US3228095A - Method of making turbine blades - Google Patents
Method of making turbine blades Download PDFInfo
- Publication number
- US3228095A US3228095A US101806A US10180661A US3228095A US 3228095 A US3228095 A US 3228095A US 101806 A US101806 A US 101806A US 10180661 A US10180661 A US 10180661A US 3228095 A US3228095 A US 3228095A
- Authority
- US
- United States
- Prior art keywords
- alloy
- blade
- nickel
- cast
- treatment
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4998—Combined manufacture including applying or shaping of fluent material
- Y10T29/49988—Metal casting
Definitions
- This invention concerns the production of the turbine rotor and stator blades of a gas turbine engine.
- the turbine rotor and stator blades are required to withstand very high temperatures and stresses for long periods of operation.
- the materials e.g. nickel based alloys
- the object of the present invention is therefore to provide a method by means of which such blades may be satisfactorily made.
- a method of making a turbine rotor or stator blade of a gas turbine engine comprising casting a mass of the material from which the blade is to be made, and employing substantially the whole of the cast mass in the production of a single turbine rotor or stator blade, the blade being formed from the cast mass by a process which involves a forging operation.
- the invention comprises a method of making a turbine motor or stator blade of a gas turbine engine from an alloy having the following percentage composition by weight:
- the combined titanium and aluminum content of the alloy being at least 6.5% and the balance of the alloy being nickel and impurities, there being at least 35% of nickel if cobalt is present or at least 45% of nickel if cobalt is not present, said method comprising casting a mass of the alloy, and employing substantially the whole of the cast mass in the production of a single turbine rotor or stator blade, the blade being formed from the cast mass by a process which involves a forging operation.
- each casting should be such that only one turbine blade can be formed therefrom it should be understood that the term casting, as used in this specification, is intended to cover the case where the casting is one of a number of interconnected castings produced from a corresponding number of moulds having a common runner.
- the allow is cast in the form of a dumbellshaped blade blank (which is known as a use).
- the surface of the cast alloy may be subjected to cold work prior to the said forging operation.
- the forging operation may conveniently be performed in two stages with a short high temperature heat-treatment therebetween. This may have the effect of increasing the creep resistance of the resulting blade.
- FIGURES 1-4 show side views and end views of a turbine blade at various stages of its manufacture.
- the use was then machined to size to produce a blank 11 and was inspected for surface defects, after which it was subjected to a controlled amount of surface cold work by shot peening, reeling, or cold swaging.
- the blank 11 was then given a first recrystallization treatment at 1150-1250 C. for 10 minutes and was quenched if necessary. After being vapour blasted, the blank 11 was nickel plated or glass coated so as to provide it with a surface lubricant and was then heated to 1200 C., after which it was press forged a controlled amount to a first deformation 12. It was then given a second recrystallization treatment at 1200" C., and was thereafter press. forged to a second deformation 13 which constituted its final shape. The blade was finally heattreated to give optimum qualities, e.g. by a solution heattreatment and by an ageing heat-treatment at one or two temperatures.
- the combined titanium and aluminium content of the alloy being at least 6.5% and the balance of the alloy being nickel and impurities, there being at least 35% of nickel if cobalt is present but at least 45% of nickel if cobalt is not present, said method comprising casting a mass of the alloy into the form of a dumbell-shaped blade blank, employing substantially the whole of the cast mass in the production of a single turbine blade, and forming the blade from the cast mass by a process which involves a hot forging operation.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
' 1966 J. R. BIRD ETAL 3,
METHOD OF MAKING TURBINE BLADES Filed April 10. 1961 United States Patent 3,228,095 METHOD OF MAKING TURBINE BLADES Jack Raymond Bird, Chellaston, Douglas Wilson Hall, Mickleover, and David Anthony Denton, Chellaston, England, assignors to Rolls-Royce Limited, Derby, England, a company of Great Britain Filed Apr. 10, 1961, Ser. No. 101,806 Claims priority, application Great Britain, Apr. 13, 1960, 13,287/60 6 Claims. (Cl. 29156.8)
This invention concerns the production of the turbine rotor and stator blades of a gas turbine engine.
In the modern gas turbine engine the turbine rotor and stator blades are required to withstand very high temperatures and stresses for long periods of operation. In order to meet these requirements, the materials (e.g. nickel based alloys) used in the production of these blades have a high content of strengthening constituents and are therefore difiicult to work. Accordingly, as the gas turbine engine becomes more and more highly developed it becomes increasingly difficult to form its turbine blades. The object of the present invention is therefore to provide a method by means of which such blades may be satisfactorily made.
