CN102776512B - Method for preparing novel gradient thermal barrier coating - Google Patents
Method for preparing novel gradient thermal barrier coating Download PDFInfo
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- CN102776512B CN102776512B CN201210283972.7A CN201210283972A CN102776512B CN 102776512 B CN102776512 B CN 102776512B CN 201210283972 A CN201210283972 A CN 201210283972A CN 102776512 B CN102776512 B CN 102776512B
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- 238000000034 method Methods 0.000 title claims abstract description 26
- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 24
- 239000000843 powder Substances 0.000 claims abstract description 70
- 238000002360 preparation method Methods 0.000 claims abstract description 30
- 239000000919 ceramic Substances 0.000 claims abstract description 25
- 238000005507 spraying Methods 0.000 claims abstract description 23
- 239000000463 material Substances 0.000 claims abstract description 20
- 239000011248 coating agent Substances 0.000 claims abstract description 17
- 238000000576 coating method Methods 0.000 claims abstract description 17
- 239000010410 layer Substances 0.000 claims description 25
- 239000007921 spray Substances 0.000 claims description 20
- 239000012790 adhesive layer Substances 0.000 claims description 18
- 229910045601 alloy Inorganic materials 0.000 claims description 14
- 239000000956 alloy Substances 0.000 claims description 14
- 238000005498 polishing Methods 0.000 claims description 12
- 150000001875 compounds Chemical class 0.000 claims description 9
- 239000000758 substrate Substances 0.000 claims description 9
- 238000000137 annealing Methods 0.000 claims description 8
- 238000000151 deposition Methods 0.000 claims description 8
- 238000000227 grinding Methods 0.000 claims description 8
- 238000005406 washing Methods 0.000 claims description 8
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 6
- 239000008367 deionised water Substances 0.000 claims description 4
- 238000001035 drying Methods 0.000 claims description 4
- 238000005488 sandblasting Methods 0.000 claims description 4
- 238000004062 sedimentation Methods 0.000 claims description 4
- 230000003064 anti-oxidating effect Effects 0.000 abstract 1
- 230000003647 oxidation Effects 0.000 description 7
- 238000007254 oxidation reaction Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 5
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 3
- 239000004411 aluminium Substances 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 229910052749 magnesium Inorganic materials 0.000 description 3
- 239000011777 magnesium Substances 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
- 230000003078 antioxidant effect Effects 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 239000004519 grease Substances 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000000395 magnesium oxide Substances 0.000 description 2
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 2
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 description 2
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 2
- 230000002000 scavenging effect Effects 0.000 description 2
- 229910052717 sulfur Inorganic materials 0.000 description 2
- 230000003746 surface roughness Effects 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- BRPQOXSCLDDYGP-UHFFFAOYSA-N calcium oxide Chemical compound [O-2].[Ca+2] BRPQOXSCLDDYGP-UHFFFAOYSA-N 0.000 description 1
- 239000000292 calcium oxide Substances 0.000 description 1
- ODINCKMPIJJUCX-UHFFFAOYSA-N calcium oxide Inorganic materials [Ca]=O ODINCKMPIJJUCX-UHFFFAOYSA-N 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 229910052814 silicon oxide Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 description 1
Classifications
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a method for preparing a novel gradient thermal barrier coating, which comprises the following steps: a) preparing spraying powder material; b) pre-treating base material; c) spraying a bonding layer; d) spraying a ceramic layer; and e) post-treating the coating. The method for preparing the novel gradient thermal barrier coating is disclosed by the invention; the method is characterized by compact working procedure arrangement, reasonable component preparation and suitable coat; the bonding layer of the coating contains oxide which easily forms an oxide film; the content of the oxide is changed in a gradient manner; thus, the prepared thermal barrier coating has good heat-resistant performance while anti-oxidation capacity is highlighted.
Description
technical field
The present invention relates to a kind of preparation method of thermal barrier coating, relate in particular to a kind of preparation method of the Thermal Barrier Coatings with gradient antioxidant property, belong to metallic coating technical field.
Background technology
Along with aircraft engine is to the development of high flow capacity ratio, high thrust-weight ratio and high turbine intake temperature direction, fuel gas temperature and gaseous-pressure in engine chamber improve constantly in recent years.In the time that the thrust-weight ratio of engine reaches 20, fuel gas inlet temperature will exceed 2000 DEG C, this temperature has exceeded manufactures the temperature that the nickel base superalloy of turbine blade and turning vane can bear, even if adopt inter-metallic compound material and utilize directional solidification technique to be also difficult to bear.Adopt pressurized air limited to the cooling performance of blade, and cooling technology is in reducing leaf temperature, inevitably loses heat greatly, has reduced the efficiency of engine.In this case, resist engine blade high temperature another kind of effective way---thermal barrier coating also just arises at the historic moment, become one of most active research topic in international high temperature coating field in recent years.
