metal alloy composition in the second region, in an amount between the amount of said element or compound in the first metal alloy composition and the amount of said element or compound in the second metal alloy composition.
  • the intermediate metal alloy composition is 85 % similar to first and second metal alloy compositions, suitably 90 % similar, suitably 95 % similar.
  • the component comprises an intermediate region
  • the intermediate region is arranged between the first and second regions of the component.
  • the intermediate metal alloy composition comprises at least 1.0 wt% cobalt, suitably at least 2.0 wt%, suitably at least 3.0 wt%.
  • the intermediate metal alloy composition comprises up to 6.0 wt% cobalt, suitably up to 5.0 wt%, suitably up to 4.0 wt%.
  • the intermediate metal alloy composition comprises from 2.0 to 5.0 wt% cobalt, suitably from 3.0 to 5.0 wt%, suitably from 3.0 to 4.0 wt%.
  • the intermediate metal alloy composition comprises at least 16 wt% chromium, suitably at least 17 wt%, suitably at least 18 wt%.
  • the intermediate metal alloy composition comprises up to 22 wt% chromium, suitably up to 21 wt%, suitably up to 20 wt%.
  • the intermediate metal alloy composition comprises from 16 to 22 wt% chromium, suitably from 17 to 21 wt%, suitably from 18 to 20 wt%.
  • the intermediate metal alloy composition comprises at least 2.0 wt% aluminium, suitably at least 2.5 wt%, suitably at least 3.0 wt%.
  • the intermediate metal alloy composition comprises up to 5.5 wt% aluminium, suitably up to 5.0 wt%, suitably up to 4.5 wt%, suitably up to 4.0 wt%.
  • the intermediate metal alloy composition comprises from 2.8 to 5.0 wt % aluminium, suitably from 2.8 to 4.4 wt %, suitably from 3.0 to 4.2 wt %, suitably from 3.0 to 4.0 wt%.
  • the intermediate metal alloy composition comprises at least 0.8 wt% titanium, suitably at least 1.0 wt%, suitably at least 1.2 wt%, suitably at least 1.4 wt%.
  • the intermediate metal alloy composition comprises up to 2.8 wt% titanium, suitably up to 2.6 wt%, suitably up to 2.4 wt%, suitably up to 2.2 wt%.
  • the intermediate metal alloy composition comprises from 1.2 to 2.5 wt % titanium, suitably from 1.3 to 2.4 wt %, suitably from 1.4 to 2.3 wt %, suitably from 1.5 to 2.2 wt%.
  • the component comprises a fourth region having a fourth metal alloy composition; wherein the fourth metal alloy composition is enriched in an element or compound which increases the quench cracking resistance of the fourth region of the component compared to the first and/or second region of the component.
  • the component comprises a fourth region having a fourth metal alloy composition; wherein the fourth metal alloy composition is enriched in a metallic element which increases the quench cracking resistance of the fourth region of the component compared to the first and/or second region of the component.
  • the metallic element which increases the quench cracking resistance of the fourth region of the component compared to the first and/or second region of the component is tungsten and/or niobium and/or molybdenum.
  • the metallic element which increases the quench cracking resistance of the fourth region of the component compared to the first and/or second region of the component is tungsten.
  • the fourth metal alloy composition comprises at least 2.0 wt% tungsten, suitably at least 2.5 wt%, suitably at least 3.0 wt%.
  • the fourth metal alloy composition comprises up to 5.0 wt% tungsten, suitably up to 4.5 wt%, suitably up to 4.0 wt%.
  • the fourth metal alloy composition comprises from 2.0 to 5.0 wt% tungsten, suitably from 2.0 to 4.0 wt%, suitably from 3.0 to 4.0 wt%.
  • the fourth metal alloy composition comprises at least 10 wt% chromium, suitably at least 12 wt%, suitably at least 14 wt%, suitably at least 16 wt%.
  • the fourth metal alloy composition comprises up to 24 wt% chromium, suitably up to 22 wt%, suitably up to 20 wt%, suitably up to 18 wt%.