According to the present invention there is provided a method of making a turbine rotor or stator blade of a gas turbine engine comprising casting a mass of the material from which the blade is to be made, and employing substantially the whole of the cast mass in the production of a single turbine rotor or stator blade, the blade being formed from the cast mass by a process which involves a forging operation.
In its preferred form the invention comprises a method of making a turbine motor or stator blade of a gas turbine engine from an alloy having the following percentage composition by weight:
Percent Cr -30 Co 0-30 Mo 5-30 W 0-20 Ti 0.5-7.0 Al 20-17 B 0.003-03 Zr 0.00l-1.0 C 0.01-0.5 Ca 0-0.1 him OO.4 Si 0-0.4 Fe O1.0 Be 00.5 Ta 0-5 Nb 0-5 Hf 0-10 Rare Earths 0-0.2 S 0-0.005 P 0-0.008 V 0-3 N 0-0.2 Mg 0-0.15 Combined O 0-0.2 Cu 0-0.5 Pb 0-0.005
the combined titanium and aluminum content of the alloy being at least 6.5% and the balance of the alloy being nickel and impurities, there being at least 35% of nickel if cobalt is present or at least 45% of nickel if cobalt is not present, said method comprising casting a mass of the alloy, and employing substantially the whole of the cast mass in the production of a single turbine rotor or stator blade, the blade being formed from the cast mass by a process which involves a forging operation.
We have found that the chief problem in forming blades of the above-mentioned alloy is to break down the coarse columnar crystal structure which the alloy has previously had in the as cast condition without exceeding the maximum shear strength of individual crystals and without forming microscopic flaws or very small cracks. We consider that the coarse crystal structure referred to above has previously been caused by casting the alloy into large ingots, since the central portion of these large ingots is very slow to cool from the liquid to the just solid state and this slow cooling permits the growth of large crystals. In the method of the present invention, however, the alloy is cast into very small masses since these masses are of a size such that only one turbine blade can be produced therefrom. Accordingly the cooling of such small masses is rapid with the result that they have relatively fine grains. Such small masses are then forged into turbine blades, faults present in the castings normally being made apparent as a result of the forging operation.
Although it is an essential feature of the present invention that each casting should be such that only one turbine blade can be formed therefrom it should be understood that the term casting, as used in this specification, is intended to cover the case where the casting is one of a number of interconnected castings produced from a corresponding number of moulds having a common runner.
Preferably the allow is cast in the form of a dumbellshaped blade blank (which is known as a use).
The surface of the cast alloy may be subjected to cold work prior to the said forging operation.
The forging operation may conveniently be performed in two stages with a short high temperature heat-treatment therebetween. This may have the effect of increasing the creep resistance of the resulting blade.
The invention is illustrated by the following Example, reference being made in the accompanying drawings, FIGURES 1-4 of which show side views and end views of a turbine blade at various stages of its manufacture.
Example An alloy having the following percentage composition by weight:
Percent Carbon 0.11 Chromium 14.80 Cobalt 10.20 Molybdenum 8.08 Aluminium 4.60 Titanium 4.42 Boron 0.005 Zirconium 0.002 Iron 0.30 Silicon 0.14 Manganese 0.10 Sulphur 0.002 Nickel Balance essentially was vacuum melted and was vacuum cast to form a use 10, that is to say a dumbell-shaped blade blank. The use 10 was inspected by X-ray methods and was given an homogenisation heat-treatment at 1200 C. for 2-24 hours.
The use was then machined to size to produce a blank 11 and was inspected for surface defects, after which it was subjected to a controlled amount of surface cold work by shot peening, reeling, or cold swaging.
The blank 11 was then given a first recrystallization treatment at 1150-1250 C. for 10 minutes and was quenched if necessary. After being vapour blasted, the blank 11 was nickel plated or glass coated so as to provide it with a surface lubricant and was then heated to 1200 C., after which it was press forged a controlled amount to a first deformation 12. It was then given a second recrystallization treatment at 1200" C., and was thereafter press. forged to a second deformation 13 which constituted its final shape. The blade was finally heattreated to give optimum qualities, e.g. by a solution heattreatment and by an ageing heat-treatment at one or two temperatures.