For high-temperature protection coating part, oxidation is one of major reason causing part failure, and the raising of its antioxidant property depends on the oxide film in thermal barrier coating, and its main component is generally aluminum oxide, magnesium oxide and silicon oxide.At high temperature, the oxide film of even compact has excellent thermostability, low spread coefficient, therefore, in protective coating, wish to add the element such as aluminium, magnesium that content is higher to generate oxide film, do not make matrix oxidated or reduce rate of oxidation, extend part work-ing life.In current technology, adopt solid bury bag infiltration method can realize the element such as aluminium, magnesium gradient infiltrate, to form high-quality oxide film, but this kind of process implementing cost is high, process procedure complexity, operational requirement is high, practicality is not good enough.
Summary of the invention
For the demand, the invention provides a kind of preparation method of Thermal Barrier Coatings, in the tack coat of this coating, contain the oxide compound that is easy to form oxide film, and oxide content has graded, make the thermal barrier coating that makes have good heat resistance can in resistance of oxidation outstanding.
The present invention is a kind of preparation method of Thermal Barrier Coatings, and this preparation method comprises the steps: a) preparation spraying powder, b) pretreatment of base material, c) spraying tack coat, d) ceramic coated layer, e) coating aftertreatment.
In a preferred embodiment of the present invention, in described step a), spraying powder comprises tack coat powder and ceramic layer powder; In tack coat powder, the granularity of MCrAlY alloy is 200-300 order, and the granularity that can form the oxide compound of oxide film is 300-400 order; Granularity after ceramic layer powder grinds is 500-600 order.
In a preferred embodiment of the present invention, in described step b), pretreatment of base material comprises sandblasting, ultrasonic washing, washed with de-ionized water and drying and processing.
In a preferred embodiment of the present invention, in described step c), tack coat adopts plasma spray coating process to be prepared, adopt the mode of two spray guns parallel powder feeding simultaneously, spray gun translational speed is 200-220mm/s, spray gun spout and base material distance are controlled at 80-100mm, and spray voltage is 30-40V, and spray time is controlled at 20-30 minute.
In a preferred embodiment of the present invention, first described lance ejection MCrAlY alloy powder, powder feeding gas is selected H
2, flow is 15-20L/min, powder feeding rate declines slightly with the increase of adhesive layer thickness, is down to 22g/min by 25g/min, and the every increase of adhesive layer thickness 0.02mm, powder feeding rate reduces 1g/min; Second lance ejection alumina powder, powder feeding gas is selected Ar, and flow is 50-55L/min, and powder feeding rate raises slightly with the increase of adhesive layer thickness, rises to 15g/min by 10g/min, the every increase of adhesive layer thickness 0.02mm, powder feeding rate increases 1.5g/min.
In a preferred embodiment of the present invention, in described step d), the ceramic layer powder after grinding is made into target, carry out the preparation of ceramic layer by electro beam physics vapour deposition technique; Vacuum tightness in vacuum chamber is 0.001-0.0001Pa, and base material rotating speed is 10-15rpm, and sedimentation velocity is 2.5-3 μ m/min, and depositing time is 40-50min.
In a preferred embodiment of the present invention, in described step e), coating aftertreatment comprises stress relief annealing and sanding and polishing processing; Stress relief annealing temperature is controlled at below 450 DEG C, and the time is 2-3 hour; Sanding and polishing processing can be used abrasive band, and the roughness value of the substrate surface after polishing can reach 0.06 μ m.
The present invention has disclosed a kind of preparation method of Thermal Barrier Coatings, this preparation method's procedure arrangement compactness, become assignment system reasonable, cost is moderate, in the tack coat of coating, contain the oxide compound that is easy to form oxide film, and oxide content has graded, the thermal barrier coating resistance of oxidation in having good heat resistance energy making is given prominence to.
Brief description of the drawings
Below in conjunction with the drawings and specific embodiments, the present invention is further detailed explanation:
Fig. 1 is the preparation method's of embodiment of the present invention Thermal Barrier Coatings process figure.
Embodiment
Below in conjunction with accompanying drawing, preferred embodiment of the present invention is described in detail, thereby so that advantages and features of the invention can be easier to be it will be appreciated by those skilled in the art that, protection scope of the present invention is made to more explicit defining.
