EP1195446A1 - Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz - Google Patents

Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz Download PDF

Info

Publication number
EP1195446A1
EP1195446A1 EP00308759A EP00308759A EP1195446A1 EP 1195446 A1 EP1195446 A1 EP 1195446A1 EP 00308759 A EP00308759 A EP 00308759A EP 00308759 A EP00308759 A EP 00308759A EP 1195446 A1 EP1195446 A1 EP 1195446A1
Authority
EP
European Patent Office
Prior art keywords
percent
article
composition
tungsten
niobium
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.)
Ceased
Application number
EP00308759A
Other languages
German (de)
English (en)
Inventor
David Paul Mourer
Eric Scott Huron
Daniel Gustov Backman
Kenneth Rees Bain
Paul Leray Reynolds
John Joseph Schirra
Timothy Paul Gabb
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.)
General Electric Co
Original Assignee
General Electric Co
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=8173302&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1195446(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by General Electric Co filed Critical General Electric Co
Priority to DE60041936T priority Critical patent/DE60041936D1/de
Priority to EP06001713.4A priority patent/EP1666618B2/fr
Priority to EP00308759A priority patent/EP1195446A1/fr
Publication of EP1195446A1 publication Critical patent/EP1195446A1/fr
Ceased legal-status Critical Current

Links

Images

Classifications

    • 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%
    • 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
    • B22F3/24—After-treatment of workpieces or articles
    • 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
    • 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
    • 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
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment

Definitions

  • This invention relates to a superalloy having nickel as the major component, and, more particularly, to such a superalloy particularly useful in the production of gas turbine disks, impellers, and shafts by powder metallurgy techniques.
  • a gas turbine (jet) engine air is drawn into the front end of the engine, compressed by a shaft-mounted compressor disk, and mixed with fuel. The mixture is ignited, producing a hot exhaust gas that is passed through a turbine which provides the power to the compressor, and then exhausted rearwardly to drive the engine and the aircraft, in which it is mounted, forwardly.
  • the turbine In the axial flow jet engine, the turbine has a turbine disk which is mounted to a drive shaft, and turbine blades extending from the periphery of the turbine disk.
  • the compressor disk is mounted to its shaft, which is driven by the turbine shaft.
  • Turbine disk must carry high multiaxial loads in tension, and must exhibit good creep resistance and dwell fatigue capability as well as good fracture toughness.
  • Turbine disks for use at moderately high temperatures have in the past typically been forged, which tends to produce a degree of anisotropy in the disk. As the operating temperatures have been increased through improvements in alloy compositions, other fabrication techniques have been developed.
  • the alloy material of construction is provided in the form of fine powders. These powders are compacted together in the form of the turbine disk or shaft, usually by extrusion and isothermal forging, and then heat treated and final machined as necessary.
  • the final article is largely isotropic due to the use of the powders, and has properties determined by the composition of the powder particles and the heat treatment.
  • the present invention provides compositions of matter, articles using the compositions of matter, and processing methods for the compositions of matter that achieve improved combinations of properties in conditions experienced in aircraft gas turbine disk and shaft applications. Both dwell fatigue crack growth rate and time to creep specific amounts or elongation are improved as compared with other alloys used for these applications. This combination of improved properties is particularly advantageous for use in aircraft engines which are not operated at the temperatures required for advanced military fighter engines but which spend long periods at moderately elevated temperature in cruise conditions.
  • the selected compositions reflect careful balancing of the amounts of both the major and minor elements.
  • a composition of matter consists essentially of, in weight percent, from about 14 percent to about 23 percent cobalt, from about 11 percent to about 15 percent chromium, from about 0.5 percent to about 4 percent tantalum, from about 0.5 to about 3 percent tungsten, from about 2.7 to about 5 percent molybdenum, from about 0.015 to about 0.15 percent zirconium, from about 0.25 to about 3 percent niobium, from about 3 to about 6 percent titanium, from about 2 to about 5 percent aluminum, from 0 to about 2.5 percent rhenium, from 0 to about 2 percent vanadium, from 0 to about 2 percent iron, from 0 to about 2 percent hafnium, from 0 to about 0.1 percent magnesium, from about 0.015 to about 0.1 percent carbon, from about 0.015 percent to about 0.045 percent boron, balance nickel and impurities.
  • the ratio (percent zirconium + percent boron)/percent carbon is preferably greater than 1.0.
  • compositions of the invention are preferably prepared in powder form, and processed into articles by combinations of extrusion, hot isostatic pressing, isothermal forging, heat treating, and other operable techniques.
  • the preferred articles made with these compositions are turbine and compressor disks and shafts, and compressor impellers for gas turbine engines.
  • the articles may be heat treated, either by solution treating and ageing or by solution treating followed by a controlled cooling to below the solvus temperature to control residual stresses.
  • the articles made according to the invention exhibit a combination of low dwell fatigue crack growth rate and long creep times that are unexpectedly improved over prior materials used for the same applications.
  • compositions, articles, and methods of the present invention result in improved dwell fatigue crack growth rate and creep properties, while retaining acceptable density and other physical and mechanical properties.
  • This combination of properties is particularly advantageous for use in turbine disk applications in advanced civilian aircraft engines, where the engine has an extended operating cycle at elevated temperature, but where the temperature requirements of the engine are not as great as in military aircraft.
  • Figure 1A shows a turbine disk 20
  • Figure 1B shows a compressor impeller 22
  • Figure 2 shows a turbine shaft 24 used in a gas turbine engine, each of which may be made by the approach of the invention.
  • a compressor disk has an appearance which is generally similar to that of a turbine disk
  • a compressor shaft has an appearance which is generally similar to that of a turbine shaft.
  • Figure 3 depicts a method of fabricating articles such as those of Figures 1 and 2.
  • a metallic composition of matter is furnished, numeral 30.
  • the composition of matter of the present invention is, in weight percent, from about 14 percent to about 23 percent cobalt, from about 11 percent to about 15 percent chromium, from about 0.5 percent to about 4 percent tantalum, from about 0.5 to about 3 percent tungsten, from about 2.7 to about 5 percent molybdenum, from about 0.015 to about 0.15 percent zirconium, from about 0.25 to about 3 percent niobium, from about 3 to about 6 percent titanium, from about 2 to about 5 percent aluminum, from 0 to about 2.5 percent rhenium, from 0 to about 2 percent vanadium, from 0 to about 2 percent iron, from 0 to about 2 percent hafnium, from 0 to about 0.1 percent magnesium from about 0.015 to about 0.1 percent carbon, from about 0.015 percent to about 0.045 percent boron, balance nickel and impurities.
  • This alloy composition produces a gamma/gamma prime microstructure, which may be controlled through heat treatments, with minor amounts of other phases present such as borides and carbides.
  • the gamma prime phase is present in an amount, based on calculation, of from about 47 to about 55 volume percent of the total volume of the material, in order to produce the desirable properties of the alloy.
  • the types and amounts of the elements in the alloy composition are chosen in cooperation with each other to achieve the desired properties, based upon testing and the analysis undertaken by the inventors. Due to the interaction between the elements, the experimental compositions defined the trends for alloying, but only limited ranges of alloy compositions exhibit the final effects of compositional influences, microstructures, and resulting properties. Together the alloying trends and the absolute elemental levels define the preferred ranges of compositions. The effects of individual elements and the results of their amounts in the alloys falling outside the indicated ranges may be summarized as follows.
  • the cobalt level is selected to control the gamma prime solvus temperature. Increasing amounts of cobalt lower the gamma prime solvus temperature, which is desirable to achieve a large processing temperature range and reduce the stresses induced by controlled cooling or quenching of the alloy used to define a portion of the gamma prime distribution and the preferred combination of mechanical properties. If the amount of cobalt is substantially less than that indicated, the gamma prime solvus temperature is too high and there is a risk of incipient melting or thermally induced porosity. If the cobalt content is substantially greater than that indicated, the alloy has an undesirably higher elemental cost.
