US20100008790A1 - Superalloy compositions, articles, and methods of manufacture - Google Patents

Superalloy compositions, articles, and methods of manufacture Download PDF

Info

Publication number
US20100008790A1
US20100008790A1 US11/095,092 US9509205A US2010008790A1 US 20100008790 A1 US20100008790 A1 US 20100008790A1 US 9509205 A US9509205 A US 9509205A US 2010008790 A1 US2010008790 A1 US 2010008790A1
Authority
US
United States
Prior art keywords
percent
disk
gas turbine
turbine engine
powder metallurgical
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US11/095,092
Other languages
English (en)
Inventor
Paul L. Reynolds
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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=36676454&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20100008790(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: REYNOLDS, PAUL L.
Priority to US11/095,092 priority Critical patent/US20100008790A1/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to TW095102250A priority patent/TW200639260A/zh
Priority to CA002533574A priority patent/CA2533574A1/en
Priority to AU2006200325A priority patent/AU2006200325A1/en
Priority to SG200600555A priority patent/SG126026A1/en
Priority to KR1020060008606A priority patent/KR100810838B1/ko
Priority to EP06250464.2A priority patent/EP1710322B1/en
Priority to CNA2006100592457A priority patent/CN1840719A/zh
Priority to JP2006019930A priority patent/JP4498282B2/ja
Priority to KR1020070119568A priority patent/KR20070114689A/ko
Priority to US12/623,862 priority patent/US8147749B2/en
Publication of US20100008790A1 publication Critical patent/US20100008790A1/en
Assigned to DEPARTMENT OF THE NAVY reassignment DEPARTMENT OF THE NAVY CONFIRMATORY LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Abandoned 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
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • 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
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel

