US3310440A - Heat treatment of nickel base alloys - Google Patents

Heat treatment of nickel base alloys Download PDF

Info

Publication number
US3310440A
US3310440A US405410A US40541064A US3310440A US 3310440 A US3310440 A US 3310440A US 405410 A US405410 A US 405410A US 40541064 A US40541064 A US 40541064A US 3310440 A US3310440 A US 3310440A
Authority
US
United States
Prior art keywords
alloy
nickel
heat treatment
hours
coated
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.)
Expired - Lifetime
Application number
US405410A
Inventor
Barry J Piearcey
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 Aircraft 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
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US405410A priority Critical patent/US3310440A/en
Priority to GB38102/65A priority patent/GB1124044A/en
Priority to NL656512668A priority patent/NL148945B/en
Priority to DE19651483315 priority patent/DE1483315B1/en
Priority to JP40061574A priority patent/JPS5136206B1/ja
Priority to SE13323/65A priority patent/SE312921B/xx
Priority to CH1455765A priority patent/CH466931A/en
Priority to FR35788A priority patent/FR1458768A/en
Priority to BE671189D priority patent/BE671189A/xx
Application granted granted Critical
Publication of US3310440A publication Critical patent/US3310440A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • C22C16/00—Alloys based on zirconium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/32—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C
    • 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
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • 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
    • 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