Fig. 1 is the preparation method's of embodiment of the present invention Thermal Barrier Coatings process figure; This preparation method comprises the steps: a) preparation spraying powder, b) pretreatment of base material, c) spraying tack coat, d) ceramic coated layer, e) coating aftertreatment.
The preparation method's of the Thermal Barrier Coatings that embodiment 1 the present invention mentions concrete implementation step is as follows: a) preparation spraying powder, and this spraying powder comprises tack coat powder and ceramic layer powder; Wherein, tack coat powder is made up of MCrAlY alloy and the oxide compound that can form oxide film, and two components need be prepared separately; The main component of MCrAlY alloy is: Co, Cr, Al, S and Ni, and after grinding, the granularity of MCrAlY alloy is 250 orders; The oxide compound that can form oxide film is selected aluminum oxide, grinds the granularity control of rear oxidation aluminium at 350 orders; Ceramic layer powder is selected yttria-stabilized zirconia pottery, and the granularity after grinding is 550 orders; B) pretreatment of base material, pretreatment of base material comprises sandblasting, ultrasonic washing, washed with de-ionized water and drying and processing; 150 object glass balls are selected in sandblast, and pressure is 0.7MPa, and surface roughness value is 0.6 μ m left and right; When ultrasonic washing, adopt acetone as washing composition, scavenging period is 15 minutes, can remove all kinds of greasy dirts and the grease of substrate surface; Bake out temperature in baking oven is controlled at 60 DEG C of left and right, and the time is 5 minutes; C) spraying tack coat, bonding layer material is selected MCrAlY alloy powder and the alumina powder that percentage composition ratio is 94%: 6%, adopts plasma spray coating process to be prepared; In plasma spray coating process implementation process, adopt the mode of two spray guns parallel powder feeding simultaneously, spray gun translational speed is 200mm/s, and spray gun spout and substrate surface distance are controlled at 90mm, and spray voltage is 35V; Wherein, a lance ejection MCrAlY alloy powder, powder feeding gas is selected H
2, flow is 15L/min, powder feeding rate declines slightly with the increase of adhesive layer thickness, is down to 22g/min left and right by 25g/min, and the every increase of adhesive layer thickness 0.02mm, powder feeding rate reduces 1g/min; Another root lance ejection alumina powder, powder feeding gas is selected Ar, and flow is 50L/min, and powder feeding rate raises slightly with the increase of adhesive layer thickness, rises to 15g/min left and right by 10g/min, the every increase of adhesive layer thickness 0.02mm, powder feeding rate increases 1.5g/min; Spray time is controlled at 25 minutes, the about 0.9mm of adhesive layer thickness that can make; D) ceramic coated layer, is made into target by the ceramic layer powder after grinding, and carries out the preparation of ceramic layer by electro beam physics vapour deposition technique; In this process implementing process, the vacuum tightness in vacuum chamber is 0.0005Pa, and base material rotating speed is 15rpm, and sedimentation velocity is 3 μ m/min, and depositing time is 50min, can make the ceramic layer that thickness is 0.15mm; E) coating aftertreatment, coating aftertreatment comprises stress relief annealing and sanding and polishing processing; Stress relief annealing temperature is controlled at 420 DEG C, and the time is 2.5 hours, eliminates and is coated with the internal stress of interlayer, improves interfacial bonding strength, and further stable dimensions; Sanding and polishing processing can be used abrasive band, and the roughness value of the substrate surface after polishing can reach 0.06 μ m.