Definitions

  • the invention relates to nickel-base superalloys. More particularly, the invention relates to such superalloys used in high-temperature gas turbine engine components such as turbine disks and compressor disks.
  • Blades are typically cast and some blades include complex internal features.
  • U.S. Pat. Nos. 3,061,426, 4,209,348, 4,569,824, 4,719,080, 5,270,123, 6,355,117, and 6706241 disclose various blade alloys.
  • One aspect of the invention involves a nickel-base composition of matter having a relatively high concentration of tantalum coexisting with a relatively high concentration of one or more other components.
  • the alloy may be used to form turbine disks via powder metallurgical processes.
  • the one or more other components may include cobalt.
  • the one or more other components may include combinations of gamma prime ( ⁇ ′) formers and/or eta ( ⁇ ) formers.
  • FIG. 1 is an exploded partial view of a gas turbine engine turbine disk assembly.
  • FIG. 2 is a flowchart of a process for preparing a disk of the assembly of FIG. 1 .
  • FIG. 3 is a table of compositions of an inventive disk alloy and of prior art alloys.
  • FIG. 4 is an etchant-aided optical micrograph of a disk alloy of FIG. 3 .
  • FIG. 5 is an etchant-aided scanning electron micrograph (SEM) of the disk alloy of FIG. 3 .
  • FIG. 6 is a table of select measured properties of the disk alloy and prior art alloys of FIG. 3 .
  • FIG. 1 shows a gas turbine engine disk assembly 20 including a disk 22 and a plurality of blades 24 .
  • the disk is generally annular, extending from an inboard bore or hub 26 at a central aperture to an outboard rim 28 .
  • a relatively thin web 30 is radially between the bore 26 and rim 28 .
  • the periphery of the rim 28 has a circumferential array of engagement features 32 (e.g., dovetail slots) for engaging complementary features 34 of the blades 24 .
  • the disk and blades may be a unitary structure (e.g., so-called “integrally bladed” rotors or disks).
  • the disk 22 is advantageously formed by a powder metallurgical forging process (e.g., as is disclosed in U.S. Pat. No. 6,521,175).
  • FIG. 2 shows an exemplary process.
  • the elemental components of the alloy are mixed (e.g., as individual components of refined purity or alloys thereof).
  • the mixture is melted sufficiently to eliminate component segregation.
  • the melted mixture is atomized to form droplets of molten metal.
  • the atomized droplets are cooled to solidify into powder particles.
  • the powder may be screened to restrict the ranges of powder particle sizes allowed.
  • the powder is put into a container.
  • the container of powder is consolidated in a multi-step process involving compression and heating.
  • the resulting consolidated powder then has essentially the full density of the alloy without the chemical segregation typical of larger castings.
  • a blank of the consolidated powder may be forged at appropriate temperatures and deformation constraints to provide a forging with the basic disk profile.
  • the forging is then heat treated in a multi-step process involving high temperature heating followed by a rapid cooling process or quench.
  • the heat treatment increases the characteristic gamma ( ⁇ ) grain size from an exemplary 10 ⁇ m or less to an exemplary 20-120 ⁇ m (with 30-60 ⁇ m being preferred).
  • the quench for the heat treatment may also form strengthening precipitates (e.g., gamma prime ( ⁇ ′) and eta ( ⁇ ) phases discussed in further detail below) of a desired distribution of sizes and desired volume percentages.
  • strengthening precipitates e.g., gamma prime ( ⁇ ′) and eta ( ⁇ ) phases discussed in further detail below
  • ⁇ ′ gamma prime
  • ⁇ eta
  • the increased grain size is associated with good high-temperature creep-resistance and decreased rate of crack growth during the service of the manufactured forging.
  • the heat treated forging is then subject to machining of the final profile and the slots.
  • Ta tantalum
  • the inventive alloys have a higher level.
  • This level of Ta is believed unique among disk alloys. More specifically, levels above 3% Ta combined with relatively high levels of other ⁇ ′ formers (namely, one or a combination of aluminum (Al), titanium (Ti), niobium (Nb), tungsten (W), and hafnium (Hf)) and relatively high levels of cobalt (Co) are believed unique.
  • the Ta serves as a solid solution strengthening additive to the ⁇ ′ and to the ⁇ . The presence of the relatively large Ta atoms reduces diffusion principally in the ⁇ ′ phase but also in the ⁇ . This may reduce high-temperature creep.
  • a Ta level above 6% in the inventive alloys is also believed to aid in the formation of the ⁇ phase and insure that these are relatively small compared with the ⁇ grains.
  • the ⁇ precipitate may help in precipitation hardening similar to the strengthening mechanisms obtained by the ⁇ ′ precipitate phase.
  • inventive alloys to the modern blade alloys. Relatively high Ta contents are common to modern blade alloys. There may be several compositional differences between the inventive alloys and modern blade alloys.
  • the blade alloys are typically produced by casting techniques as their high-temperature capability is enhanced by the ability to form very large polycrystalline and/or single grains (also known as single crystals). Use of such blade alloys in powder metallurgical applications is compromised by the formation of very large grain size and their requirements for high-temperature heat treatment. The resulting cooling rate would cause significant quench cracking and tearing (particularly for larger parts).
  • those blade alloys have a lower cobalt (Co) concentration than the exemplary inventive alloys.
  • the exemplary inventive alloys have been customized for utilization in disk manufacture through the adjustment of several other elements, including one or more of Al, Co, Cr, Hf, Mo, Nb, Ti, and W. Nevertheless, possible use of the inventive alloys for blades, vanes, and other non-disk components can't be excluded.
  • a high-Ta disk alloy having improved high temperature properties e.g., for use at temperatures of 1200-1500° F. (649-816° C.) or greater.
  • metric is a conversion from the English (e.g., an English measurement) and should not be regarded as indicating a false degree of precision.
  • Table I of FIG. 3 shows a specification for one exemplary alloy or group of alloys.
  • the nominal composition and nominal limits were derived based upon sensitivities to elemental changes (e.g., derived from phase diagrams).
  • the table also shows a measured composition of a test sample.
  • the table also shows nominal compositions of the prior art alloys NF3 and ME16 (discussed, e.g., in U.S. Pat. No. 6,521,175 and EP1195446, respectively). Except where noted, all contents are by weight and specifically in weight percent.