Definitions

  • the present invention relates to the heat-treatment of nickel-base superalloys which are commonly coated to improve their high temperature oxidation, sulfidation and erosion resistance, which heat treatment improves the mechanical properties of the alloys compared with their normal properties in the coated condition.
  • nickel-base alloys for use in gas turbine power plants either as rotor or stator members have been provided with coatings adapted to render the blades or vanes more highly resistant to oxidation and thermal while not impairing their other desirable properties.
  • a further object is the provision of a novel and improved process for the heat treatment of certain cast nickel-base superalloys so as to improve the creep properties of such alloy members at intermediate and elevated temperatures.
  • the process of the present invention is' particularly adapted for use with the nickel-base, coated superalloys which are used in gas turbine blades and vanes to be operated at temperatures in excess of 1200" F. and even as high as 2200 F. under extreme conditions.
  • Such blades are conventionally provided with an adherant surface coating which contributes greatly to the improvement of the properties of the blades and vanes with respect to high temperature oxidation, sulfidation and erosion resistance, but often does so at the cost of some re- I duction in the life of such blades under continuously applied stress such as 1400 F. and 95,000 psi.
  • gas turbine blades and vanes formed of nickel-base, high temperature, corrosion-resistant alloys, provided with their protective coatings exhibit a greatly extended life at the same high temperatures and operating stresses, as compared with the identical blades or vanes which have not been subjected to the heat treatment of the present invention, while none of the desirable properties of such coated, and un-heattreated parts are sacrificed.
  • the process of the present invention is particularly applicable to those nickel-base superalloys which are similar to those commonly referred to as SM-200 and which have approximately the following specification analysis:
  • a gas turbine blade or vane cast from the nickel base alloy is preferably provided with a protective coating in accordance with the prior patent to Joseph, No. 3,102,044 of 1963, specifically in accordance with Examples 1, 2, 3, or 4 of said Joseph patent, but preferably at 2000 F. for a period of about four hours.
  • any of these treatments provides the blade or vane member with a surface layer of a composition selected from the group of metals comprising aluminum, magnesium, chromium, columbium, cobalt, titanium, tantalum, tungsten, silicon, alloys thereof, oxides thereof and mixtures of the foregoing, which has been sintered on the surface of the blade or vane, and preferably comprises about 64% titanium, and 36% aluminum, the Weight of the coating being about 30% of the weight of the coated vane or blade; or alternatively the coating consists of a mixture of finely divided particles of aluminum and silicon comprising about aluminum and about 10% silicon.
  • the coated blades or vanes are subjected after coating to heat treatment and the preferred procedure for this coating treatment comprises heating the coated blade or vane members in vacuum or an inert gas, such as argon, or less preferably in air at 2000 F. for a period of about four hours, followed by about one to four hours heating at 2250" F., followed by heat treatment at 1600 F. for a period of from 32 to 64 hours; the step of normalizing by cooling in a gas, preferably an inert atmosphere, being carried out between each of the three heat treating operations.
  • the heat treatment may be varied, while achieving the results of the present invention by initially heating the coated blade or vane at about 2000 F.
  • the heat treatment may comprise initially heating the coated vane or blade at an increasing temperature in the range of 1800 to 2200 or 2260 F., the temperature being increased at the rate of about 100 F. per hour, and thereafter holding the blade or vane at a temperature of 2200 to 2260 F., preferably 2250 F. for from one to 4 hours, all preferably in an inert atmosphere.
  • the cooling in gas is preferably in an inert atmosphere, such as argon, or less preferably in air.
  • the blades and vanes treated according to the present invention are not only made from an alloy of the specified composition, but are also characterized by the elongated, columnar grain structure having grain boundaries substantially parallel to the principal axis and with substantially no grain boundaries normal to the principal axis, all in accordance with the disclosure of the copending application of Francis L. Ver Snyder, Ser. No. 361,323, filed Apr. 17, 1964, now Patent No. 3,260,505 which described methods of producing such substantially uni-directionally oriented crystals forming either a blade or a vane member.
  • Specimen A Alloy SM-200, as cast.
  • Specimen B Alloy SM-200, coated with a protective coating in accordance with the procedure set forth in the Joseph patent, involving heating at 2000 F. for four hours.
  • Specimen C Alloy SM-200 un-coated, but heated for four hours in vacuum at 2000 F.
  • Specimen D Alloy SM-200, coated the same as speci- B, but then heat treated after coating by heating in vacuum at 2250 F. for four hours, air cooling, and again heating for 64 hours at 1600 F., followed by air cooling.
  • the heat treatment of the test specimen increased the life of the stress rupture test specimen more than three times over life of any of the other specimens of the same alloy which had not been so heat treated.
  • specimen D treated according to the present invention oxidized much less in air at elevated temperatures than the same alloy as cast (specimen A) and much the same as the coated but un-heattreated specimen B, showing that the heat treatment at 4 2250 F. did not detrimentally affect the oxidation resistance imparted by the coating.
  • the balance of the alloy consisting of nickel, and heat-treating such alloy by heating the alloy fora period of one to four hours at a temperature of about 2000 F., cooling the alloy in gas, heating the alloy to a temperature of from 2200 F. to 2260 F. for several hours, cooling the alloy in gas, reheating the alloy to a temperature in the range of from 1550 to 1650 F. for a period of one to three days, and again cooling the alloy in gas.
  • Tungsten 11.5 to 13.5
  • the 6 balance of the alloy consisting of nickel, and heat-treating such alloy by heating the alloy for a period of one to four hours at a temperature of from 1800 to 2260 F., and holding the alloy at a temperature of from 2200" F. to 2260 F. for several hours, cooling the alloy in gas, reheating the alloy to a temperature in the range of from 1500" to 1650 F. for a period of one to three days, and again cooling the alloy in gas.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Heat Treatments In General, Especially Conveying And Cooling (AREA)
  • Heat Treatment Of Nonferrous Metals Or Alloys (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ceramic Products (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)