  • chromium is beneficial to oxidation resistance, corrosion resistance, and fatigue crack growth resistance. If the amount of chromium present is substantially less than that indicated, these properties may suffer. If it is substantially more than that indicated, there may be alloy, chemical, or phase instability during extended exposure to elevated temperatures, and creep performance suffers.
  • the control of the refractory elements tantalum, tungsten, niobium, and molybdenum is important to achieving the balance required in the alloy and articles of the invention.
  • Tantalum whose presence and percentage content of tantalum is important to achieving the beneficial results obtained for the alloys of the invention, primarily enters the gamma-prime phase and has the effect of improving the stability of the gamma-prime phase and improving the creep resistance and fatigue crack growth resistance of the alloy. If the tantalum content is substantially lower than these amounts, the creep life of the alloy is reduced and the dwell fatigue crack growth resistance is insufficient. Increasing the tantalum substantially above the indicated amounts has the undesirable effect of raising the gamma-prime solvus temperature so as to reduce the processibility of the alloy and increase its density.
  • Tungsten and niobium are two relatively dense elements which function together to achieve synergistic positive results with respect to creep capability.
  • Figure 4 shows the time for a standard tensile specimen to creep to 0.2 percent elongation at 1200°F and under a load of 115,000 pounds per square inch. With less than about 0.5 weight percent tungsten and less than about 0.25 weight percent niobium, or with one or the other of the two elements present but not both, the creep properties are relatively poor. If both tungsten and niobium are present above these indicated minimum limits, the creep properties are markedly better.
  • Tungsten enters the matrix as a solid-solution strengthening element, and also aids in forming gamma prime precipitates. If the amount of tungsten is substantially less than that indicated, the creep properties may be insufficient. However, tungsten is relatively dense and also can lead to notch sensitivity and chemical instability. If the amount of tungsten is substantially greater than that indicated, the density of the alloy is too high, and, in addition, notch sensitivity is enhanced and chemical instability is of concern.
  • niobium is relatively dense and also can lead to notch sensitivity, chemical instability, and loss of dwell fatigue crack growth capability. If the amount of niobium is substantially greater than that indicated, the density of the alloy is too high, and, in addition, notch sensitivity is enhanced and chemical instability and reduced dwell fatigue crack growth capability are of concern.
  • Molybdenum is another relatively dense refractory element that partitions primarily to the gamma phase and has a beneficial effect on creep capability. If the. amount of molybdenum is substantially less than about 2.7 weight percent, the creep capability of the material may be reduced below desirable levels. If the amount of molybdenum is greater than about 5 weight percent, alloy stability is reduced and alloy density is increased above the desired level.
  • Titanium is a relatively light element and therefore may be added more freely to the alloy, from a density standpoint, to contribute to gamma prime formation. If titanium is present in an amount substantially less than that indicated, the tensile and dwell fatigue crack growth properties may be insufficient. If titanium is present in an amount substantially greater than that indicated, the heat treat window may be unacceptably reduced because the gamma prime solvus temperature is raised excessively. Substantially greater titanium levels may also stabilize or produce undesirable phases such as eta phase, which ties up the titanium and prevents it from participating in the production of the desired gamma prime microstructure.
  • Aluminum is present to contribute to gamma prime phase formation and to promote gamma prime phase stability.
  • Aluminum is the lowest-density gamma prime forming element and offsets the presence of higher-density elements. If aluminum is present in an amount substantially less than or greater than that indicated, then too little or too much of the gamma prime phase is present, and the stability of the alloy is adversely affected.
  • Carbon is present to aid in controlling grain size of the alloy. If the carbon content is substantially less than that indicated, the grain size of the alloy tends to grow too large, particularly during supersolvus processing. However, if the carbon content is substantially greater than that indicated, the carbon may have an adverse effect on the fracture properties of the alloy through premature failure. The higher carbon content also adversely affects the dwell fatigue crack growth resistance and creep capability.
  • Boron in moderate amounts improves the dwell fatigue crack growth resistance. If the boron is substantially less than that indicated, the alloy has insufficient dwell fatigue crack growth resistance. However, boron in an amount substantially greater than that indicated tends to cause residual porosity or thermally induced porosity and incipient melting during processing, and to reduce creep capability.
  • Zirconium is present in an amount of from about 0.015 percent to about 0.15 percent, more preferably from about 0.35 to about 0.055 percent, and most preferably from about 0.04 to about 0.05 percent.
  • the presence of zirconium in controlled small amounts improves the elongation and ductility of the alloy, and also reduces the crack growth rate.
  • Zirconium in amounts substantially in excess of the indicated levels tends to increase the creep rate of the alloy.
  • the ratio (percent zirconium + percent boron)/percent carbon is preferably greater than 1.0. As this ratio increases, the dwell fatigue crack growth rate decreases. As shown in Figure 5, for lesser values of this ratio, the dwell fatigue crack growth rate increases to an unacceptably high value of more than about 10 -6 inches per second in testing at 1300°F, at a maximum stress intensity K max of 30 KSI (inch) 1/2 .
  • rhenium in an amount up to about 2.5 percent by weight, magnesium in an amount up to about 0.1 percent by weight, vanadium in an amount up to about 2 percent by weight, iron in an amount up to about 2 percent by weight, and hafnium in an amount up to about 2 percent by weight may be present without adversely affecting the properties.
  • the hafnium may improve the dwell fatigue crack growth rate but with a slight negative effect on low cycle fatigue.
  • the composition is, in weight percent, from about 16 percent to about 20 percent cobalt, from about 11 percent to about 15 percent chromium, from about 2 percent to about 4 percent tantalum, from 0.5 to about 3 percent tungsten, from about 3 to about 5 percent molybdenum, from about 0.015 to about 0.15 percent zirconium, from 1 to about 3 percent niobium, from about 2.6 to about 4.6 percent titanium, from about 2.6 to about 4.6 percent aluminum, from 0 to about 2.5 percent rhenium, from 0 to about 2 percent vanadium, from 0 to about 2 percent iron, from 0 to about 2 percent hafnium, from 0 to about 0.1 percent magnesium from about 0.015 to about 0.1 percent carbon, from about 0.015 percent to about 0.045 percent boron, balance nickel and impurities.