In the case of some alloys, it may be necessary, immediately prior to the final heat-treatment, to give the blade a further recrystallization treatment and to press forge it again.
Moreover, in the case of some alloys it is possible to omit the homogenization heat treatment, the machining to size, the surface cold work, the first recrystallization treatment, and by the vapour blast.
We claim:
1. A method of making a turbine blade of a gas turbine engine from an alloy having the following percentage composition by weight:
Percent Mn 0-0.4 Si 00.4
Be O-O.5 Ta 0-5 Nb -0-5 Hf 0-10 Rare Earths O-0.2
N 0-0.2 Mg 0-0.15 Combined O 0-0.2 Cu 0-0.5
the combined titanium and aluminium content of the alloy being at least 6.5% and the balance of the alloy being nickel and impurities, there being at least 35% of nickel if cobalt is present but at least 45% of nickel if cobalt is not present, said method comprising casting a mass of the alloy into the form of a dumbell-shaped blade blank, employing substantially the whole of the cast mass in the production of a single turbine blade, and forming the blade from the cast mass by a process which involves a hot forging operation.
2. A method as claimed in claim 1 in which the hot forging operation is performed in two stages with a high temperature heat-treatment at 1200' C. therebetween.
3. A method as claimed in claim 1 wherein the cast mass, before the forming operation, is given a homogenisation heat-treatment at 1200 C. for 2-24 hours and the subsequent hot forging operation is carried out in tWo stages with heat-treatment at 1200 C. therebetween.
4. A method of making a turbine blade of a gas turbine engine from an alloy having the following percentage composition by weight:
Percent Co 0-30 Mo 5-30 Al 2.0-17 B 0.003-0 3 Zr 0001-1 0 C 0.01-0.5
Ca 0-0.l
Mn O-O.4
Si O-O.4
Fe O-l.0
Be 0-0.5 Ta 0-5 Nb 0-5 Hf O-lO Rare Earths 0-0.2 S 0-0.00S
P 0-0.008 V O-3 N 0-0.2 Mg 00.1S Combined O O-0.2 Cu 0-O.5 Pb 0-0.005
the combined titanium and aluminium content of the alloy being at least 6.5% and the balance of the alloy being nickel and impurities, there being at least 35% of nickel if cobalt is present but at least 45% of nickel if cobalt is not present, said method comprising casting a mass of the alloy into the form of a dumbell-shaped blade blank, employing substantially the whole of the cast mass in the production of a single turbine blade, and forming the blade from the castmass by a processwhich involves subjecting the surface of the cast mass to cold work and thereafter subjecting the cast mass to a hot forging operation.
5. The method of claim 4 wherein the cast mass after coldworking is subjected to a recrystallization heat treatment before said hot forging operation and another recrystallization heat treatment after said hot forging operation.
6. The method of claim 4 wherein the hot forging operation comprises recrystallization heat treatment and press forging.
References Cited by the Examiner UNITED STATES PATENTS 2,447,897 8/1948 Clarke 29-1568 2,977,222 3/1961 Bieber -171 2,987,806- 6/1961 Pekarek 29-1568 3,047,381 7/1962 Hanink et al. 75-171 3,107,999 10/1-963- Gittus 75-171 3,110,587 11/1963 Gittus et'al. 75-171 FOREIGN PATENTS 548,777 11/ 1957 Canada.
CHARLIE T. MOON, Primary Examiner.
HYLAND BIGOT, WHITMORE A. WILTZ, Examiners J. D. HOBART, J. C. HOLMAN, Assistant Examiners.
