WO1999066089A1 - ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION - Google Patents
ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION Download PDFInfo
- Publication number
- WO1999066089A1 WO1999066089A1 PCT/JP1999/003136 JP9903136W WO9966089A1 WO 1999066089 A1 WO1999066089 A1 WO 1999066089A1 JP 9903136 W JP9903136 W JP 9903136W WO 9966089 A1 WO9966089 A1 WO 9966089A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- single crystal
- crystal alloy
- recrystallization
- alloy
- based single
- Prior art date
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5806—Thermal treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
-
- 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
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
- C30B29/10—Inorganic compounds or compositions
- C30B29/52—Alloys
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B33/00—After-treatment of single crystals or homogeneous polycrystalline material with defined structure
Definitions
- the present invention relates to a Ni-based single crystal alloy having a recrystallization crack preventing coating capable of preventing grain boundary cracking due to recrystallization.
- the elements Zr (zirconium), Hf (hafnium), B (boron) and C (carbon) have the effect of strengthening the grain boundaries in the Ni-base superalloy, so that the grain boundary strengthening element, or It is simply called a grain boundary strengthening element. Since these elements adversely affect the structure of the grains and reduce the strength of the Ni-based superalloy, the above-mentioned grain boundary strengthening element is originally added to a Ni-based single crystal alloy having no grain boundaries. No or only slightly added.
- the Ni-based single crystal alloy does not contain or has a small amount of grain boundary strength elements, so that the Ni-based single crystal alloy undergoes recrystallization once.
- the strength of the grain boundary portion becomes lower than that inside the crystal grain. For this reason, when low strain or stress is applied, cracks occur at the grain boundaries, and the cracks cause a problem that the material properties such as creep strength and fatigue strength of the Ni-based single crystal alloy are significantly reduced.
- the present invention provides a Ni-based single crystal alloy to which a grain boundary strengthening element has not been added or a small amount of the element has been added.
- An object of the present invention is to provide a Ni-based single crystal alloy capable of preventing a decrease in strength caused by the above.
- the present invention originally provides a grain boundary strengthening element of the group consisting of Zr, Hi, B and C on the surface of a Ni-based single crystal alloy containing no or a small amount of grain boundary strengthening element. After coating the Ni-based alloy containing at least one or more layers in layers, recrystallization of the above-mentioned Ni-based single crystal alloy occurs.
- the grain boundary strengthening element exists in the very surface layer of the Ni-based single crystal alloy member, for example, within a range of 20 to 250 m inside the surface of the Ni-based single crystal alloy, the grain boundary strengthening element is provided.
- the effect that the addition of the element reduces the strength of the base material is small.
- a Ni-based single crystal alloy member is used as a base material, and a Ni-based alloy coating is formed in a layer on the surface thereof.
- This Ni-based single crystal alloy member has a low content of an element having a grain boundary strengthening effect.
- “the content of the element having the effect of strengthening the grain boundary is low” means that the grain boundary strengthening element is not added or the amount is small.
- the Ni-based alloy coating is made of a Ni-based alloy containing at least one of the group consisting of Zr, Hf, B and B as a grain boundary strengthening element.
- the content of grain boundary strengthening elements present in Zr is 0.1 wt% or less, Hf is 10 wt% or less, B is 0.1 wt% or less, and C is 0.5 wt% or less.
- the lower limit is preferably 0.01% by weight for ⁇ ] ", 0.1% by weight for?, 0.05% by weight for B, and 0.01% by weight for C.
- the crystal grains in the Ni-based alloy coating The composition other than the boundary strengthening element enhances the adhesion to the base metal, Ni-base single crystal alloy, and strengthens the grain boundary during coating of the Ni-base alloy. In order to suppress the diffusion of elements other than elements, it is preferable that the composition is the same as or similar to the composition of the Ni-based single crystal alloy member.
- Ni-based alloy coating on the surface of the Ni-based single crystal alloy member
- various methods such as thermal spraying, physical vapor deposition (including EB-PVD), and chemical vapor deposition can be used. Is not particularly limited. Its thickness is suitably 5 to 200 m.
- the above-mentioned Ni-based alloy coating can be applied when newly manufacturing a Ni-based single crystal alloy member or before applying re-heat treatment to restore the strength of a used Ni-based single crystal alloy member. good.
- the Ni-based single crystal alloy member is heat-treated at a temperature at which recrystallization does not occur, for example, 800 to 1300, for 50 to 0.5 hours, and the grain boundary strengthening element in the Ni-based alloy coating is heated. Is diffused to form a recrystallization crack preventing coating (hereinafter, also referred to as a recrystallization cracking resistant coating) only on the surface of the Ni-based single crystal alloy member.