  • alloy ME1-16 has a composition of, in weight percent, about 18.2 percent cobalt, about 13.1 percent chromium, about 2.7 percent tantalum, about 1.9 percent tungsten, about 3.8 percent molybdenum, about 0.050 percent zirconium, about 1.4 percent niobium, about 3.5 percent titanium, about 3.5 percent aluminum, about 0.030 percent carbon, about 0.030 percent boron, balance nickel and impurities.
  • the composition is, in weight percent, from about 16 percent to about 20 percent cobalt, from about 11 percent to about 15 percent chromium, from about 0.5 percent to about 2 percent tantalum, from 0.5 to about 3 percent tungsten, from about 3 to about 5 percent molybdenum, from about 0.015 to about 0.15 percent zirconium, from about 0.25 to about 1.5 percent niobium, from about 4.3 to about 5.8 percent titanium, from about 2.4 to about 4.4 percent aluminum, from 0 to about 2.5 percent rhenium, from 0 to about 2 percent vanadium, from 0 to about 2 percent iron, from 0 to about 2 percent hafnium, from 0 to about 0.1 percent magnesium from about 0.015 to about 0.1 percent carbon, from about 0.015 percent to about 0.045 percent boron, balance nickel and impurities.
  • alloy ME1-12 has a composition of, in weight percent, about 18.0 percent cobalt, about 13.3 percent chromium, about 1.0 percent tantalum, about 1.9 percent tungsten, about 3.8 percent molybdenum, about 0.050 percent zirconium, about 0.5 percent niobium, about 5.1 percent titanium, about 3.3 percent aluminum, about 0.040 percent carbon, about 0.025 percent boron, balance nickel and impurities.
  • the composition is, in weight percent, from about 17.8 percent to about 22.2 percent cobalt, from about 11 percent to about 15 percent chromium, from about 1 percent to about 3 percent tantalum, from about 1.4 to about 2.5 percent tungsten, from about 2.8 to about 4.8 percent molybdenum, from about 0.015 to about 0.15 percent zirconium, from about 0.8 to about 1.5 percent niobium, from about 3.1 to about 4.3 percent titanium, from about 3.1 to about 4.3 percent aluminum, from 0 to about 2.5 percent rhenium, from 0 to about 2 percent vanadium, from 0 to about 2 percent iron, from 0 to about 2 percent hafnium, from 0 to about 0.1 percent magnesium from about 0.015 to about 0.1 percent carbon, from about 0.015 percent to about 0.045 percent boron, balance nickel and impurities.
  • a specific most preferred alloy within this third preferred range has a composition, in weight percent, of about 20 percent cobalt, about 13 percent chromium, about 2 percent tantalum, about 2 percent tungsten, about 3.8 percent molybdenum, about 0.050 percent zirconium, about 1.2 percent niobium, about 3.7 percent titanium, about 3.7 percent aluminum, about 0.05 percent carbon, about 0.03 percent boron, balance nickel and impurities.
  • compositions are a result of the selection of the combination of elements, not any one element in isolation.
  • the more preferred and most preferred compositions yield progressively improved results than the broad composition within the operable range, but it is also possible to attain improved results by combining the narrowed composition ranges of some elements producing improved results with the broader composition ranges of other elements.
  • the alloy composition is formed into a powder, numeral 32, by any operable technique. Gas or vacuum atomization is preferred.
  • the powder particles are preferably finer than -60 mesh, and most preferably -140 mesh or -270 mesh.
  • the powder is consolidated to a billet or forging preform shape and then subsequently deformed to a final shape, numeral 34.
  • the preferred approach to consolidation is extrusion processing at an extrusion temperature of from about 1850°F to about 2025°F, and a 3:1 to 6:1 extrusion ratio.
  • the alloy is deformed to a shaped contour oversize to, but approximating the outline of, the final part.
  • the deformation step is preferably accomplished by isothermal forging in a strain-controlled mode.
  • the consolidation, deformation, and a subsequent supersolvus solution heat treatment are preferably selected to yield a grain size of from about ASTM 2 to about ASTM 8, preferably from about ASTM 5 to about ASTM 8.
  • the consolidation, deformation, and a subsequent subsolvus solution heat treatment are selected to yield a grain size of from about ASTM 9 to about ASTM 12, preferably from about ASTM 10 to about ASTM 12.
  • the extruded article is heat treated, numeral 36, to produce the desired microstructure.
  • the article is solution heat treated by heating to a supersolvus temperature, such as from about 2100°F to about 2225°F for a period of time sufficient that the entire article reaches this temperature range.
  • the solution-treated article is quenched (cooled) to room temperature by a fan air cool, optionally followed by an oil quench.
  • the solution-treated-and-quenched article is then aged by reheating to a temperature below the solvus temperature, preferably from about 1350°F to about 1500°F, for a time of about 8 hours.
  • the article may be stress relieved by heating it to a stress-relieving temperature of from about 1500°F to about 1800°F, most preferably about 1550°F for 4 hours, either after the quenching step and before the aging step, or after the final age step.
  • the article is solution treated at a partial subsolvus solution-treating temperature of from about 2000°F to about 2100°F, quenched as described above and aged, or cooled, stress relieved and aged, as described above.
  • the article is slow cooled from a supersolvus solution temperature at rates of less than 500°F per hour to a subsolvus temperature.
  • the article is then quenched as described above and aged, or stress relieved and aged, as described above.
  • Figure 6 illustrates data for dwell fatigue crack growth rates, performed at a temperature of 1300°F, with a ratio R of minimum to maximum stress during fatigue of 0.1, a maximum stress intensity K max of 30 KSI (inch) 1/2 , and a dwell period of two hours between loading to maximum load and unloading.
  • Figure 6 also illustrates data for the time for reach 0.2 percent creep when measured at 1200°F and a stress of 115,000 pounds per square inch.
  • compositions of the present invention achieve significantly improved dwell fatigue crack growth rates and improved creep times, as compared with conventional alloys.
  • data is presented for IN100 and Rene 88DT, standard disk and shaft alloys.
  • Alloy ME 1-16 is within the scope of the first preferred embodiment of the present invention discussed above, alloy ME1-12 is within the scope of the second preferred embodiment, and alloy ME2 is within the scope of the third preferred embodiment.
  • Alloy CH98 is the preferred composition disclosed in US Patent 5,662,749.
  • the alloys of the present invention achieve an improvement of approximately a factor of 50 over IN100 in creep life and approximately a factor of 200 over Rene 88DT in dwell fatigue crack growth rate.
  • the alloys of the present invention have about the same dwell fatigue crack growth performance as alloy CH98, and exhibit substantially improved creep life over alloy CH98.
  • the present alloys provide a level of enhanced performance for both dwell fatigue crack growth rate and time to creep that is desirable for articles such as gas turbine disks and shafts that are subjected to both types of loading during service.