  • the fourth metal alloy composition comprises from 11 to 23 wt% chromium, suitably from 13 to 21 wt%, suitably from 15 to 19 wt%, suitably from 15 to 18 wt%.
  • the fourth metal alloy composition comprises at least 0.5 wt% cobalt, suitably at least 1.0 wt%, suitably at least 1.5 wt%, suitably approximately 2.0 wt% cobalt.
  • the fourth metal alloy composition comprises up to 3.0 wt% cobalt, suitably up to 2.5 wt%, suitably up to 2.0 wt%.
  • the fourth metal alloy composition comprises a ratio of aluminium to titanium of from 0.4 to 0.8, suitably from 0.5 to 0.7, suitably from 0.6 to 0.7.
  • the first, second, the optional intermediate and the optional fourth metal alloy compositions are based on a base metal alloy with the amounts of at least one element or compound varying in each of the first, second, the optional intermediate and the optional fourth metal alloy compositions compared to each other.
  • the amounts of at least one element or compound vary in each of the first, second, the optional intermediate and the optional fourth metal alloy compositions compared to the base metal alloy composition.
  • the base metal alloy composition is a commercially available metal alloy composition.
  • One of the first, second, the optional intermediate and the optional fourth metal alloy compositions may have the same composition as the base metal alloy composition.
  • the component is formed of nickel alloys.
  • the first, second, the optional intermediate, the optional fourth and the optional base metal alloy compositions are nickel alloy compositions.
  • the component is a turbine disc wherein the first region is a rim region of the turbine disc and the second region is a hub region of the turbine disc.
  • the turbine disc comprises the fourth region and the fourth region of the turbine disc is in contact with the hub region and arranged between the hub region and the rim region.
  • composition gradient across at least one dimension is radially through the turbine disc.
  • a method of manufacturing a component from metal alloy powders comprising the steps of:
  • the component manufactured by the method of this second aspect may have any of the suitable features or advantages described in relation to the component of the first aspect.
  • the first and second metal alloy powders used in the method of this second aspect may have any of the suitable features or advantages described in relation to the first and second metal alloy compositions of the first aspect.
  • the first metal alloy powder is provided by enriching a base metal alloy in a metallic element which decreases the gamma prime solvus temperature of the first metal alloy powder.
  • the component is formed of nickel alloys and the first and second metal alloy powders are nickel alloy powders.
  • step c) involves processing the first metal alloy powder and the second metal alloy powder using hot isostatic pressing.
  • step b) of the method of this second aspect involves providing a hollow canister for use in a process of hot isostatic pressing, the canister having a first section and a second section, the first section having a greater strength than the second section, the first section corresponding to the first region in the component and the second section corresponding to the second region in the component; wherein the first metal alloy powder is added to the first section of the canister and the second metal alloy powder is added to the second section of the canister.
  • step c) involves subjecting the canister comprising the first and second metal alloy powders to a hot isostatic pressing process to form the component inside the canister; wherein the pressure exerted on the metal alloy powders inside the canister by the hot isostatic pressing process is greater at the second section of the canister than at the first section of the canister.
  • the canister comprises first and second sections, the first section having a greater strength than the second section.
  • the first and second sections of the canister, along with any other section or sections present, are joined together to form a contiguous canister comprising a contiguous cavity into which metal alloy powders can be added to undergo the hot isostatic pressing procedure.
  • a contiguous canister comprising a contiguous cavity into which metal alloy powders can be added to undergo the hot isostatic pressing procedure.
  • the first and second sections of the canister may be distinguished from each other by the use of different materials to form the first and second sections.
  • the first section of the canister has a higher strength than the second section.
  • This may be additionally or alternatively defined as the first section of the canister having a higher resistance to pressure exerted on the canister, for example during hot isostatic pressing, than the second section. Therefore the second section of the canister may exert a higher pressure on the second metal alloy powder contained within the second section than the first section of the canister exerts on first metal alloy powder contained within the first section, when the canister is subjected to a constant uniform pressure across its extent from an external source, for example during hot isostatic pressing.