Description

March 21, 1967 J. PIEARCEY HEAT TREATMENT OF NICKEL BASE ALLOYS Filed Oct. 21, 1964 mmDOI ME; 2 w. E N 0- m N q I- 0 zwszuwam I m Zm$=uwmw I 526m; 0 Q N o I I I. I I I u I Q I I I I I I I I I I I I O u I I I 0 mo OONN mDO Iwm ZO n:XO O I Q l INVENTOR BARRY J. PIEARCEY W0 SW V zwv BY MORGAN, FINNEGAN, DURHAM 8 PINE ATTORNEYS United States Patent Ofi1ce 3,310,440 Patented Mar. 21, 1967 3,310,440 HEAT TREATMENT OF NICKEL BASE ALLOYS Barry J. Piearcey, Cheshire, Cnn., assignor to United Aircraft Corporation, East Hartford, Conn., 21 corporation of Delaware Filed Oct. 21, 1964, Ser. No. 405,410
5 Claims. (Cl. 148-13) The present invention relates to the heat-treatment of nickel-base superalloys which are commonly coated to improve their high temperature oxidation, sulfidation and erosion resistance, which heat treatment improves the mechanical properties of the alloys compared with their normal properties in the coated condition.
Heretofore, nickel-base alloys for use in gas turbine power plants, either as rotor or stator members have been provided with coatings adapted to render the blades or vanes more highly resistant to oxidation and thermal while not impairing their other desirable properties.
A further object is the provision of a novel and improved process for the heat treatment of certain cast nickel-base superalloys so as to improve the creep properties of such alloy members at intermediate and elevated temperatures.
The process of the present invention is' particularly adapted for use with the nickel-base, coated superalloys which are used in gas turbine blades and vanes to be operated at temperatures in excess of 1200" F. and even as high as 2200 F. under extreme conditions. Such blades are conventionally provided with an adherant surface coating which contributes greatly to the improvement of the properties of the blades and vanes with respect to high temperature oxidation, sulfidation and erosion resistance, but often does so at the cost of some re- I duction in the life of such blades under continuously applied stress such as 1400 F. and 95,000 psi.
As the result of the present invention, gas turbine blades and vanes formed of nickel-base, high temperature, corrosion-resistant alloys, provided with their protective coatings exhibit a greatly extended life at the same high temperatures and operating stresses, as compared with the identical blades or vanes which have not been subjected to the heat treatment of the present invention, while none of the desirable properties of such coated, and un-heattreated parts are sacrificed.
The process of the present invention is particularly applicable to those nickel-base superalloys which are similar to those commonly referred to as SM-200 and which have approximately the following specification analysis:
Although the actual analysis of SM-200 alloys supplied according to this specification analysis may vary somewhat beyond the ranges noted, the typical range of actual analyses of alloys to be treated according to the process of the present invention is as follows, expressed as weight percent:
Tungsten 11.5 to 13.5
Aluminum 4.75 to 5.25 Titanium 1.75 to 2.25 Boron 0.01 to 0.02 Zirconium 0.03 to 0.08
(but not more than 5 times boron content) Carbon 0.12 to 0.17 Columbium 0.75 to 1.25 Nickel Balance Impurities Percent maximum Manganese 0.2 Sulfur 0.015 Silicon 0.2 Iron .Q. Q. 1.5 Copper 0.1
The preferred analysis of such a nickel-base superalloy to be used inthe process of the present invention consists of the following essential elements, in approximately the weight percentages set forth, although normal manufacturing deviations from this analysis may be tolerated in accordance with normal procedures in the production of nickel-base superalloys.
Percent Chromium 9.0 Cobalt H 10.0 Tungsten 12.5 C'olumbiunr 1.0 Aluminum 51,.0 Titanium 2.0 -Iron max 1.5 Boron 0.015 Carbon 0.15
Other elements as specified above? ,Nickel, balance, except for minor impurities.
' According to the process of the present invention, a gas turbine blade or vane cast from the nickel base alloy is preferably provided with a protective coating in accordance with the prior patent to Joseph, No. 3,102,044 of 1963, specifically in accordance with Examples 1, 2, 3, or 4 of said Joseph patent, but preferably at 2000 F. for a period of about four hours.
Any of these treatments provides the blade or vane member with a surface layer of a composition selected from the group of metals comprising aluminum, magnesium, chromium, columbium, cobalt, titanium, tantalum, tungsten, silicon, alloys thereof, oxides thereof and mixtures of the foregoing, which has been sintered on the surface of the blade or vane, and preferably comprises about 64% titanium, and 36% aluminum, the Weight of the coating being about 30% of the weight of the coated vane or blade; or alternatively the coating consists of a mixture of finely divided particles of aluminum and silicon comprising about aluminum and about 10% silicon.
According to the process of the present invention, the coated blades or vanes are subjected after coating to heat treatment and the preferred procedure for this coating treatment comprises heating the coated blade or vane members in vacuum or an inert gas, such as argon, or less preferably in air at 2000 F. for a period of about four hours, followed by about one to four hours heating at 2250" F., followed by heat treatment at 1600 F. for a period of from 32 to 64 hours; the step of normalizing by cooling in a gas, preferably an inert atmosphere, being carried out between each of the three heat treating operations. The heat treatment may be varied, while achieving the results of the present invention by initially heating the coated blade or vane at about 2000 F. for about 4 hours, normalizing by cooling in air or an inert atmosphere, heating at a temperature of from 2200 to 2260 F. for from one to 4 hours, followed by cooling in air or an inert gas, the heating at 1550 to 16 50 F. for a period of from one to. three days, again followed by air cooling or in an inert atmosphere.