  • Ni 3 Ti The most basic ⁇ form is Ni 3 Ti. It has generally been believed that, in modern disk and blade alloys, ⁇ forms when the Al to Ti weight ratio is less than or equal to one. In the exemplary alloy, this ratio is greater than one. From compositional analysis of the n phase, it appears that Ta significantly contributes to the formation of the ⁇ phase as Ni 3 (Ti, Ta). A different correlation (reflecting more than Al and Ti) may therefore be more appropriate. Utilizing standard partitioning coefficients one can estimate the total mole fraction (by way of atomic percentages) of the elements that substitute for atomic sites normally occupied by Al. These elements include Hf, Mo, Nb, Ta, Ti, V, W and, to a smaller extent, Cr. These elements act as solid solution strengtheners to the ⁇ ′ phase.
  • ⁇ will form when the molar ratio of Al atoms to the sum of the other atoms that partition to the Al site in ⁇ ′ is less than or equal to about 0.79-0.81. This is particularly significant in concert with the high levels of Ta. Nominally, for NF3 this ratio is 0.84 and the Al to Ti weight percent ratio is 1.0. For test samples of NF3 these were observed as 0.82 and 0.968, respectively.
  • the ⁇ phase would be predicted in NF3 by the conventional wisdom Al to Ti ratio but has not been observed.
  • ME16 has similar nominal values of 0.85 and 0.98, respectively, and also does not exhibit the ⁇ phase as would be predicted by the Al to Ti ratio.
  • ⁇ formation and quality thereof are believed particularly sensitive to the Ti and Ta contents. If the above-identified ratio of Al to its substitutes is satisfied, there may be a further approximate predictor for the formation of ⁇ . It is estimated that ⁇ will form if the Al content is less than or equal to about 3.5%, the Ta content is greater than or equal to about 6.35%, the Co content is greater than or equal to about 16%, the Ti content is greater than or equal to about 2.25%, and, perhaps most significantly, the sum of Ti and Ta contents is greater than or equal to about 8.0%.
  • the Ta has a particular effect on controlling the size of the ⁇ precipitates.
  • a ratio of Ta to Ti contents of at least about three may be effective to control ⁇ precipitate size for advantageous mechanical properties.
  • FIGS. 4 and 5 show microstructure of the sample composition reflecting atomization to powder of about 74 ⁇ m (0.0029 inch) and smaller size, followed by compaction, forging, and heat treatment at 1182° C. (2160° F.) for two hours and a 0.93-1.39° C./s (56-83° C./minute (100-150° F./minute)) quench.
  • FIG. 4 shows ⁇ precipitates 100 as appearing light colored within a ⁇ matrix 102 .
  • An approximate grain size is 30 ⁇ m.
  • FIG. 5 shows the matrix 102 as including much smaller ⁇ ′ precipitates 104 in a ⁇ matrix 106 .
  • These micrographs show a substantially uniform distribution of the ⁇ phase.
  • the ⁇ phase is no larger than the ⁇ grain size so that it may behave as a strengthening phase without the detrimental influence on cyclic behavior that would occur if the ⁇ phase were significantly larger.
  • FIG. 5 shows the uniformity of the ⁇ ′ precipitates. These precipitates and their distribution contribute to precipitation strengthening. Control of precipitate size (coarsening) and spacing may be used to control the degree and character of precipitate strengthening. Additionally, along the ⁇ interface is a highly ordered/aligned region 108 of smaller ⁇ ′ precipitates. These regions 108 may provide further impediments to dislocation motion. The impediment is a substantial component of strengthening against time-dependent deformation, such as creep. The uniformity of the distribution and very fine size of the ⁇ ′ in the region 108 indicates this is formed well below the momentary temperatures found during quenching.
  • Alloys with a high ⁇ ′ content have been generally regarded as difficult to weld. This difficulty is due to the sudden cooling from the welding (temporary melting) of the alloy. The sudden cooling in high ⁇ ′ alloys causes large internal stresses to build up in the alloy leading to cracking.
  • the one particular ⁇ precipitate enlarged in FIG. 5 has an included carbide precipitate 120 .
  • the carbide is believed primarily a titanium and/or tantalum carbide which is formed during the solidification of the powder particles and is a natural by-product of the presence of carbon.
  • the carbon serves to strengthen grain boundaries and avoid brittleness.
  • Such carbide particles are extremely low in volume fraction, extremely stable because of their high melting points and believed not to substantially affect properties of the alloy.
  • ⁇ phase is approximately 2-14 ⁇ m long in a field of 0.2 ⁇ m cooling ⁇ ′ and an average grain diameter (for the ⁇ ) of 30-45 ⁇ m. This size is approximately the size of large ⁇ ′ precipitates as found in conventional powder metallurgy alloys such as IN100 and ME16. Testing to date has indicated no detrimental results (e.g., no loss of notch ductility and rupture life).
  • Table II of FIG. 6 shows select mechanical properties of the exemplary alloy and prior art alloys. All three alloys were heat treated to a grain size of nominal ASTM 6.5 (a diameter of about 37.8 ⁇ m (0.0015 inch)). All data were taken from similarly processed subscale material (i.e., heat treated above the ⁇ ′ solvus to produce the same grain size and cooled at the same rate). The data show a most notable improvement in quench crack resistance for the inventive alloys. It is believed that the very fine distribution of ⁇ ′ in the region 108 around the ⁇ precipitate (which ⁇ ′ precipitates do not form until very low temperatures are reached during the quench cycle) are participating in the improved resistance to quench cracking. A lack of this ⁇ ′ around the ⁇ might encourage the redistribution of the stresses during the quench cycle to ultimately cause cracking.
  • the sample composition has significant improvements at 816° C. (1500° F.) in time dependent (creep and rupture) capability and yield and ultimate tensile strengths. At 732° C. (1350° F.) the sample composition has slightly lower yield strength than NF3 but still significantly better than ME16. Further gains in these properties might be achieved with further composition and processing refinements.
  • Alternative alloys with lower Ta contents and/or a lack of n precipitates may still have some advantageous high temperature properties.
  • lower Ta contents in the 3-6% range or, more narrowly the 4-6% range are possible.
  • the sum of Ti and Ta contents would be approximately 5-9%.
  • Other contents could be similar to those of the exemplary specification (thus likely having a slightly higher Ni content).
  • such alloys may also be distinguished by high Co and high combined Co and Cr contents.
  • Exemplary combined Co and Cr contents are at least 26.0% for the lower Ta alloys and may be similar or broader (e.g., 20.0% or 22.0%) for the higher Ta alloys.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/095,092 2005-03-30 2005-03-30 Superalloy compositions, articles, and methods of manufacture Abandoned US20100008790A1 (en)