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)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP00308759A 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz Ceased EP1195446A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE60041936T DE60041936D1 (de) 2000-10-04 2000-10-04 Ni-basis-Superlegierung und ihre Verwendung als Gasturbinen-Scheiben, -Wellen und -Laufräder
EP06001713.4A EP1666618B2 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz
EP00308759A EP1195446A1 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00308759A EP1195446A1 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP06001713.4A Division EP1666618B2 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz

Publications (1)

Publication Number Publication Date
EP1195446A1 true EP1195446A1 (fr) 2002-04-10

Family

ID=8173302

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06001713.4A Expired - Lifetime EP1666618B2 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz
EP00308759A Ceased EP1195446A1 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06001713.4A Expired - Lifetime EP1666618B2 (fr) 2000-10-04 2000-10-04 Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz

Country Status (2)

Country Link
EP (2) EP1666618B2 (fr)
DE (1) DE60041936D1 (fr)

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005052198A2 (fr) * 2003-08-29 2005-06-09 Honeywell International, Inc. Superalliage de la metallurgie des poudres haute temperature avec la resistance amelioree a la rupture par fatigue et fluage
WO2005056852A2 (fr) * 2003-09-30 2005-06-23 General Electric Company Alliages contenant du nickel, leur procede de production et les articles derives de ces alliages
WO2005103310A1 (fr) * 2003-12-19 2005-11-03 Honeywell International Inc. Superalliage refractaire de la metallurgie des poudres presentant une resistance amelioree a la fatigue et au fluage
US6974508B1 (en) 2002-10-29 2005-12-13 The United States Of America As Represented By The United States National Aeronautics And Space Administration Nickel base superalloy turbine disk
EP1710322A1 (fr) 2005-03-30 2006-10-11 United Technologies Corporation Composition de superalliage à base de nickel, article, et procédé de fabrication
EP1840232A1 (fr) * 2006-03-31 2007-10-03 Snecma Alliage à base de nickel
EP1842934A1 (fr) * 2004-12-02 2007-10-10 National Institute for Materials Science Superalliage resistant a la chaleur
EP2045345A1 (fr) * 2007-10-02 2009-04-08 Rolls-Royce plc Superalliage à base de nickel
WO2009112380A1 (fr) * 2008-03-14 2009-09-17 Siemens Aktiengesellschaft Alliage à base de nickel et son utilisation, pale ou aube de turbine et turbine à gaz
US7708846B2 (en) 2005-11-28 2010-05-04 United Technologies Corporation Superalloy stabilization
EP2251446A1 (fr) * 2009-05-14 2010-11-17 General Electric Company Superalliages de cobalt-nickel et articles associés
EP2281907A1 (fr) 2009-06-30 2011-02-09 General Electric Company Superalliages à base de nickel et composants formés à partir de ceux-ci
EP2295612A1 (fr) 2009-06-30 2011-03-16 General Electric Company Procédé de contrôle et d'affinement de la grosseur de grain finale dans des superalliages à base de nickel traité par traitement thermique intermédiaire
WO2012063879A1 (fr) 2010-11-10 2012-05-18 本田技研工業株式会社 Alliage de nickel
EP2628810A1 (fr) 2012-02-14 2013-08-21 United Technologies Corporation Compositions de superalliage, articles et procédés de fabrication
EP2628811A1 (fr) 2012-02-14 2013-08-21 United Technologies Corporation Compositions de superalliage, articles et procédés de fabrication
EP2333244A3 (fr) * 2009-11-20 2014-09-17 Honeywell International Inc. Procédés de formation de composants à microstructure double
US8992699B2 (en) 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
US8992700B2 (en) 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
EP2894234A1 (fr) * 2014-01-09 2015-07-15 Rolls-Royce plc Composition d'alliage à base de nickel
EP3000728A1 (fr) * 2014-09-26 2016-03-30 Goodrich Corporation Composants de train d'atterrissage présentant des liaisons améliorées
EP3042973A1 (fr) * 2015-01-07 2016-07-13 Rolls-Royce plc Alliage de nickel
WO2016053489A3 (fr) * 2014-08-18 2016-08-18 General Electric Company Superalliages améliorés par l'ajout de zirconium
EP3231881A1 (fr) 2016-04-11 2017-10-18 United Technologies Corporation Matériau de brasage de structures hybrides
EP1524325B1 (fr) * 2003-10-15 2017-12-06 General Electric Company Procédé pour diminuer les tensions résiduelles des pièces en superalliage à base de nickel après un recuit de mise en solution
EP3421622A1 (fr) 2017-06-26 2019-01-02 United Technologies Corporation Soudage à l'état solide de superalliages à base de nickel de métallurgie des poudres à grains grossiers.
US10227678B2 (en) 2011-06-09 2019-03-12 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
US10266919B2 (en) 2015-07-03 2019-04-23 Rolls-Royce Plc Nickel-base superalloy
CN109963961A (zh) * 2016-11-16 2019-07-02 三菱日立电力系统株式会社 镍基合金高温构件的制造方法
US10793934B2 (en) 2017-05-02 2020-10-06 United Technologies Corporation Composition and method for enhanced precipitation hardened superalloys
CN111906311A (zh) * 2020-08-30 2020-11-10 中南大学 一种预防选区激光熔融镍基高温合金开裂的方法
WO2020260806A1 (fr) * 2019-06-28 2020-12-30 Safran Poudre de superalliage, piece et procede de fabrication de la piece a partir de la poudre
US11458537B2 (en) * 2017-03-29 2022-10-04 Mitsubishi Heavy Industries, Ltd. Heat treatment method for additive manufactured Ni-base alloy object, method for manufacturing additive manufactured Ni-base alloy object, Ni-base alloy powder for additive manufactured object, and additive manufactured Ni-base alloy object
CN115679157A (zh) * 2022-12-29 2023-02-03 北京钢研高纳科技股份有限公司 镍基高温合金及其制备方法和结构件
CN115747577A (zh) * 2022-11-21 2023-03-07 北京钢研高纳科技股份有限公司 涡轮盘用变形高温合金及其制备方法
US11634792B2 (en) * 2017-07-28 2023-04-25 Alloyed Limited Nickel-based alloy