' Alternatively the heat treatment may comprise initially heating the coated vane or blade at an increasing temperature in the range of 1800 to 2200 or 2260 F., the temperature being increased at the rate of about 100 F. per hour, and thereafter holding the blade or vane at a temperature of 2200 to 2260 F., preferably 2250 F. for from one to 4 hours, all preferably in an inert atmosphere.
The cooling in gas is preferably in an inert atmosphere, such as argon, or less preferably in air.
Most preferably, the blades and vanes treated according to the present invention are not only made from an alloy of the specified composition, but are also characterized by the elongated, columnar grain structure having grain boundaries substantially parallel to the principal axis and with substantially no grain boundaries normal to the principal axis, all in accordance with the disclosure of the copending application of Francis L. Ver Snyder, Ser. No. 361,323, filed Apr. 17, 1964, now Patent No. 3,260,505 which described methods of producing such substantially uni-directionally oriented crystals forming either a blade or a vane member.
In the following table are shown test results on four different uni-directionally cast test specimens of the same composition, from the same heat, and which are di'fferentiated, as follows:
Specimen A: Alloy SM-200, as cast.
Specimen B: Alloy SM-200, coated with a protective coating in accordance with the procedure set forth in the Joseph patent, involving heating at 2000 F. for four hours.
Specimen C: Alloy SM-200 un-coated, but heated for four hours in vacuum at 2000 F.
Specimen D: Alloy SM-200, coated the same as speci- B, but then heat treated after coating by heating in vacuum at 2250 F. for four hours, air cooling, and again heating for 64 hours at 1600 F., followed by air cooling.
When subjected to stress rupture tests at elevated temperatures (1400 F.) with a stress loading of 95,000 pounds per square inch, the following test results were obtained:
Thus, the heat treatment of the test specimen increased the life of the stress rupture test specimen more than three times over life of any of the other specimens of the same alloy which had not been so heat treated.
The properties were obtained with no loss in oxidation resistance with respect to specimen B and are shown in the drawing where the oxidation resistance of material similar to specimens A, B and D are compared by measurement of weight gain with time in air at 2200 F. It is considered that there is no significant difference between the oxidation resistance of specimens B and D and therefore the heat-treatment described results in no loss in oxidation resistance but with improved properties in other respects. 7
It will be noted that specimen D, treated according to the present invention oxidized much less in air at elevated temperatures than the same alloy as cast (specimen A) and much the same as the coated but un-heattreated specimen B, showing that the heat treatment at 4 2250 F. did not detrimentally affect the oxidation resistance imparted by the coating.
In the drawing, time in hours is plotted against increase in mass (weight) for a given area, expressed as milligrams weight gain for each one-hundredth of a square centimeter of alloy area is plotted against time. Furthermore, no loss in high-temperature strength is observed as evidenced by the following data:
Temp, Stress, Percent Percent Specimen F. p.s.i. Life (hrs) Elouga- Reduction tion in area A 1, 800 20, 000 657. 4 22. 7 37. 5 D 1, 800 20, 000 690. G 23. 6 47. 1
Percent Chromium 8 to 10 Cobalt 9 to 11 Tungsten 11.5 to 13.5 Aluminum 4.7 to 5.25 Titanium 1.75 tov 2.25 Columbium 0.75 to 1.25 Boron 0.01 to 0.02 Carbon 0.12 to 0.17 Zirconium 0.03 to 0.08
(but not more than 5 times the boron content), and the balance of the alloy consisting of nickel, and heat-treating such alloy by heating the alloy fora period of one to four hours at a temperature of about 2000 F., cooling the alloy in gas, heating the alloy to a temperature of from 2200 F. to 2260 F. for several hours, cooling the alloy in gas, reheating the alloy to a temperature in the range of from 1550 to 1650 F. for a period of one to three days, and again cooling the alloy in gas.
2. The method according to claim 1 in which the alloy is initially heated at 2000 F., is next heated at 2250 F., and is finally heated at 1600 F.
3. The method according to claim 1 in which the alloy 'has the following composition, excluding incidental impurities:
Percent Chromium 9 Cobalt 10 Tungsten 12.5 Columbium 1 Aluminum 5 Titanium 2 Boron 0.015 Carbon 0.15 Nickel Balance 4. The method according to claim 2 in which the alloy has the following composition, excluding incidental impurities:
Percent Chromium 9 Cobalt 10 Tungsten 12.5
Columbium '1 'Aluminum Q. 5 Titanium .Q 2-
Percent Boron 0.015 Carbon 0.15 Nickel Balance 5. The method of heat treating a nickel-base alloy to.
improve its stress rupture life at temperatures in excess of 1200 F. which comprises subjecting a nickel-base alloy having essentially the following composition, excluding incidental impurities:
Percent Chromium 8 to 10 Cobalt 9 to 11 Tungsten 11.5 to 13.5 Aluminum 4.75 to 5.25 Titanium 1.75 to 2.25 Columbium 0.75 to 1.25 Boron 0.01 to 0.02 Carbon 0.12 to 0.17 Zirconium 0.03 to 0.08
(but not more than 5 times the boron content), and the 6 balance of the alloy consisting of nickel, and heat-treating such alloy by heating the alloy for a period of one to four hours at a temperature of from 1800 to 2260 F., and holding the alloy at a temperature of from 2200" F. to 2260 F. for several hours, cooling the alloy in gas, reheating the alloy to a temperature in the range of from 1500" to 1650 F. for a period of one to three days, and again cooling the alloy in gas.
References Cited by the Examiner UNITED STATES PATENTS 2,887,420 5/1959 Llewelyn et al 14813.1 3,166,412 1/1965 Bieber 75-171 3,212,886 10/1965 Freedman 75171 3,254,994 6/1966 Quigg 75-171 3,272,666 9/1966 Symonds 14813 DAVID L. RECK, Primary Examiner.
20 R. O. DEAN, Assistant Examiner.