- a recrystallization crack preventing coating hereinafter, also referred to as a recrystallization cracking resistant coating
- Ni-based single crystal alloy (base material) to be used in the present invention examples include, for example, CMS X-2 and CMSX-4 (both manufactured by Canon Muskegon Co., USA) having the compositions shown in Table 1 below. Name) and MC-2 (product name of Aubert Kurd, France).
- Bal of the Ni component means the remainder, and the units of the numbers are all wt%.
- CM247 (a product name of Cannon Muskegon Co., USA), which is an existing alloy containing Zr, Hf, B and C.
- the typical composition of this CM247 is, by weight%, 8.2% (: 10.0% (30, 0.6% Mo, 10.0% W, 3.0% Ta, 1. 0% Ti, 5.5% Al, 0.020% B, 0.16% C, 0.09% Zr, 1.5% Hf, and N for i It is.
- CMS X-2 (a product name of Canon Muskegon Co., Ltd.) described in U.S. Pat. No. 4,582,548 was used as a Ni-based single crystal alloy member as a base material.
- the typical composition of this CMS X-2 is, by weight%, 4.3-4.9% (: 0, 7.5-8.2% Cr, 0.3-0.7% Mo, 7% 6-8.4% W, 5.8-6.2% Ta, 5.45-6.2% A and 0.8-: L. 2% T i, and 3 ⁇ 4 part N i.
- the Ni-based alloy coating serving as a recrystallization crack preventing coating is reduced to a thickness of about 10 by low-pressure plasma spraying. Formed.
- the composition of the Ni-based alloy coating is 0.1% r, 0.1% ⁇ , 7.5% Cr, 4% Co, 0.5% Mo, 7.5% by weight. % W, 6% Ding & 1% Ding 5.5% 8 1, and the rest consist of Ni.
- a comparative material As a comparative material, a comparative material (DdXD was prepared as described below. Among these, comparative material 1 was prepared by subjecting a surface of a CMS X-2 single crystal alloy to processing strain due to dalid plast, The heat treatment was performed at 1200 ° C for 4 hours. The comparative material CM was heat-treated at 1200 ° C for 4 hours without giving a work strain due to dalid plast to the surface of CMSX-2 single crystal alloy As a comparative material (3), CMSX-2 single crystal alloy is coated with the same composition as CMSX-2, which does not contain Zr, Hf, B, or C, after processing strain is applied to the surface by grid blasting. Was applied to a thickness of about 100 micrometer by low pressure plasma spraying and heat treated at 1200 ° C for 4 hours This heat treatment was performed in vacuum at 1200 ° C for 4 hours. Table 2 summarizes the test materials. Table 2
- the presence or absence of recrystallization was confirmed by observing the cross-sectional structures of the inventive material 1 and the comparative material.
- the material of the present invention 1, the comparative material 2 and the comparative material 3 are the surfaces of the CMSX-2 single crystal alloy (in the material 1 of the present invention, the single crystal alloy side of the interface between the CMSX-2 single crystal alloy and the recrystallization crack preventing coating) ), A recrystallized layer having a width of about 10 micrometers was observed, but no recrystallized layer was observed in the comparative material.
- the test conditions for the high cycle fatigue test were the Ono-type rotary bending test method, with the test temperature: 900 ° C, stress amplitude: 40 kg / mm, frequency: 60 Hz. The results are shown in Table 3.
- CMS X-2 was used as the base material single crystal alloy.
- the composition of this CMSX-2 is, by weight: 7.9% Cr, 4.6% Co, 0.6% Mo, 8.0% W, 6% Ta, 1% T i, 5.6% of A 1, and the balance Ni.
- Ni-based alloy coating serving as a recrystallization crack preventing coating is formed on the surface by physical vapor deposition to a thickness of about 100 ⁇ m. Formed.
- the composition of this Ni-based alloy coating is, by weight: 3.0% Hf, 0.2% (:, 7.5% Cr, 4% Co, 0.5% Mo, 7.
- Comparative Material ⁇ was prepared by subjecting the surface of CMS X-2 single crystal alloy to processing strain due to grid plasts and then heat-treating at 1200 ° C for 4 hours.
- Heat treatment was performed at 1200 for 4 hours without giving any processing strain due to dalipid plast to the surface of the single crystal alloy.