Claims (1)
1. A METHOD OF MAKING A TURBINE BLADE OF A GAS TURBINE ENGINE FROM AN ALLOY HAVING THE FOLLOWING PERCENTAGE COMPOSITION BY WEIGHT:
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB13287/60A GB909948A (en) | 1960-04-13 | 1960-04-13 | Method of making turbine blades |
Publications (1)
Publication Number | Publication Date |
---|---|
US3228095A true US3228095A (en) | 1966-01-11 |
Family
ID=10020222
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US101806A Expired - Lifetime US3228095A (en) | 1960-04-13 | 1961-04-10 | Method of making turbine blades |
Country Status (2)
Country | Link |
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US (1) | US3228095A (en) |
GB (1) | GB909948A (en) |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3301670A (en) * | 1964-01-08 | 1967-01-31 | Int Nickel Co | Cast nickel-base alloy |
US4528048A (en) * | 1982-12-06 | 1985-07-09 | United Technologies Corporation | Mechanically worked single crystal article |
US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
US5980653A (en) * | 1997-01-23 | 1999-11-09 | Ngk Metals Corporation | Nickel-copper-beryllium alloy compositions |
US6112410A (en) * | 1997-09-19 | 2000-09-05 | The Research Corporation Of State University Of New York | Methods for fabricating a structural beam |
US20050155679A1 (en) * | 2003-04-09 | 2005-07-21 | Coastcast Corporation | CoCr alloys and methods for making same |
US20050246895A1 (en) * | 2004-03-03 | 2005-11-10 | Snecma Moteurs | Method of manufacturing a hollow blade for a turbomachine |
US20150093284A1 (en) * | 2013-09-30 | 2015-04-02 | Liburdi Engineering Limited | Welding material for welding of superalloys |
CZ306719B6 (en) * | 2015-10-25 | 2017-05-24 | Univerzita J. E. Purkyně V Ústí Nad Labem | An aluminium alloy, especially for the production of thin-walled and dimensionally complex castings |
JP2017519643A (en) * | 2014-04-28 | 2017-07-20 | リバルディ エンジニアリング リミテッド | Malleable boron-supported nickel-based welding material |
US10493568B2 (en) | 2014-10-21 | 2019-12-03 | Liburdi Engineering Limited | Ductile boron bearing nickel based welding material |
RU2737835C1 (en) * | 2020-06-03 | 2020-12-03 | Акционерное общество "Объединенная двигателестроительная корпорация (АО "ОДК") | Nickel-based heat-resistant wrought alloy and article made from it |
CN114160728A (en) * | 2021-11-18 | 2022-03-11 | 王江明 | Machining process of aviation part turbine fan blade |
RU2777099C1 (en) * | 2021-11-01 | 2022-08-01 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Национального исследовательского центра "Курчатовский институт" (НИЦ "Курчатовский институт" - ВИАМ) | Heat-resistant welded nickel-based alloy and a product made of it |
Families Citing this family (1)
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---|---|---|---|---|
CN106563753A (en) * | 2015-10-08 | 2017-04-19 | 陕西宏远航空锻造有限责任公司 | Forging method of high-temperature alloy turbine moving blade |
Citations (7)
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---|---|---|---|---|
US2447897A (en) * | 1946-05-23 | 1948-08-24 | Armco Steel Corp | High-temperature stainless steel |
CA548777A (en) * | 1957-11-12 | G. Bieber Clarence | Nickel-base heat-resistant alloy | |
US2977222A (en) * | 1955-08-22 | 1961-03-28 | Int Nickel Co | Heat-resisting nickel base alloys |
US2987806A (en) * | 1956-05-24 | 1961-06-13 | Thompson Ramo Wooldridge Inc | Method of making turbine blades and the like |
US3047381A (en) * | 1958-02-03 | 1962-07-31 | Gen Motors Corp | High temperature heat and creep resistant alloy |
US3107999A (en) * | 1959-11-04 | 1963-10-22 | Int Nickel Co | Creep-resistant nickel-chromiumcobalt alloy |
US3110587A (en) * | 1959-06-23 | 1963-11-12 | Int Nickel Co | Nickel-chromium base alloy |
-
1960
- 1960-04-13 GB GB13287/60A patent/GB909948A/en not_active Expired
-
1961
- 1961-04-10 US US101806A patent/US3228095A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA548777A (en) * | 1957-11-12 | G. Bieber Clarence | Nickel-base heat-resistant alloy | |
US2447897A (en) * | 1946-05-23 | 1948-08-24 | Armco Steel Corp | High-temperature stainless steel |
US2977222A (en) * | 1955-08-22 | 1961-03-28 | Int Nickel Co | Heat-resisting nickel base alloys |
US2987806A (en) * | 1956-05-24 | 1961-06-13 | Thompson Ramo Wooldridge Inc | Method of making turbine blades and the like |