Claims (1)

1. THE METHOD OF HEAT TREATING A NICKEL-BASE ALLOY TO IMPROVE ITS STRESS RUPTURE LIFE AT TEMPERATURES IN EXCESS OF 1200* F. WHICH COMPRISES SUBJECTING A NICKEL-BASE ALLOY HAVING ESSENTIALY THE FOLLOWING COMPOSITION, EXCLUDING INCIDENTAL IMPURITIES:
US405410A 1964-10-21 1964-10-21 Heat treatment of nickel base alloys Expired - Lifetime US3310440A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US405410A US3310440A (en) 1964-10-21 1964-10-21 Heat treatment of nickel base alloys
GB38102/65A GB1124044A (en) 1964-10-21 1965-09-07 Improvements in and relating to heat treatment of nickel-base alloys
NL656512668A NL148945B (en) 1964-10-21 1965-09-30 PROCEDURE FOR THE HEAT TREATMENT OF GAS TURBIN PARTS AND GAS TURBIN PARTS TREATED IN ACCORDANCE WITH THIS PROCESS.
DE19651483315 DE1483315B1 (en) 1964-10-21 1965-10-05 USE OF A HIGH-MELTING SOLDER TO MANUFACTURE A THREE-LAYER COMPOSITE BODY
JP40061574A JPS5136206B1 (en) 1964-10-21 1965-10-06
SE13323/65A SE312921B (en) 1964-10-21 1965-10-14
CH1455765A CH466931A (en) 1964-10-21 1965-10-21 Heat treatment process for a nickel-based alloy
FR35788A FR1458768A (en) 1964-10-21 1965-10-21 Heat treatment of alloys
BE671189D BE671189A (en) 1964-10-21 1965-10-21