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8613810B2 (en) * 2009-05-29 2013-12-24 General Electric Company Nickel-base alloy, processing therefor, and components formed thereof
WO2015100074A1 (fr) * 2013-12-27 2015-07-02 Chin Herbert A Alliage de nickel corroyé à haute résistance et haute conductivité thermique
US10280498B2 (en) 2016-10-12 2019-05-07 Crs Holdings, Inc. High temperature, damage tolerant superalloy, an article of manufacture made from the alloy, and process for making the alloy

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0372170A1 (fr) * 1988-09-28 1990-06-13 General Electric Company Superalliage à base de nickel résistant à la formation des fendillements par fatigue et produit obtenu
EP0373298A1 (fr) * 1988-09-26 1990-06-20 General Electric Company Superalliage à base de nickel résistant à la formation de criques de fatigue
US5120373A (en) * 1991-04-15 1992-06-09 United Technologies Corporation Superalloy forging process
EP0849370A1 (fr) * 1996-12-17 1998-06-24 United Technologies Corporation Objects en superalliage à base de nickel à haute résistance mechanique et avec une surface usinée

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3561955A (en) † 1966-08-30 1971-02-09 Martin Marietta Corp Stable nickel base alloy
US3589893A (en) † 1967-11-24 1971-06-29 Martin Metals Co Sulfidation resistant alloys and structures
US5328659A (en) † 1982-10-15 1994-07-12 United Technologies Corporation Superalloy heat treatment for promoting crack growth resistance
US4894089A (en) † 1987-10-02 1990-01-16 General Electric Company Nickel base superalloys
US5662749A (en) 1995-06-07 1997-09-02 General Electric Company Supersolvus processing for tantalum-containing nickel base superalloys
GB9608617D0 (en) † 1996-04-24 1996-07-03 Rolls Royce Plc Nickel alloy for turbine engine components

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0373298A1 (fr) * 1988-09-26 1990-06-20 General Electric Company Superalliage à base de nickel résistant à la formation de criques de fatigue
EP0372170A1 (fr) * 1988-09-28 1990-06-13 General Electric Company Superalliage à base de nickel résistant à la formation des fendillements par fatigue et produit obtenu
US5120373A (en) * 1991-04-15 1992-06-09 United Technologies Corporation Superalloy forging process
EP0849370A1 (fr) * 1996-12-17 1998-06-24 United Technologies Corporation Objects en superalliage à base de nickel à haute résistance mechanique et avec une surface usinée