- comparison material II after applying a machining strain by grid blasting to the surface of CMS X-2 single crystal alloy, a coating of the same composition as CMSX-2 without Zr, Hf, B or C was applied by physical vapor deposition. It is formed to a thickness of about 100 micrometers and heat-treated at 120 Ot: for 4 hours. This heat treatment was performed in a vacuum at a temperature of 120 for 4 hours. Table 4 summarizes these test materials.
- test conditions for high-cycle fatigue test by Ono type rotating bending test method, the test temperature is 900 ° C, stress 4 0 k gZmm 2 added conducted under conditions of frequency 6 0Hz, the results are shown in Table 5.
- Test temperature 900 ° C
- the comparative material ⁇ clearly shows a decrease in fracture life due to recrystallization from the comparison with the comparative material 5.
- the material 2 of the present invention had a shorter life than the comparative material 2 which did not undergo recrystallization, but had a clearly longer life than the comparative material 2.
- the material 2 of the present invention clearly had a longer life than the comparative material 2, and the results of Hf and C in the recrystallization crack preventing coating were clearly shown.
- CMS X-2 was used as the single crystal alloy as the base material.
- the composition of this CMS X-2 is, by weight: 7.9% Cr, 4.6% Co, 0.6% Mo, 8.0% W, 6% Ta, 1%
- the portion A of 5.6% of Ti is Ni.
- the composition of the first type of Ni-based alloy coating (material 3 of the present invention) was 0.1% by weight of “!” And 0.1% by weight.
- 1% B 0.1% C, 7.5% Cr, 4% Co, 0.5% Mo, 7.5% W, 6% Ding & 1% Ding 5
- the composition of the second Ni-based alloy coating (material 4 of the present invention) is 0.3% C, 7.5% C by weight%.
- a comparative material (EXD described below was prepared.
- the comparative material ⁇ was subjected to a machining strain due to a dalipid plast on the surface of the CMSX-2 single crystal alloy, and was subjected to 1200- The heat treatment was performed for 4 hours, and Comparative Material No. 4 was a heat treatment performed at 1200 ° C for 4 hours without subjecting the surface of the CMSX-2 single crystal alloy to processing strain due to dalipid plast.
- Comparative Material No. 4 was a heat treatment performed at 1200 ° C for 4 hours without subjecting the surface of the CMSX-2 single crystal alloy to processing strain due to dalipid plast.
- a coating of the same composition as CMSX-2 without Zr, Hf, B or C was applied by high-speed flame spraying. It was formed to a thickness of about 200 micrometers and subjected to a heat treatment for 4 hours at 1200 ° C. This heat treatment was performed in a vacuum at a temperature of 1200 for 4 hours. The results are summarized in Fig.
- the test conditions for the high-cycle fatigue test were the Ono-type rotary bending test method, with a test temperature of 900 ° (: applied stress of 40 kg / mm and a frequency of 6 OHz. Shown in
- the comparison material 7 clearly shows a decrease in fracture life due to recrystallization from the comparison material 8.
- the materials of the present invention 3 and 4 showed a longer life than the comparative material ⁇ ⁇ , though the life was shorter than that of the comparative material ⁇ ⁇ ⁇ without recrystallization.
- the inventive materials 3 and 4 have a clearly longer life than the comparative material ⁇ , and the results of the composite addition of B and C in the coating for preventing recrystallization cracking and the addition of C alone are clearly shown.
- the present invention can be used, for example, in a process for strengthening the surface of a turbine blade used under high temperatures.
- the crystal grain boundaries generated during recrystallization are strengthened, and the material strength characteristics after recrystallization are improved. be able to.