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US405410A US3310440A (en) 1964-10-21 1964-10-21 Heat treatment of nickel base alloys

Publications (1)

Publication Number Publication Date
US3310440A true US3310440A (en) 1967-03-21

Family

ID=23603591

Family Applications (1)

Application Number Title Priority Date Filing Date
US405410A Expired - Lifetime US3310440A (en) 1964-10-21 1964-10-21 Heat treatment of nickel base alloys

Country Status (8)

Country Link
US (1) US3310440A (en)
JP (1) JPS5136206B1 (en)
BE (1) BE671189A (en)
CH (1) CH466931A (en)
DE (1) DE1483315B1 (en)
GB (1) GB1124044A (en)
NL (1) NL148945B (en)
SE (1) SE312921B (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3753790A (en) * 1972-08-02 1973-08-21 Gen Electric Heat treatment to dissolve low melting phases in superalloys
US4151017A (en) * 1976-05-07 1979-04-24 Maschinenfabric Augsburg-Nurnberg Aktiengesellschaft Method of producing heat-resistant parts
US4221610A (en) * 1978-02-24 1980-09-09 The United States Of America As Represented By The United States Department Of Energy Method for homogenizing alloys susceptible to the formation of carbide stringers and alloys prepared thereby
US4492672A (en) * 1982-04-19 1985-01-08 The United States Of America As Represented By The Secretary Of The Navy Enhanced microstructural stability of nickel alloys
US4717432A (en) * 1986-04-09 1988-01-05 United Technologies Corporation Varied heating rate solution heat treatment for superalloy castings
US4753686A (en) * 1984-11-08 1988-06-28 Societe Nationale D'etude Et De Construction De Moteur D'aviation "S.N.E.C.M.A." Regeneration of nickel-based superalloy parts damaged by creep
EP1207005A1 (en) * 2000-11-17 2002-05-22 General Electric Company Heat treatment of weld repaired gas turbine engine components
EP1688592A1 (en) * 2004-12-23 2006-08-09 Nuovo Pignone S.P.A. Vapour turbine
EP1688593A1 (en) * 2004-12-23 2006-08-09 Nuovo Pignone S.P.A. Vapour turbine
EP1691036A1 (en) * 2004-12-23 2006-08-16 Nuovo Pignone S.P.A. Vapour turbine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS52154903U (en) * 1976-05-20 1977-11-24
AT383762B (en) * 1985-12-23 1987-08-25 Plansee Metallwerk METHOD FOR PRODUCING MULTI-COMPONENT, CONGRUENTLY MELTING SOLDER MATERIALS
CH675256A5 (en) * 1988-03-02 1990-09-14 Asea Brown Boveri

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2887420A (en) * 1956-04-06 1959-05-19 Bristol Aero Engines Ltd Surface treatments for articles made from heat resisting alloys
US3166412A (en) * 1962-08-31 1965-01-19 Int Nickel Co Cast nickel-base alloy for gas turbine rotors
US3212886A (en) * 1961-10-03 1965-10-19 Armco Steel Corp High temperature alloy
US3254994A (en) * 1963-06-24 1966-06-07 Trw Inc Alloys having improved stress rupture properties
US3272666A (en) * 1963-12-09 1966-09-13 Du Pont Method of heat treating nickel base alloy articles up to 20 mils in thickness

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE533026C (en) * 1928-12-30 1931-09-10 Georg Brunhuebner Lot
DE1153226B (en) * 1957-10-23 1963-08-22 Philips Nv Method for joining a foil consisting of a high-melting metal to an object made of a high-melting metal with the aid of a powder-form soldering material containing a monocarbide of this metal
DE1146728B (en) * 1959-11-23 1963-04-04 Atomic Energy Commission Process for soldering together parts made of niobium

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2887420A (en) * 1956-04-06 1959-05-19 Bristol Aero Engines Ltd Surface treatments for articles made from heat resisting alloys
US3212886A (en) * 1961-10-03 1965-10-19 Armco Steel Corp High temperature alloy
US3166412A (en) * 1962-08-31 1965-01-19 Int Nickel Co Cast nickel-base alloy for gas turbine rotors
US3254994A (en) * 1963-06-24 1966-06-07 Trw Inc Alloys having improved stress rupture properties
US3272666A (en) * 1963-12-09 1966-09-13 Du Pont Method of heat treating nickel base alloy articles up to 20 mils in thickness