  • the method may therefore allow the first region and the second region of the component to be produced by hot isostatic pressing at different pressures which are more appropriate for favourable mechanical property development than in known methods wherein the first and second regions are formed at the same pressure.
  • the method may therefore provide a component having better mechanical properties in at least one of the first region and the second region than a similar component formed from a method of the prior art using a canister having the same strength in each section.
  • the strength of the first and second sections of the canister can be measured by standard techniques using samples of the materials used to make the sections of the canister, for example as described in ASTM E8/E8M-16 A "Standard Test Methods for Tension Testing of Metallic Materials”.
  • the stated difference in strength of the first and second sections is intended to result from an intentional design choice in the materials or construction of the first and second sections and is not intended to cover the relatively small variance in strength which may arise from the shape of the canister necessitated by the desired shape of the component to be formed within the canister.
  • the difference in strength between the first section and the second section is at least 40 MPa, suitably at least 50 MPa, suitably at least 60 MPa or at least 75 MPa, for example at least 100 MPa.
  • the method of this first aspect comprises a step, after step c), of removing the component from then canister.
  • the canister comprises a third section having a strength lower than the first section and greater than the second section, and optionally wherein the canister comprises a fourth section having a strength lower than the first and third sections and greater than the second section.
  • the component is a turbine disc and the first section of the canister provides a rim section of the turbine disc and the second section of the canister provides a hub section of the turbine disc.
  • step c) involves subjecting the canister to the same conditions of temperature and pressure throughout the canister.
  • step c) involves subjecting the canister to a pressure of at least 80 MPa, suitably at least 100 MPa, suitably at least 120 MPa.
  • step c) involves subjecting the canister to a pressure of up to 200 MPa, suitably up to 175 MPa, suitably up to 150 MPa.
  • step c) involves subjecting the canister to a temperature of at least 700 °C, suitably at least 750 °C, suitably at least 800 °C, suitably at least 850 °C.
  • step c) involves subjecting the canister to a temperature of up to 1,100 °C, suitably up to 1,000 °C, suitably up to 950 °C, suitably up to 900 °C.
  • the strength of the first and second sections, and optionally the third and fourth sections, of the canister are matched to the ideal pressure during hot isostatic pressing of the metal alloy powders in the first and second, and optionally third and fourth, sections of the canister.
  • ideal pressure we mean a pressure which, when applied to the metal alloy powder in question, at a particular temperature, provides improved (suitably optimised) mechanical properties in the corresponding regions of the component after hot isostatic pressing.
  • Figure 1 shows a component (100) which comprises a first region (110) having a first metal alloy composition and comprising a gamma prime phase, and a second region (120) having a second metal alloy composition and comprising a gamma prime phase.
  • the component (100) also comprises an intermediate region (130) having an intermediate metal alloy composition arranged between the first and second regions of the component.
  • the first, second and intermediate metal alloy compositions are different to each other and provide a composition gradient through the component (100) from the first region (110), through the intermediate region (130) and to the second region (120).
  • the component also comprises a first interface region (111) between the first region (110) and the intermediate region (130), and a second interface region (121) between the intermediate region (130) and the second region (120).
  • the interface regions have a composition which is a mixture of the metal alloy compositions of the adjacent regions.
  • the first interface region (111) has a composition which is a mixture of the first metal alloy composition and the intermediate metal alloy composition
  • the second interface region (121) has a composition which is a mixture of the intermediate metal alloy composition and the second metal alloy composition.
  • the interface regions provide a gradual change in composition and properties from one region to the adjacent region, and may provide an improved strength at said interface compared to components which have radically different metal alloy compositions adjacent to each other and/or which may not be mixed to form said interface regions.
  • the gamma prime solvus temperature of the second metal alloy composition is higher than the gamma prime solvus temperature of the first metal alloy composition, and the intermediate metal alloy composition has a gamma prime solvus temperature higher than the gamma prime solvus temperature of the first metal alloy composition and lower than the gamma prime solvus temperature of the second metal alloy composition.
  • the average grain size of the first metal alloy composition in the first region is larger than the average grain size of the second metal alloy composition in the second region.