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Inorganic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA002301092A CA2301092A1 (en) | 1998-06-15 | 1999-06-11 | Ni-based single crystal alloy having coating film for preventing recrystallization fracture |
EP99924009A EP1036850A4 (en) | 1998-06-15 | 1999-06-11 | NICKEL-BASED SINGLE CRYSTAL ALLOY WITH COATING FILM TO PREVENT CRYSTALIZATION BREAKING |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP10/166849 | 1998-06-15 | ||
JP16684998 | 1998-06-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1999066089A1 true WO1999066089A1 (fr) | 1999-12-23 |
Family
ID=15838799
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1999/003136 WO1999066089A1 (fr) | 1998-06-15 | 1999-06-11 | ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP1036850A4 (ja) |
CA (1) | CA2301092A1 (ja) |
WO (1) | WO1999066089A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019523825A (ja) * | 2016-06-10 | 2019-08-29 | サフラン | ハフニウムを含有するニッケル系超合金でできた部品の製造方法 |
CN112301315A (zh) * | 2020-09-18 | 2021-02-02 | 中国航发北京航空材料研究院 | 一种在涂层制备扩散过程中抑制单晶再结晶的方法 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6719853B2 (en) | 2001-04-27 | 2004-04-13 | Siemens Aktiengesellschaft | Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane |
EP1284390A1 (de) | 2001-06-27 | 2003-02-19 | Siemens Aktiengesellschaft | Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
EP1595968A1 (de) * | 2004-04-30 | 2005-11-16 | Siemens Aktiengesellschaft | Wärmebehandlungsverfahren für einkristalline oder direktional verfestigte Bauteile |
US20110256421A1 (en) * | 2010-04-16 | 2011-10-20 | United Technologies Corporation | Metallic coating for single crystal alloys |
CN107119325B (zh) * | 2017-06-26 | 2019-03-12 | 中国科学院金属研究所 | 一种消除激光3d打印单晶高温合金再结晶倾向的方法 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH05247569A (ja) * | 1991-12-05 | 1993-09-24 | General Electric Co <Ge> | 拡散アルミナイド被覆をもつニッケル基超合金基体の安定化 |
JPH0770678A (ja) * | 1993-09-07 | 1995-03-14 | Hitachi Metals Ltd | 高強度超合金および高強度単結晶鋳造物 |
JPH09157778A (ja) * | 1995-12-12 | 1997-06-17 | Mitsubishi Materials Corp | 耐熱疲労特性、高温クリープおよび高温耐食性に優れたNi基単結晶合金 |
JPH09291379A (ja) * | 1995-12-22 | 1997-11-11 | General Electric Co <Ge> | 至適化された白金アルミニド皮膜を有するニッケル基超合金 |
JPH10168556A (ja) * | 1996-07-23 | 1998-06-23 | Rolls Royce Plc | プラチナ・アルミナイジングされた単一結晶超合金 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4582548A (en) * | 1980-11-24 | 1986-04-15 | Cannon-Muskegon Corporation | Single crystal (single grain) alloy |
US5043138A (en) * | 1983-12-27 | 1991-08-27 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
US4921405A (en) * | 1988-11-10 | 1990-05-01 | Allied-Signal Inc. | Dual structure turbine blade |
CA2076091A1 (en) * | 1991-09-09 | 1993-03-10 | Edward H. Goldman | Superalloy component with dispersion-containing protective coatings, and method of preparation |
US5316866A (en) * | 1991-09-09 | 1994-05-31 | General Electric Company | Strengthened protective coatings for superalloys |
-
1999
- 1999-06-11 CA CA002301092A patent/CA2301092A1/en not_active Abandoned
- 1999-06-11 EP EP99924009A patent/EP1036850A4/en not_active Withdrawn
- 1999-06-11 WO PCT/JP1999/003136 patent/WO1999066089A1/ja not_active Application Discontinuation
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH05247569A (ja) * | 1991-12-05 | 1993-09-24 | General Electric Co <Ge> | 拡散アルミナイド被覆をもつニッケル基超合金基体の安定化 |
JPH0770678A (ja) * | 1993-09-07 | 1995-03-14 | Hitachi Metals Ltd | 高強度超合金および高強度単結晶鋳造物 |
JPH09157778A (ja) * | 1995-12-12 | 1997-06-17 | Mitsubishi Materials Corp | 耐熱疲労特性、高温クリープおよび高温耐食性に優れたNi基単結晶合金 |
JPH09291379A (ja) * | 1995-12-22 | 1997-11-11 | General Electric Co <Ge> | 至適化された白金アルミニド皮膜を有するニッケル基超合金 |
JPH10168556A (ja) * | 1996-07-23 | 1998-06-23 | Rolls Royce Plc | プラチナ・アルミナイジングされた単一結晶超合金 |
Non-Patent Citations (1)
Title |
---|
See also references of EP1036850A4 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019523825A (ja) * | 2016-06-10 | 2019-08-29 | サフラン | ハフニウムを含有するニッケル系超合金でできた部品の製造方法 |
CN112301315A (zh) * | 2020-09-18 | 2021-02-02 | 中国航发北京航空材料研究院 | 一种在涂层制备扩散过程中抑制单晶再结晶的方法 |
Also Published As
Publication number | Publication date |
---|---|
CA2301092A1 (en) | 1999-12-23 |
EP1036850A4 (en) | 2003-05-02 |
EP1036850A1 (en) | 2000-09-20 |
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