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3753790A (en) * 1972-08-02 1973-08-21 Gen Electric Heat treatment to dissolve low melting phases in superalloys
US4151017A (en) * 1976-05-07 1979-04-24 Maschinenfabric Augsburg-Nurnberg Aktiengesellschaft Method of producing heat-resistant parts
US4221610A (en) * 1978-02-24 1980-09-09 The United States Of America As Represented By The United States Department Of Energy Method for homogenizing alloys susceptible to the formation of carbide stringers and alloys prepared thereby
US4492672A (en) * 1982-04-19 1985-01-08 The United States Of America As Represented By The Secretary Of The Navy Enhanced microstructural stability of nickel alloys
US4753686A (en) * 1984-11-08 1988-06-28 Societe Nationale D'etude Et De Construction De Moteur D'aviation "S.N.E.C.M.A." Regeneration of nickel-based superalloy parts damaged by creep
US4717432A (en) * 1986-04-09 1988-01-05 United Technologies Corporation Varied heating rate solution heat treatment for superalloy castings
EP1207005A1 (en) * 2000-11-17 2002-05-22 General Electric Company Heat treatment of weld repaired gas turbine engine components
EP1688592A1 (en) * 2004-12-23 2006-08-09 Nuovo Pignone S.P.A. Vapour turbine
EP1688593A1 (en) * 2004-12-23 2006-08-09 Nuovo Pignone S.P.A. Vapour turbine
EP1691036A1 (en) * 2004-12-23 2006-08-16 Nuovo Pignone S.P.A. Vapour turbine

Also Published As

Publication number Publication date
NL6512668A (en) 1966-04-22
JPS5136206B1 (en) 1976-10-07
DE1483315B1 (en) 1971-06-09
GB1124044A (en) 1968-08-21
BE671189A (en) 1966-02-14
NL148945B (en) 1976-03-15
CH466931A (en) 1968-12-31
SE312921B (en) 1969-07-28

Similar Documents

Publication Publication Date Title
EP0434996B1 (en) Nickle-based single crystal superalloy
US5328659A (en) Superalloy heat treatment for promoting crack growth resistance
US3310440A (en) Heat treatment of nickel base alloys
JP2881626B2 (en) Single crystal nickel-based superalloy
US4885216A (en) High strength nickel base single crystal alloys
CA2023400C (en) High strength fatigue crack-resistant alloy article and method for making the same
CN111051548B (en) Precipitation hardenable cobalt-nickel based superalloys and articles made therefrom
US5516381A (en) Rotating blade or stationary vane of a gas turbine
US4820353A (en) Method of forming fatigue crack resistant nickel base superalloys and product formed
US3540863A (en) Art of protectively metal coating columbium and columbium - alloy structures
US3642543A (en) Thermomechanical strengthening of the superalloys
EP0076360A2 (en) Single crystal nickel-base superalloy, article and method for making
US4386976A (en) Dispersion-strengthened nickel-base alloy
US4512817A (en) Method for producing corrosion resistant high strength superalloy articles
US2766155A (en) Production of high temperature articles and alloys therefor
US3536542A (en) Alloy heat treatment
US2996379A (en) Cobalt-base alloy
JPH0312134B2 (en)
JPH02115332A (en) Astroloy type nickel-base superalloy having a fatigue- failure resistance and a product made from it
EP0362661A1 (en) Cast columnar grain hollow nickel base alloy article and alloy and heat treatment for making
JP7139418B2 (en) Alloy turbine parts containing MAX phase
JPH02115330A (en) Method for manufacturing an in-100 type nickel-base superalloy having a fatigue-failure resistance and its product
US3145124A (en) Heat treatment of nickel chromiumcobalt alloys
US4401480A (en) Method of selective grain growth in nickel-base superalloys by controlled boron diffusion
US3047381A (en) High temperature heat and creep resistant alloy