  • the average grain size of the intermediate metal alloy composition in the intermediate region may be larger than the average grain size of the second metal alloy composition in the second region and smaller than the average grain size of the first metal alloy composition in the first region.
  • the first, second and intermediate compositions may be based on the following base alloy composition, Nimonic 80: Table 1: Base metal alloy composition - Nimonic 80 chromium 18-21 wt% titanium 1.8-2.7 wt% aluminium 1.0-1.8 wt% iron 3.0 max wt% cobalt 2.0 max wt% manganese 1.0 max wt% nickel Balance
  • the first metal alloy composition may comprise a relatively high amount of cobalt and/or chromium, compared to the second and/or intermediate metal alloy composition. Said increased amount of cobalt and/or chromium may decrease the gamma prime solvus temperature of the first metal alloy composition relative to the second and/or intermediate metal alloy compositions. Said increased amount of cobalt and/or chromium may also decrease the gamma prime solvus temperature of the first metal alloy composition relative to the base metal alloy composition.
  • the first metal alloy composition may comprise a relatively high ratio of aluminium to titanium, compared to the second and/or intermediate metal alloy composition. Said increased ratio of aluminium to titanium may increase the creep resistance of the first metal alloy composition relative to the second and/or intermediate metal alloy compositions. Said increased ratio of aluminium to titanium may increase the creep resistance of the first metal alloy composition relative to the base metal alloy composition.
  • the first metal alloy composition may be as follows: Table 2: First metal alloy composition chromium 15-18 wt% titanium 1.0-1.7 wt% aluminium 3.0- 4.0 wt% iron 3.0 max wt% cobalt 8.0 max wt% manganese 1.0 max wt% nickel Balance
  • the second metal alloy composition may comprise a relatively low amount of cobalt and/or chromium, compared to the first and/or intermediate metal alloy composition. Said decreased amount of cobalt and/or chromium may increase the gamma prime solvus temperature of the first metal alloy composition relative to the first and/or intermediate metal alloy compositions. The amount of cobalt and/or chromium in the second metal alloy composition may be approximate to the amount of cobalt and/or chromium in the base metal alloy composition.
  • the second metal alloy composition may comprise a relatively high amount of tungsten and/or niobium and/or molybdenum, compared to the first and/or intermediate metal alloy compositions. Said increased amount of tungsten and/or niobium and/or molybdenum may increase the strength of the second metal alloy composition relative to the first and/or intermediate metal alloy compositions. Said increased amount of tungsten and/or niobium and/or molybdenum may increase the strength of the second metal alloy composition relative to the base metal alloy composition.
  • the second metal alloy composition may be as follows: Table 3: Second metal alloy composition chromium 12-15 wt% titanium 1.8-2.7 wt% aluminium 1.0- 1.8 wt% iron 3.0 max wt% cobalt 2.0 max wt% niobium 1.0 max wt% tungsten 4-5 max wt% nickel Balance
  • the intermediate metal alloy composition may have the composition of the base metal alloy composition. In some embodiments, the intermediate metal alloy composition may be a mixture of the first and second metal alloy compositions, for example a 1:1 mixture of the first and second metal alloy compositions.
  • Figure 2 shows a radial cross section of a nickel alloy turbine disc (200) comprising a first region (210) having a first metal alloy composition and comprising a gamma prime phase and a second region (220) having a second metal alloy composition and comprising a gamma prime phase.
  • the turbine disc (200) also comprises an intermediate region (230) having an intermediate metal alloy composition arranged between the first and second regions of the component.
  • the turbine disc (200) also comprises a fourth region (240) having a fourth metal alloy composition arranged between the first and intermediate regions of the component.
  • the first, second and intermediate metal alloy compositions are as described in relation to the component (100) shown in Figure 1 .
  • the fourth metal alloy composition is different to each of the first, second and fourth metal alloy compositions.
  • the first, second, fourth and intermediate metal alloy compositions provide a composition gradient radially through the turbine disc (200) from the first region (210), through the intermediate region (230), through the fourth region (240) and to the second region (220).