Priority Applications (11)

Application Number Priority Date Filing Date Title
US11/095,092 US20100008790A1 (en) 2005-03-30 2005-03-30 Superalloy compositions, articles, and methods of manufacture
TW095102250A TW200639260A (en) 2005-03-30 2006-01-20 Superalloy compositions, articles, and methods of manufacture
CA002533574A CA2533574A1 (en) 2005-03-30 2006-01-23 Superalloy compositions, articles, and methods of manufacture
AU2006200325A AU2006200325A1 (en) 2005-03-30 2006-01-25 Superalloy compositions, articles, and methods of manufacture
SG200600555A SG126026A1 (en) 2005-03-30 2006-01-26 Superalloy compositions, articles, and methods of manufacture
KR1020060008606A KR100810838B1 (ko) 2005-03-30 2006-01-27 초합금 조성물, 제품 및 그 제조 방법
EP06250464.2A EP1710322B1 (en) 2005-03-30 2006-01-27 Nickel based superalloy compositions, articles, and methods of manufacture
CNA2006100592457A CN1840719A (zh) 2005-03-30 2006-01-28 超耐热合金组成、制品、及制造方法
JP2006019930A JP4498282B2 (ja) 2005-03-30 2006-01-30 超合金組成物、物品及び製造方法
KR1020070119568A KR20070114689A (ko) 2005-03-30 2007-11-22 초합금 조성물, 제품 및 그 제조 방법
US12/623,862 US8147749B2 (en) 2005-03-30 2009-11-23 Superalloy compositions, articles, and methods of manufacture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/095,092 US20100008790A1 (en) 2005-03-30 2005-03-30 Superalloy compositions, articles, and methods of manufacture

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/623,862 Continuation US8147749B2 (en) 2005-03-30 2009-11-23 Superalloy compositions, articles, and methods of manufacture

Publications (1)

Publication Number Publication Date
US20100008790A1 true US20100008790A1 (en) 2010-01-14

Family

ID=36676454

Family Applications (2)

Application Number Title Priority Date Filing Date
US11/095,092 Abandoned US20100008790A1 (en) 2005-03-30 2005-03-30 Superalloy compositions, articles, and methods of manufacture
US12/623,862 Active US8147749B2 (en) 2005-03-30 2009-11-23 Superalloy compositions, articles, and methods of manufacture