US3047381A (en) * | 1958-02-03 | 1962-07-31 | Gen Motors Corp | High temperature heat and creep resistant alloy |
US3110587A (en) * | 1959-06-23 | 1963-11-12 | Int Nickel Co | Nickel-chromium base alloy |
US3107999A (en) * | 1959-11-04 | 1963-10-22 | Int Nickel Co | Creep-resistant nickel-chromiumcobalt alloy |
Cited By (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3301670A (en) * | 1964-01-08 | 1967-01-31 | Int Nickel Co | Cast nickel-base alloy |
US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
US4528048A (en) * | 1982-12-06 | 1985-07-09 | United Technologies Corporation | Mechanically worked single crystal article |
US6093264A (en) * | 1997-01-23 | 2000-07-25 | Ngk Metals Corporation | Nickel-copper-beryllium alloy compositions |
US5980653A (en) * | 1997-01-23 | 1999-11-09 | Ngk Metals Corporation | Nickel-copper-beryllium alloy compositions |
US6112410A (en) * | 1997-09-19 | 2000-09-05 | The Research Corporation Of State University Of New York | Methods for fabricating a structural beam |
US20050155679A1 (en) * | 2003-04-09 | 2005-07-21 | Coastcast Corporation | CoCr alloys and methods for making same |
US20050246895A1 (en) * | 2004-03-03 | 2005-11-10 | Snecma Moteurs | Method of manufacturing a hollow blade for a turbomachine |
US7526862B2 (en) * | 2004-03-03 | 2009-05-05 | Snecma | Method of manufacturing a hollow blade for a turbomachine |
US20150093284A1 (en) * | 2013-09-30 | 2015-04-02 | Liburdi Engineering Limited | Welding material for welding of superalloys |
CN104511702A (en) * | 2013-09-30 | 2015-04-15 | 利宝地工程有限公司 | Welding material for welding of superalloys |
EP2853339A3 (en) * | 2013-09-30 | 2015-08-12 | Liburdi Engineering Limited | Welding material for welding of superalloys |
US10414003B2 (en) * | 2013-09-30 | 2019-09-17 | Liburdi Engineering Limited | Welding material for welding of superalloys |
JP2017519643A (en) * | 2014-04-28 | 2017-07-20 | リバルディ エンジニアリング リミテッド | Malleable boron-supported nickel-based welding material |
EP3137253A4 (en) * | 2014-04-28 | 2017-10-04 | Liburdi Engineering Limited | A ductile boron bearing nickel based welding material |
US10493568B2 (en) | 2014-10-21 | 2019-12-03 | Liburdi Engineering Limited | Ductile boron bearing nickel based welding material |
CZ306719B6 (en) * | 2015-10-25 | 2017-05-24 | Univerzita J. E. Purkyně V Ústí Nad Labem | An aluminium alloy, especially for the production of thin-walled and dimensionally complex castings |
RU2737835C1 (en) * | 2020-06-03 | 2020-12-03 | Акционерное общество "Объединенная двигателестроительная корпорация (АО "ОДК") | Nickel-based heat-resistant wrought alloy and article made from it |
WO2021246908A1 (en) * | 2020-06-03 | 2021-12-09 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Nickel-based heat-resistant wrought alloy and article made from same |
CN115768911A (en) * | 2020-06-03 | 2023-03-07 | 联合发动机制造集团股份公司 | Heat resistant wrought nickel-base alloys and articles thereof |
RU2777099C1 (en) * | 2021-11-01 | 2022-08-01 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Национального исследовательского центра "Курчатовский институт" (НИЦ "Курчатовский институт" - ВИАМ) | Heat-resistant welded nickel-based alloy and a product made of it |
CN114160728A (en) * | 2021-11-18 | 2022-03-11 | 王江明 | Machining process of aviation part turbine fan blade |
RU2798860C1 (en) * | 2022-07-06 | 2023-06-28 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Национального исследовательского центра "Курчатовский институт" (НИЦ "Курчатовский институт" - ВИАМ) | ALLOY BASED ON Ni3Al INTERMETALLIC COMPOUND AND A PRODUCT MADE FROM IT |
RU2794497C1 (en) * | 2022-07-15 | 2023-04-19 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Национального исследовательского центра "Курчатовский институт" (НИЦ "Курчатовский институт" - ВИАМ) | Heat-resistant nickel-based alloy and a product made from it |
RU2802841C1 (en) * | 2022-09-07 | 2023-09-04 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Национального исследовательского центра "Курчатовский институт" (НИЦ "Курчатовский институт" - ВИАМ) | Heat-resistant nickel-based casting alloy and a product made from it |
Also Published As
Publication number | Publication date |
---|---|
GB909948A (en) | 1962-11-07 |
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