  • the turbine disc also comprises first interface region (211) between the first region (210) and the intermediate region (230), second interface region (221) between the second region (220) and the fourth region (240) and fourth interface region (231) between the fourth region (240) and the intermediate region (230).
  • the interface regions have a composition which is a mixture of the metal alloy compositions of the adjacent regions, as described in relation to the component (100) of Figure 1 .
  • the interface regions provide a gradual change in composition and properties from one region to the adjacent region, and may provide an improved strength at said interface compared to components which have radically different metal alloy compositions adjacent to each other.
  • the first region (210) of the turbine disc (200) is a rim region of the turbine disc and may have the composition described in relation to the first metal alloy composition of the component (100) of Figure 1 .
  • the second region (220) of the turbine disc (200) is a hub region of the turbine disc and may have the composition described in relation to the second metal alloy composition of the component (100) of Figure 1 .
  • the average grain size of the first metal alloy composition in the rim region is larger than the average grain size of the second metal alloy composition in the hub region.
  • the rim region having the coarser grain size may have an improved creep resistance compared to the hub and/or intermediate regions and compared to rim regions in prior art turbine discs referred to above.
  • the hub region having the finer grain size may have an improved strength compared to the rim and/or intermediate regions and compared to hub regions in prior art turbine discs referred to above.
  • Turbine disc (200) may therefore have optimised mechanical properties for the rim and hub regions, unlike the some of the prior art turbine discs referred to above.
  • the intermediate region (230) of the turbine disc (200) may have the intermediate metal alloy composition shown below: Table 4: Intermediate metal alloy composition chromium 18-20 wt% titanium 1.5-2.2 wt% aluminium 3.0- 4.0 wt% iron 3.0 max wt% cobalt 4.0 max wt% manganese 1.0 max wt% nickel Balance
  • the fourth region (240) of the turbine disc (200) may be a region of the turbine disc (200) which is prone to quench cracking, for example a region adjacent to the hub region (220).
  • the fourth metal alloy composition of the fourth region (240) may have a relatively low ratio of aluminium to titanium, compared to the first and/or second and/or intermediate metal alloy composition. Said decreased ratio of aluminium to titanium may increase the quench cracking resistance of the fourth metal alloy composition relative to the first and/or second and/or intermediate metal alloy compositions. Said decreased ratio of aluminium to titanium may increase the quench cracking resistance of the fourth metal alloy composition relative to the base metal alloy composition.
  • the fourth metal alloy composition may comprise a relatively high amount of tungsten and/or niobium and/or molybdenum, compared to the first and/or intermediate metal alloy compositions. Said increased amount of tungsten and/or niobium and/or molybdenum may increase the strength of the fourth metal alloy composition relative to the first and/or intermediate metal alloy compositions. Said increased amount of tungsten and/or niobium and/or molybdenum may increase the strength of the second metal alloy composition relative to the base metal alloy composition.
  • the amount of tungsten and/or niobium and/or molybdenum in the fourth metal alloy composition may be lower than the amount of tungsten and/or niobium and/or molybdenum in the second metal alloy composition of the hub region (220). This may provide a strength intermediate between the hub region (220) and the intermediate region (230), which may provide a more gradual change in composition and properties between the hub region (220) and the intermediate region (230) than would otherwise be possible, and may provide an improved bond between the hub region (220), the intermediate region (230) and the fourth region (240) and compared to known similar components.
  • the fourth metal alloy composition may be as follows: Table 5: Fourth metal alloy composition at regions prone to quench cracking chromium 15-18 wt% titanium 1.8-2.7 wt% aluminium 1.0- 1.8 wt% iron 3.0 max wt% cobalt 2.0 max wt% tungsten 3-4 max wt% nickel Balance
  • the first, second and intermediate compositions may be based on the following base alloy composition, IN718: Table 6: Base metal alloy composition - IN718 nickel 50-55 wt% iron 18.95 wt% chromium 17-21 wt% molybdenum 2.8-3.3 wt% carbon 0.08 wt% aluminium 0.2 -0.8 wt% titanium 0.65 -1.15 wt% niobium 4.75 - 5.5 wt%
  • the composition of IN718 may be adapted as described above for Nimonic 80 to provide the desired properties in the first, second, intermediate and fourth regions of the component.