Cited By (65)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6974508B1 (en) 2002-10-29 2005-12-13 The United States Of America As Represented By The United States National Aeronautics And Space Administration Nickel base superalloy turbine disk
WO2005052198A3 (fr) * 2003-08-29 2005-09-01 Honeywell Int Inc Superalliage de la metallurgie des poudres haute temperature avec la resistance amelioree a la rupture par fatigue et fluage
US6969431B2 (en) 2003-08-29 2005-11-29 Honeywell International, Inc. High temperature powder metallurgy superalloy with enhanced fatigue and creep resistance
WO2005052198A2 (fr) * 2003-08-29 2005-06-09 Honeywell International, Inc. Superalliage de la metallurgie des poudres haute temperature avec la resistance amelioree a la rupture par fatigue et fluage
WO2005056852A2 (fr) * 2003-09-30 2005-06-23 General Electric Company Alliages contenant du nickel, leur procede de production et les articles derives de ces alliages
WO2005056852A3 (fr) * 2003-09-30 2005-09-01 Gen Electric Alliages contenant du nickel, leur procede de production et les articles derives de ces alliages
CN1886526B (zh) * 2003-09-30 2010-09-01 通用电气公司 含镍合金、其制造方法和由其得到的制品
EP1524325B1 (fr) * 2003-10-15 2017-12-06 General Electric Company Procédé pour diminuer les tensions résiduelles des pièces en superalliage à base de nickel après un recuit de mise en solution
WO2005103310A1 (fr) * 2003-12-19 2005-11-03 Honeywell International Inc. Superalliage refractaire de la metallurgie des poudres presentant une resistance amelioree a la fatigue et au fluage
EP1842934A4 (fr) * 2004-12-02 2008-03-05 Nat Inst For Materials Science Superalliage resistant a la chaleur
EP1842934A1 (fr) * 2004-12-02 2007-10-10 National Institute for Materials Science Superalliage resistant a la chaleur
US8147749B2 (en) 2005-03-30 2012-04-03 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
EP1710322A1 (fr) 2005-03-30 2006-10-11 United Technologies Corporation Composition de superalliage à base de nickel, article, et procédé de fabrication
US7708846B2 (en) 2005-11-28 2010-05-04 United Technologies Corporation Superalloy stabilization
FR2899240A1 (fr) * 2006-03-31 2007-10-05 Snecma Sa Alliage a base de nickel
EP1840232A1 (fr) * 2006-03-31 2007-10-03 Snecma Alliage à base de nickel
EP2045345A1 (fr) * 2007-10-02 2009-04-08 Rolls-Royce plc Superalliage à base de nickel
EP2103700A1 (fr) * 2008-03-14 2009-09-23 Siemens Aktiengesellschaft Alliages à base de nickel et leur utilisateur, pale ou aube de turbine et turbine à gaz
WO2009112380A1 (fr) * 2008-03-14 2009-09-17 Siemens Aktiengesellschaft Alliage à base de nickel et son utilisation, pale ou aube de turbine et turbine à gaz
US7993101B2 (en) 2008-03-14 2011-08-09 Siemens Aktiengesellschaft Nickel base alloy and use of it, turbine blade or vane and gas turbine
CN101970702B (zh) * 2008-03-14 2012-11-28 西门子公司 镍基合金及其用途，涡轮机叶片或轮叶以及燃气涡轮机
EP2251446A1 (fr) * 2009-05-14 2010-11-17 General Electric Company Superalliages de cobalt-nickel et articles associés
JP2010275635A (ja) * 2009-05-14 2010-12-09 General Electric Co <Ge> コバルト−ニッケル超合金及び関連物品
US8349250B2 (en) * 2009-05-14 2013-01-08 General Electric Company Cobalt-nickel superalloys, and related articles
US8992700B2 (en) 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
US8992699B2 (en) 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
US9518310B2 (en) 2009-05-29 2016-12-13 General Electric Company Superalloys and components formed thereof
EP2281907A1 (fr) 2009-06-30 2011-02-09 General Electric Company Superalliages à base de nickel et composants formés à partir de ceux-ci
EP2295612A1 (fr) 2009-06-30 2011-03-16 General Electric Company Procédé de contrôle et d'affinement de la grosseur de grain finale dans des superalliages à base de nickel traité par traitement thermique intermédiaire
EP2333244A3 (fr) * 2009-11-20 2014-09-17 Honeywell International Inc. Procédés de formation de composants à microstructure double
US9216453B2 (en) 2009-11-20 2015-12-22 Honeywell International Inc. Methods of forming dual microstructure components
US8961646B2 (en) 2010-11-10 2015-02-24 Honda Motor Co., Ltd. Nickel alloy
EP2602336A4 (fr) * 2010-11-10 2014-02-19 Honda Motor Co Ltd Alliage de nickel
WO2012063879A1 (fr) 2010-11-10 2012-05-18 本田技研工業株式会社 Alliage de nickel
EP2602336A1 (fr) * 2010-11-10 2013-06-12 Honda Motor Co., Ltd. Alliage de nickel
US10227678B2 (en) 2011-06-09 2019-03-12 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
EP2628810A1 (fr) 2012-02-14 2013-08-21 United Technologies Corporation Compositions de superalliage, articles et procédés de fabrication
EP2628811A1 (fr) 2012-02-14 2013-08-21 United Technologies Corporation Compositions de superalliage, articles et procédés de fabrication
US9783873B2 (en) 2012-02-14 2017-10-10 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US9752215B2 (en) 2012-02-14 2017-09-05 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
EP2894234A1 (fr) * 2014-01-09 2015-07-15 Rolls-Royce plc Composition d'alliage à base de nickel
US10309229B2 (en) 2014-01-09 2019-06-04 Rolls-Royce Plc Nickel based alloy composition
WO2016053489A3 (fr) * 2014-08-18 2016-08-18 General Electric Company Superalliages améliorés par l'ajout de zirconium
US10767246B2 (en) 2014-08-18 2020-09-08 General Electric Company Enhanced superalloys by zirconium addition
US9452827B2 (en) 2014-09-26 2016-09-27 Goodrich Corporation Landing gear components having improved joints
EP3000728A1 (fr) * 2014-09-26 2016-03-30 Goodrich Corporation Composants de train d'atterrissage présentant des liaisons améliorées
US10138534B2 (en) 2015-01-07 2018-11-27 Rolls-Royce Plc Nickel alloy
EP3042973A1 (fr) * 2015-01-07 2016-07-13 Rolls-Royce plc Alliage de nickel
US10422024B2 (en) 2015-07-03 2019-09-24 Rolls-Royce Plc Nickel-base superalloy
US10266919B2 (en) 2015-07-03 2019-04-23 Rolls-Royce Plc Nickel-base superalloy
EP3231881A1 (fr) 2016-04-11 2017-10-18 United Technologies Corporation Matériau de brasage de structures hybrides
US11401597B2 (en) 2016-11-16 2022-08-02 Mitsubishi Heavy Industries, Ltd. Method for manufacturing nickel-based alloy high-temperature component
CN109963961A (zh) * 2016-11-16 2019-07-02 三菱日立电力系统株式会社 镍基合金高温构件的制造方法
US11021780B2 (en) 2016-11-16 2021-06-01 Mitsubishi Power, Ltd. Method for manufacturing nickel-based alloy high-temperature component
US11458537B2 (en) * 2017-03-29 2022-10-04 Mitsubishi Heavy Industries, Ltd. Heat treatment method for additive manufactured Ni-base alloy object, method for manufacturing additive manufactured Ni-base alloy object, Ni-base alloy powder for additive manufactured object, and additive manufactured Ni-base alloy object
US10793934B2 (en) 2017-05-02 2020-10-06 United Technologies Corporation Composition and method for enhanced precipitation hardened superalloys
EP3421622A1 (fr) 2017-06-26 2019-01-02 United Technologies Corporation Soudage à l'état solide de superalliages à base de nickel de métallurgie des poudres à grains grossiers.
EP3995594A1 (fr) 2017-06-26 2022-05-11 Raytheon Technologies Corporation Soudage à l'état solide de métallurgie des poudres à grains grossiers de superalliages à base de nickel
US11634792B2 (en) * 2017-07-28 2023-04-25 Alloyed Limited Nickel-based alloy
WO2020260806A1 (fr) * 2019-06-28 2020-12-30 Safran Poudre de superalliage, piece et procede de fabrication de la piece a partir de la poudre
FR3097876A1 (fr) * 2019-06-28 2021-01-01 Safran Poudre de superalliage, piece et procede de fabrication de la piece a partir de la poudre
CN111906311A (zh) * 2020-08-30 2020-11-10 中南大学 一种预防选区激光熔融镍基高温合金开裂的方法
CN115747577A (zh) * 2022-11-21 2023-03-07 北京钢研高纳科技股份有限公司 涡轮盘用变形高温合金及其制备方法
CN115747577B (zh) * 2022-11-21 2024-04-12 北京钢研高纳科技股份有限公司 涡轮盘用变形高温合金及其制备方法
CN115679157A (zh) * 2022-12-29 2023-02-03 北京钢研高纳科技股份有限公司 镍基高温合金及其制备方法和结构件