Family Applications After (1)

Application Number Title Priority Date Filing Date
US12/623,862 Active US8147749B2 (en) 2005-03-30 2009-11-23 Superalloy compositions, articles, and methods of manufacture

Country Status (9)

Country Link
US (2) US20100008790A1 (ko)
EP (1) EP1710322B1 (ko)
JP (1) JP4498282B2 (ko)
KR (2) KR100810838B1 (ko)
CN (1) CN1840719A (ko)
AU (1) AU2006200325A1 (ko)
CA (1) CA2533574A1 (ko)
SG (1) SG126026A1 (ko)
TW (1) TW200639260A (ko)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2628810A1 (en) 2012-02-14 2013-08-21 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
EP2628811A1 (en) 2012-02-14 2013-08-21 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US9377245B2 (en) 2013-03-15 2016-06-28 Ut-Battelle, Llc Heat exchanger life extension via in-situ reconditioning
US9435011B2 (en) 2013-08-08 2016-09-06 Ut-Battelle, Llc Creep-resistant, cobalt-free alloys for high temperature, liquid-salt heat exchanger systems
US9540714B2 (en) 2013-03-15 2017-01-10 Ut-Battelle, Llc High strength alloys for high temperature service in liquid-salt cooled energy systems
US9605565B2 (en) 2014-06-18 2017-03-28 Ut-Battelle, Llc Low-cost Fe—Ni—Cr alloys for high temperature valve applications
US9683280B2 (en) 2014-01-10 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9683279B2 (en) 2014-05-15 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
EP3231881A1 (en) 2016-04-11 2017-10-18 United Technologies Corporation Braze material for hybrid structures
US10017842B2 (en) 2013-08-05 2018-07-10 Ut-Battelle, Llc Creep-resistant, cobalt-containing alloys for high temperature, liquid-salt heat exchanger systems
EP3421622A1 (en) 2017-06-26 2019-01-02 United Technologies Corporation Solid-state welding of coarse grain powder metallurgy nickel-based superalloys
CN115652147A (zh) * 2022-12-29 2023-01-31 北京钢研高纳科技股份有限公司 粉末高温合金及其制备方法和应用

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP2503013B1 (en) * 2009-11-19 2017-09-06 National Institute for Materials Science Heat-resistant superalloy
US8177516B2 (en) * 2010-02-02 2012-05-15 General Electric Company Shaped rotor wheel capable of carrying multiple blade stages
CA2804402C (en) * 2010-07-09 2018-02-13 General Electric Company Nickel-base alloy, processing therefor, and components formed thereof
CN102794354A (zh) * 2011-05-26 2012-11-28 昆山市瑞捷精密模具有限公司 一种具有耐高温涂层的镍基超耐热合金冲压模具
US9034247B2 (en) * 2011-06-09 2015-05-19 General Electric Company Alumina-forming cobalt-nickel base alloy and method of making an article therefrom
US9598774B2 (en) 2011-12-16 2017-03-21 General Electric Corporation Cold spray of nickel-base alloys
US9828658B2 (en) 2013-08-13 2017-11-28 Rolls-Royce Corporation Composite niobium-bearing superalloys
US9938610B2 (en) 2013-09-20 2018-04-10 Rolls-Royce Corporation High temperature niobium-bearing superalloys
EP3090075B1 (en) 2013-12-24 2018-12-05 United Technologies Corporation Hot corrosion-protected article and manufacture method therefor
US10266958B2 (en) * 2013-12-24 2019-04-23 United Technologies Corporation Hot corrosion-protected articles and manufacture methods
US10793934B2 (en) 2017-05-02 2020-10-06 United Technologies Corporation Composition and method for enhanced precipitation hardened superalloys
FR3071255B1 (fr) * 2017-09-21 2019-09-20 Centre National De La Recherche Scientifique (Cnrs) Piece de turbine en alliage comprenant une phase max
GB2573572A (en) 2018-05-11 2019-11-13 Oxmet Tech Limited A nickel-based alloy
US11306595B2 (en) 2018-09-14 2022-04-19 Raytheon Technologies Corporation Wrought root blade manufacture methods
JP2020056106A (ja) * 2018-09-27 2020-04-09 株式会社アテクト ニッケル基合金製または鉄基合金製の耐熱部材の製造方法
DE102020116868A1 (de) * 2019-07-05 2021-01-07 Vdm Metals International Gmbh Pulver aus einer Nickel-Kobaltlegierung, sowie Verfahren zur Herstellung des Pulvers
US11786973B2 (en) 2020-12-18 2023-10-17 General Electric Company Method for manufacturing a component using an additive process

Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3061426A (en) * 1960-02-01 1962-10-30 Int Nickel Co Creep resistant alloy
US3744996A (en) * 1969-10-28 1973-07-10 Int Nickel Co Nickel base alloys of improved high temperature tensile ductility
US3865575A (en) * 1972-12-18 1975-02-11 Int Nickel Co Thermoplastic prealloyed powder
US3869284A (en) * 1973-04-02 1975-03-04 French Baldwin J High temperature alloys
US3890816A (en) * 1973-09-26 1975-06-24 Gen Electric Elimination of carbide segregation to prior particle boundaries
US4061495A (en) * 1974-07-08 1977-12-06 Johnson, Matthey & Co., Limited Platinum group metal-containing alloy
US4209348A (en) * 1976-11-17 1980-06-24 United Technologies Corporation Heat treated superalloy single crystal article and process
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
US4814023A (en) * 1987-05-21 1989-03-21 General Electric Company High strength superalloy for high temperature applications
US4894089A (en) * 1987-10-02 1990-01-16 General Electric Company Nickel base superalloys
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5104614A (en) * 1986-02-06 1992-04-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Superalloy compositions with a nickel base
US5240491A (en) * 1991-07-08 1993-08-31 General Electric Company Alloy powder mixture for brazing of superalloy articles
US5270123A (en) * 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
US5399313A (en) * 1981-10-02 1995-03-21 General Electric Company Nickel-based superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries
US5743713A (en) * 1995-09-21 1998-04-28 Ngk Insulators, Ltd. Blade, turbine disc and hybrid type gas turbine blade
US6007645A (en) * 1996-12-11 1999-12-28 United Technologies Corporation Advanced high strength, highly oxidation resistant single crystal superalloy compositions having low chromium content
US20020041821A1 (en) * 2000-09-29 2002-04-11 Manning Andrew J. Nickel base superalloy
US6521175B1 (en) * 1998-02-09 2003-02-18 General Electric Co. Superalloy optimized for high-temperature performance in high-pressure turbine disks
US20030041930A1 (en) * 2001-08-30 2003-03-06 Deluca Daniel P. Modified advanced high strength single crystal superalloy composition
US6533117B2 (en) * 1999-12-28 2003-03-18 Aroma Naturals, Inc. Candle packaging system and method of producing same
US6673308B2 (en) * 2000-08-30 2004-01-06 Kabushiki Kaisha Toshiba Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof
US20040011443A1 (en) * 2000-02-29 2004-01-22 General Electric Company Nickel base superalloys and turbine components fabricated therefrom
US6706241B1 (en) * 2002-11-12 2004-03-16 Alstom Technology Ltd Nickel-base superalloy
US20040221927A1 (en) * 2002-07-19 2004-11-11 Raymond Edward Lee Isothermal forging of nickel-base superalloys in air
US20060093849A1 (en) * 2004-11-02 2006-05-04 Farmer Andrew D Method for applying chromium-containing coating to metal substrate and coated article thereof