  • IN718 is a gamma double prime strengthened alloy.
  • the gamma double prime phase has a reduced microstructural stability which results in the formation of delta phase and leads to the loss of mechanical properties and low component lives when temperatures exceed 600 °C, as typically seen at the rim of a gas turbine disc.
  • IN718 cannot be used when temperatures at the rim of the disc exceed 600 °C.
  • adjusting the composition of IN718 as described herein for Nimonic 80 may improve the temperature capability of IN718 moderately.
  • the coarsening rate of the gamma double prime phase may be slowed down to improve the thermal stability of the material. For example by having a higher Al/Ti as well as a higher (Al+Ti)/Nb content along with higher Al+Ti+Nb content at the expense of reducing the Ni content, slows down the coarsening behaviour of gamma double prime phase which results in increasing the transformation temperature of gamma double prime to delta phase.
  • the temperature capability of IN718 can therefore be extended by a further 50 °C.
  • Ticolloy has an Al+Ti+Nb content of 6.75%. Ticolloy has a higher temperature capability than IN718 and could therefore be used as the intermediate metal alloy composition in the intermediate region of the turbine disc.
  • Figure 3 shows a schematic (300) of a method according to the second aspect of the present invention of manufacturing a component, such as component (100) of Figure 1 or turbine disc (200) of Figure 2 , from metal alloy powders.
  • the method comprises operation (301) of providing a first metal alloy powder and a second metal alloy powder, wherein the second metal alloy has a higher gamma prime solvus temperature than the second metal alloy powder.
  • Operation (301) is followed by operation (302) of arranging the first metal alloy powder to provide a first region of the component and arranging the second metal alloy powder to provide a second region of the component.
  • Operation (302) is followed by operation (303) of processing the first metal alloy powder and the second metal alloy powder to provide the component comprising the first region and the second region.
  • Operation (303) is followed by operation (304) of heat treating the component at a temperature between the gamma prime solvus temperature of the first metal alloy powder and the gamma prime solvus temperature of the second metal alloy powder.
  • operation (302) involves providing an open canister and filling the canister with the metal alloy powders, for example from a hopper or hoppers, so that the different metal alloy powders are arranged as discussed above to provide the first and second regions and optionally the intermediate and fourth regions of the component.
  • the adjacent metal alloy powders partially mix as they are added to the open canister to provide interface regions in the component.
  • operation (303) involves processing the first metal alloy powder and the second metal alloy powder by hot isostatic pressing (HPI) to provide the component comprising the first region and the second region.
  • HIP hot isostatic pressing
  • the HIP process may involve closing the canister containing the metal alloy powders, degassing and sealing the closed canister and subjecting the canister to hot isostatic pressing (HIP).
  • the Hot isostatic pressing may be carried out at a temperature of 800 to 950 °C and at a pressure of around 100 MPa for 4 hours.
  • the HIP process can also be carried out as a multi-step process by applying a second value of pressure and temperature for a further amount of time to further enhance inter-particle bonding.
  • HIP hot isostatic pressing
  • the metal alloy powders are typically placed into a container known as a "canister” or “can”.
  • the canister is then sealed and degassed to ensure all oxygen is removed.
  • the canister and its contents are subsequently placed in vacuum in a Hot isostatic pressing (HIP) chamber.
  • the canister is then subject to elevated temperature and pressure on the outside typically using an inert gas like argon.
  • the inert gas applies pressure on the canister and then subsequently on the enclosed powder at all sides and directions.
  • the pressure and temperature conditions chosen for proper densification and bonding of powder particles during HIP is normally dependent on the alloy being used.
  • PPBs Prior Particle Boundaries
  • the component may then be removed from the canister by standard methods such as machining or by acid treatment.
  • the component may be then be isothermally forged or extruded, prior to operation (304) of heat treating the component.