Also Published As

Publication number Publication date
DE60041936D1 (de) 2009-05-14
EP1666618B1 (fr) 2009-04-01
EP1666618A1 (fr) 2006-06-07
EP1666618B2 (fr) 2015-06-03

Similar Documents

Publication Publication Date Title
EP1666618B1 (fr) Superalliage à base Ni et son utilisation comme disques, arbres et rotors de turbines à gaz
US6521175B1 (en) Superalloy optimized for high-temperature performance in high-pressure turbine disks
JP6576379B2 (ja) チタン−アルミニウム基合金から成る部材の製造方法及び部材
JP3010050B2 (ja) 耐疲労亀裂進展性のニッケル基物品および合金並びに製造方法
EP1842934B1 (fr) Superalliage resistant a la chaleur
JP4287991B2 (ja) ＴｉＡｌ基合金及びその製造方法並びにそれを用いた動翼
JP3944271B2 (ja) ニッケル基超合金における結晶粒度の制御
JP5398123B2 (ja) ニッケル系合金
US10526689B2 (en) Heat-resistant Ti alloy and process for producing the same
US5746846A (en) Method to produce gamma titanium aluminide articles having improved properties
US6974508B1 (en) Nickel base superalloy turbine disk
EP1201777B1 (fr) Superalliage optimalise pour performance a haute temperature dans disques de turbine a haute pression
US10422024B2 (en) Nickel-base superalloy
US10309229B2 (en) Nickel based alloy composition
US5571345A (en) Thermomechanical processing method for achieving coarse grains in a superalloy article
EP0388527A1 (fr) Alliages du type aluminiure de titane
JP6315319B2 (ja) Ｆｅ−Ｎｉ基超耐熱合金の製造方法
EP3572541B1 (fr) Superalliage à base de nickel
JP5645054B2 (ja) アニーリングツインを含有するニッケル基耐熱超合金と耐熱超合金部材
US7138020B2 (en) Method for reducing heat treatment residual stresses in super-solvus solutioned nickel-base superalloy articles
JP7233659B2 (ja) 熱間鍛造用のチタンアルミナイド合金材及びチタンアルミナイド合金材の鍛造方法並びに鍛造体
WO2017123186A1 (fr) Alliages à base de titane/aluminium ayant une meilleure résistance au fluage par renforcement de la phase gamma
CN115466867B (zh) 一种能够改善其均匀变形能力的TiAl合金及其制备方法
WO2015182454A1 (fr) ALLIAGE DE MOULAGE À BASE DE TiAl ET SON PROCÉDÉ DE PRODUCTION
GB2457998A (en) A method of working titanium alloys

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

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

Kind code of ref document: A1

Designated state(s): DE FR GB IT

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20021010

AKX Designation fees paid

Free format text: DE FR GB IT

17Q First examination report despatched

Effective date: 20030211

APBN Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2E

APBR Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3E

APBK Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNE

APAF Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNE

APBT Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9E

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

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20060131