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE29920E (en) * 1975-07-29 1979-02-27 High temperature alloys
US4047933A (en) * 1976-06-03 1977-09-13 The International Nickel Company, Inc. Porosity reduction in inert-gas atomized powders
US4261742A (en) 1978-09-25 1981-04-14 Johnson, Matthey & Co., Limited Platinum group metal-containing alloys
US4569824A (en) 1980-05-09 1986-02-11 United Technologies Corporation Corrosion resistant nickel base superalloys containing manganese
JPH01165741A (ja) 1987-12-21 1989-06-29 Kobe Steel Ltd 結晶粒度の異なる同種合金からなるタービンディスク
US4878953A (en) 1988-01-13 1989-11-07 Metallurgical Industries, Inc. Method of refurbishing cast gas turbine engine components and refurbished component
US6355117B1 (en) 1992-10-30 2002-03-12 United Technologies Corporation Nickel base superalloy single crystal articles with improved performance in air and hydrogen
RU2038401C1 (ru) 1993-05-06 1995-06-27 Институт порошковой металлургии Порошковый высокотемпературный износостойкий сплав на основе никеля
GB9608617D0 (en) * 1996-04-24 1996-07-03 Rolls Royce Plc Nickel alloy for turbine engine components
US6444057B1 (en) 1999-05-26 2002-09-03 General Electric Company Compositions and single-crystal articles of hafnium-modified and/or zirconium-modified nickel-base superalloys
EP1201777B1 (en) 2000-09-29 2004-02-04 General Electric Company Superalloy optimized for high-temperature performance in high-pressure turbine disks
EP1666618B2 (en) 2000-10-04 2015-06-03 General Electric Company Ni based superalloy and its use as gas turbine disks, shafts and impellers
US6521053B1 (en) * 2000-11-08 2003-02-18 General Electric Co. In-situ formation of a protective coating on a substrate
JP4146178B2 (ja) 2001-07-24 2008-09-03 三菱重工業株式会社 Ｎｉ基焼結合金
US6919042B2 (en) * 2002-05-07 2005-07-19 United Technologies Corporation Oxidation and fatigue resistant metallic coating

Patent Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3061426A (en) * 1960-02-01 1962-10-30 Int Nickel Co Creep resistant alloy
US3744996A (en) * 1969-10-28 1973-07-10 Int Nickel Co Nickel base alloys of improved high temperature tensile ductility
US3865575A (en) * 1972-12-18 1975-02-11 Int Nickel Co Thermoplastic prealloyed powder
US3869284A (en) * 1973-04-02 1975-03-04 French Baldwin J High temperature alloys
US3890816A (en) * 1973-09-26 1975-06-24 Gen Electric Elimination of carbide segregation to prior particle boundaries
US4061495A (en) * 1974-07-08 1977-12-06 Johnson, Matthey & Co., Limited Platinum group metal-containing alloy
US4209348A (en) * 1976-11-17 1980-06-24 United Technologies Corporation Heat treated superalloy single crystal article and process
US5399313A (en) * 1981-10-02 1995-03-21 General Electric Company Nickel-based superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
US5104614A (en) * 1986-02-06 1992-04-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Superalloy compositions with a nickel base
US4814023A (en) * 1987-05-21 1989-03-21 General Electric Company High strength superalloy for high temperature applications
US4894089A (en) * 1987-10-02 1990-01-16 General Electric Company Nickel base superalloys
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5240491A (en) * 1991-07-08 1993-08-31 General Electric Company Alloy powder mixture for brazing of superalloy articles
US5270123A (en) * 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
US5743713A (en) * 1995-09-21 1998-04-28 Ngk Insulators, Ltd. Blade, turbine disc and hybrid type gas turbine blade
US6007645A (en) * 1996-12-11 1999-12-28 United Technologies Corporation Advanced high strength, highly oxidation resistant single crystal superalloy compositions having low chromium content
US6521175B1 (en) * 1998-02-09 2003-02-18 General Electric Co. Superalloy optimized for high-temperature performance in high-pressure turbine disks
US6533117B2 (en) * 1999-12-28 2003-03-18 Aroma Naturals, Inc. Candle packaging system and method of producing same
US20040011443A1 (en) * 2000-02-29 2004-01-22 General Electric Company Nickel base superalloys and turbine components fabricated therefrom
US6673308B2 (en) * 2000-08-30 2004-01-06 Kabushiki Kaisha Toshiba Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof
US20020041821A1 (en) * 2000-09-29 2002-04-11 Manning Andrew J. Nickel base superalloy
US20030041930A1 (en) * 2001-08-30 2003-03-06 Deluca Daniel P. Modified advanced high strength single crystal superalloy composition
US20040221927A1 (en) * 2002-07-19 2004-11-11 Raymond Edward Lee Isothermal forging of nickel-base superalloys in air
US6706241B1 (en) * 2002-11-12 2004-03-16 Alstom Technology Ltd Nickel-base superalloy
US20060093849A1 (en) * 2004-11-02 2006-05-04 Farmer Andrew D Method for applying chromium-containing coating to metal substrate and coated article thereof