  • Operation (304) involves subjecting the whole of the component to a single step of heat treatment at a temperature between the gamma prime solvus temperature of the first metal alloy powder and the gamma prime solvus temperature of the second metal alloy powder.
  • This heat treatment step allows the first region to obtain a coarser grain size than the second region (at this super-solvus temperature with respect to the first region) and allows the second region to obtain a finer grain size than the first region (at this sub-solvus temperature with respect to the second region), thereby providing optimised mechanical properties for the first and second regions.
  • the first region having the coarser grain size may have an improved creep resistance compared to the second and/or intermediate regions and compared to similar regions in similar components of the prior art.
  • the second region having the finer grain size may have an improved strength compared to the first and/or intermediate regions and compared to similar regions in similar components of the prior art.
  • This method may be used to produce the turbine disc (200) of Figure 2 by providing a turbine disc canister shaped appropriately for the production of the turbine disc (200) and by filing the canister with the first, second, intermediate and fourth metal alloy powders in the appropriate regions of the turbine disc canister to provide the rim (210), hub (220), intermediate (230) and fourth regions (240) of the turbine disc (200) respectively with the partial mixing of the different adjacent metal alloy powders providing the interface regions (211, 221 and 231).
  • the method may therefore provide a turbine disc (200) having an average grain size of the first metal alloy composition in the rim region which is larger than the average grain size of the second metal alloy composition in the hub region.
  • the rim region having the coarser grain size may have an improved creep resistance compared to the hub and/or intermediate regions and compared to rim regions in prior art turbine discs referred to above.
  • the hub region having the finer grain size may have an improved strength compared to the rim and/or intermediate regions and compared to hub regions in prior art turbine discs referred to above.
  • the method of Figure 3 may therefore provide a turbine disc (200) having optimised mechanical properties for the rim and hub regions.
  • the present invention provides a component, such as a nickel alloy turbine disc.
  • the component has a composition gradient through the component and comprises a first region having a first metal alloy composition and comprising a gamma prime phase; and a second region having a second metal alloy composition and comprising a gamma prime phase.
  • the gamma prime solvus temperature of the second metal alloy composition is higher than the gamma prime solvus temperature of the first metal alloy composition; and the average grain size of the first metal alloy composition is larger than the average grain size of the second metal alloy composition.
  • the component may have optimised mechanical properties at specific regions of the component, for example at the rim and hub regions of a turbine disc.
  • a method of manufacturing such a component from metal alloy powders is also disclosed.
  • compositions consisting essentially of a set of components will comprise less than 5% by weight, typically less than 3% by weight, more typically less than 1% by weight of non-specified components.
  • the first metal alloy composition comprises at least 3.0 wt% cobalt
  • the first metal alloy composition is provided by cobalt.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Composite Materials (AREA)
  • Powder Metallurgy (AREA)
EP17185350.0A 2017-08-08 2017-08-08 Verbesserungen an aus metalllegierungen hergestellten komponenten Withdrawn EP3441166A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17185350.0A EP3441166A1 (de) 2017-08-08 2017-08-08 Verbesserungen an aus metalllegierungen hergestellten komponenten
PCT/EP2018/071357 WO2019030211A1 (en) 2017-08-08 2018-08-07 IMPROVEMENTS RELATING TO COMPONENTS MANUFACTURED FROM METALLIC ALLOYS

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17185350.0A EP3441166A1 (de) 2017-08-08 2017-08-08 Verbesserungen an aus metalllegierungen hergestellten komponenten