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2628810A1 (en) 2012-02-14 2013-08-21 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
EP2628811A1 (en) 2012-02-14 2013-08-21 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
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
US9540714B2 (en) 2013-03-15 2017-01-10 Ut-Battelle, Llc High strength alloys for high temperature service in liquid-salt cooled energy systems
US9377245B2 (en) 2013-03-15 2016-06-28 Ut-Battelle, Llc Heat exchanger life extension via in-situ reconditioning
US10017842B2 (en) 2013-08-05 2018-07-10 Ut-Battelle, Llc Creep-resistant, cobalt-containing alloys for high temperature, liquid-salt heat exchanger systems
US9435011B2 (en) 2013-08-08 2016-09-06 Ut-Battelle, Llc Creep-resistant, cobalt-free alloys for high temperature, liquid-salt heat exchanger systems
US9683280B2 (en) 2014-01-10 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9683279B2 (en) 2014-05-15 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9605565B2 (en) 2014-06-18 2017-03-28 Ut-Battelle, Llc Low-cost Fe—Ni—Cr alloys for high temperature valve applications
US9752468B2 (en) 2014-06-18 2017-09-05 Ut-Battelle, Llc Low-cost, high-strength Fe—Ni—Cr alloys for high temperature exhaust valve applications
EP3231881A1 (en) 2016-04-11 2017-10-18 United Technologies Corporation Braze material for hybrid structures
EP3421622A1 (en) 2017-06-26 2019-01-02 United Technologies Corporation Solid-state welding of coarse grain powder metallurgy nickel-based superalloys
EP3995594A1 (en) 2017-06-26 2022-05-11 Raytheon Technologies Corporation Solid-state welding of coarse grain powder metallurgy nickel-based superalloys
CN115652147A (zh) * 2022-12-29 2023-01-31 北京钢研高纳科技股份有限公司 粉末高温合金及其制备方法和应用

Also Published As

Publication number Publication date
AU2006200325A1 (en) 2006-10-19
KR100810838B1 (ko) 2008-03-07
SG126026A1 (en) 2006-10-30
JP4498282B2 (ja) 2010-07-07
CN1840719A (zh) 2006-10-04
JP2006283186A (ja) 2006-10-19
EP1710322A1 (en) 2006-10-11
KR20060106635A (ko) 2006-10-12
CA2533574A1 (en) 2006-09-30
EP1710322B1 (en) 2014-06-18
US8147749B2 (en) 2012-04-03
US20100158695A1 (en) 2010-06-24
KR20070114689A (ko) 2007-12-04
TW200639260A (en) 2006-11-16

Similar Documents

Publication Publication Date Title
US8147749B2 (en) Superalloy compositions, articles, and methods of manufacture
RU2433197C2 (ru) Жаропрочный сплав на основе никеля, способ изготовления детали и деталь турбомашины
US9783873B2 (en) Superalloy compositions, articles, and methods of manufacture
CA2957786C (en) Enhanced superalloys by zirconium addition
CA2804402C (en) Nickel-base alloy, processing therefor, and components formed thereof
JP6826235B2 (ja) Ｎｉ基合金軟化粉末および該軟化粉末の製造方法
EP2628811B1 (en) Superalloy compositions, articles, and methods of manufacture
EP2069546A2 (en) Nickel-base alloy for gas turbine applications
US8858874B2 (en) Ternary nickel eutectic alloy
JP5981250B2 (ja) 鋳造用Ｎｉ基合金、鋳造用Ｎｉ基合金の製造方法およびタービン鋳造部品
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
JP2004256840A (ja) 複合強化型Ｎｉ基超合金とその製造方法
KR102142439B1 (ko) 고온 크리프 특성과 내산화성이 우수한 니켈기 초내열 합금 및 그 제조방법
EP2913417B1 (en) Article and method for forming article
JP2014058702A (ja) 鋳造用Ｎｉ基合金およびタービン鋳造部品
JPH0776402B2 (ja) 超耐熱合金
JPH09184041A (ja) クロム−鉄系単結晶合金及びそれを用いたガスタービン部材

Legal Events

Date Code Title Description
AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:REYNOLDS, PAUL L.;REEL/FRAME:016474/0783

Effective date: 20050329

STCB Information on status: application discontinuation

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

AS Assignment

Owner name: DEPARTMENT OF THE NAVY, MARYLAND

Free format text: CONFIRMATORY LICENSE;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:028162/0525

Effective date: 20120308