Publications (1)

Publication Number Publication Date
EP3441166A1 true EP3441166A1 (de) 2019-02-13

Family

ID=59713771

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17185350.0A Withdrawn EP3441166A1 (de) 2017-08-08 2017-08-08 Verbesserungen an aus metalllegierungen hergestellten komponenten

Country Status (2)

Country Link
EP (1) EP3441166A1 (de)
WO (1) WO2019030211A1 (de)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5161950A (en) * 1989-10-04 1992-11-10 General Electric Company Dual alloy turbine disk
US6660110B1 (en) 2002-04-08 2003-12-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Heat treatment devices and method of operation thereof to produce dual microstructure superalloy disks
US20060260126A1 (en) * 2005-05-17 2006-11-23 General Electric Company Method for making a compositionally graded gas turbine disk
US20070081912A1 (en) * 2005-10-11 2007-04-12 Honeywell International, Inc. Method of producing multiple microstructure components
US7895874B2 (en) 2008-01-03 2011-03-01 General Electric Company Near net shape forging process for compressor and turbine wheels and turbine spacer wheels
US20110123386A1 (en) * 2009-11-26 2011-05-26 Rolls-Royce Plc Method of manufacturing a multiple composition component
US20120279067A1 (en) * 2011-05-04 2012-11-08 General Electric Company Components and processes of producing components with regions having different grain structures

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5161950A (en) * 1989-10-04 1992-11-10 General Electric Company Dual alloy turbine disk
US6660110B1 (en) 2002-04-08 2003-12-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Heat treatment devices and method of operation thereof to produce dual microstructure superalloy disks
US20060260126A1 (en) * 2005-05-17 2006-11-23 General Electric Company Method for making a compositionally graded gas turbine disk
US20070081912A1 (en) * 2005-10-11 2007-04-12 Honeywell International, Inc. Method of producing multiple microstructure components
US7895874B2 (en) 2008-01-03 2011-03-01 General Electric Company Near net shape forging process for compressor and turbine wheels and turbine spacer wheels
US20110123386A1 (en) * 2009-11-26 2011-05-26 Rolls-Royce Plc Method of manufacturing a multiple composition component
US20120279067A1 (en) * 2011-05-04 2012-11-08 General Electric Company Components and processes of producing components with regions having different grain structures

Also Published As

Publication number Publication date
WO2019030211A1 (en) 2019-02-14

Similar Documents

Publication Publication Date Title
EP3611282B1 (de) Kobaltbasiertes legierungspulver
US11725267B2 (en) Methods for processing nickel-base alloys
US8147749B2 (en) Superalloy compositions, articles, and methods of manufacture
CN105695837B (zh) 一种WC‑Ni细晶硬质合金的制备方法
US5891272A (en) Nickel-base superalloy having improved resistance to abnormal grain growth
JP5398123B2 (ja) ニッケル系合金
US8357328B2 (en) Methods for processing nanostructured ferritic alloys, and articles produced thereby
EP3117934B1 (de) Ausscheidungshärtungsedelstahlpulver und gesintertes kompakt
EP2778241A1 (de) Hitzebeständige superlegierung auf nickelbasis
US8889064B2 (en) Method for preparing a nickel superalloy part, and the part thus obtained
Groh et al. Development of a new cast and wrought alloy (René 65) for high temperature disk applications
US5571345A (en) Thermomechanical processing method for achieving coarse grains in a superalloy article
US20070020135A1 (en) Powder metal rotating components for turbine engines and process therefor
EP3031938B1 (de) Kobalt - nickel - legierung
WO2019030213A1 (en) IMPROVEMENTS ASSOCIATED WITH HOT ISOSTATIC PRESSING
JP2006118016A (ja) Ｎｉ−Ｆｅ基超合金とその製造法及びガスタービン
EP3441166A1 (de) Verbesserungen an aus metalllegierungen hergestellten komponenten
EP2423342A1 (de) Geschmiedete Legierung für Dampfturbinen und Dampfturbinenrotor damit
US3702791A (en) Method of forming superalloys
JP2023505880A (ja) ニッケル系超合金
WO2020179082A1 (ja) コバルト基合金粉末、コバルト基合金焼結体およびコバルト基合金焼結体の製造方法
CN113249620B (zh) δ相强化镍基高温合金及其制备方法
KR20200094155A (ko) Ni-Cr-Co-Mo-Ti-Al 합금의 개선된 연성을 위한 열처리
EP3653322A1 (de) Gesinterte materialien aus austenitstahlpulver und turbinenelemente
JPH0665601A (ja) Ｎｉ基合金粉末

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20190814