The preparation method's of the Thermal Barrier Coatings that embodiment 2 the present invention mention concrete implementation step is as follows: a) preparation spraying powder, and this spraying powder comprises tack coat powder and ceramic layer powder; Wherein, tack coat powder is made up of MCrAlY alloy and the oxide compound that can form oxide film, and two components need be prepared separately; The main component of MCrAlY alloy is: Co, Cr, Al, S and Ni, and after grinding, the granularity of MCrAlY alloy is 250 orders; The oxide compound that can form oxide film is selected magnesium oxide, grinds the granularity control of rear oxidation magnesium at 400 orders; Ceramic layer powder is stable calcium oxide zirconia ceramics material, and the granularity after grinding is 600 orders; B) pretreatment of base material, pretreatment of base material comprises sandblasting, ultrasonic washing, washed with de-ionized water and drying and processing; 150 object glass balls are selected in sandblast, and pressure is 0.6MPa, and surface roughness value is 0.6 μ m left and right; When ultrasonic washing, adopt acetone as washing composition, scavenging period is 12 minutes, can remove all kinds of greasy dirts and the grease of substrate surface; Bake out temperature in baking oven is controlled at 60 DEG C of left and right, and the time is 20 minutes; C) spraying tack coat, bonding layer material is selected MCrAlY alloy powder and the alumina powder that percentage composition ratio is 94.5%: 5.5%, adopts plasma spray coating process to be prepared; In plasma spray coating process implementation process, adopt the mode of two spray guns parallel powder feeding simultaneously, spray gun translational speed is 220mm/s, and spray gun spout and substrate surface distance are controlled at 100mm, and spray voltage is 40V; Wherein, a lance ejection MCrAlY alloy powder, powder feeding gas is selected H
2, flow is 20L/min, powder feeding rate declines slightly with the increase of adhesive layer thickness, is down to 22g/min left and right by 25g/min, and the every increase of adhesive layer thickness 0.02mm, powder feeding rate reduces 1g/min; Another root lance ejection alumina powder, powder feeding gas is selected Ar, and flow is 55L/min, and powder feeding rate raises slightly with the increase of adhesive layer thickness, rises to 15g/min left and right by 10g/min, the every increase of adhesive layer thickness 0.02mm, powder feeding rate increases 1.5g/min; Spray time is controlled at 30 minutes, and the adhesive layer thickness that can make is about 0.1mm; D) ceramic coated layer, is made into target by the ceramic layer powder after grinding, and carries out the preparation of ceramic layer by electro beam physics vapour deposition technique; In this process implementing process, the vacuum tightness in vacuum chamber is 0.0005Pa, and base material rotating speed is 12rpm, and sedimentation velocity is 2.5 μ m/min, and depositing time is 40min, can make the ceramic layer that thickness is 0.1mm; E) coating aftertreatment, coating aftertreatment comprises stress relief annealing and sanding and polishing processing; Stress relief annealing temperature is controlled at below 400 DEG C, and the time is 3 hours, eliminates and is coated with the internal stress of interlayer, improves interfacial bonding strength, and further stable dimensions; Sanding and polishing processing can be used abrasive band, and the roughness value of the substrate surface after polishing can reach 0.06 μ m.
The present invention has disclosed a kind of preparation method of Thermal Barrier Coatings, be characterized in: this preparation method's procedure arrangement compactness, become assignment system reasonable, cost is moderate, in the tack coat of coating, contain the oxide compound that is easy to form oxide film, and oxide content has graded, the thermal barrier coating resistance of oxidation in having good heat resistance energy making is given prominence to.
The above; it is only the specific embodiment of the present invention; but protection scope of the present invention is not limited to this; any those of ordinary skill in the art are in the disclosed technical scope of the present invention; the variation that can expect without creative work or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain that claims were limited.
Claims (4)
1. a preparation method for Thermal Barrier Coatings, is characterized in that, this preparation method comprises the steps: a) preparation spraying powder, b) pretreatment of base material, and c) spraying tack coat, d) ceramic coated layer, e) coating aftertreatment,
In described step c), tack coat adopts plasma spray coating process to be prepared, adopt the mode of two spray guns parallel powder feeding simultaneously, spray gun translational speed is 200-220mm/s, spray gun spout and substrate surface distance are controlled at 80-100mm, spray voltage is 30-40V, and spray time is controlled at 20-30 minute.First lance ejection MCrAlY alloy powder, powder feeding gas is selected H
2, flow is 15-20L/min, powder feeding rate declines slightly with the increase of adhesive layer thickness, is down to 22g/min by 25g/min, and the every increase of adhesive layer thickness 0.02mm, powder feeding rate reduces 1g/min; Second lance ejection alumina powder, powder feeding gas is selected Ar, and flow is 50-55L/min, and powder feeding rate raises slightly with the increase of adhesive layer thickness, rises to 15g/min by 10g/min, the every increase of adhesive layer thickness 0.02mm, powder feeding rate increases 1.5g/min; In described step d), the ceramic layer powder after grinding is made into target, carries out the preparation of ceramic layer by electro beam physics vapour deposition technique; Vacuum tightness in vacuum chamber is 0.001-0.0001Pa, and base material rotating speed is 10-15rpm, and sedimentation velocity is 2.5-3 μ m/min, and depositing time is 40-50min.
2. according to the preparation method of the Thermal Barrier Coatings described in claim 1, it is characterized in that, in described step a), spraying powder comprises tack coat powder and ceramic layer powder; In tack coat powder, the granularity of MCrAlY alloy is 200-300 order, and the granularity that can form the oxide compound of oxide film is 300-400 order; Granularity after ceramic layer powder grinds is 500-600 order.
3. according to the preparation method of the Thermal Barrier Coatings described in claim 1, it is characterized in that, in described step b), pretreatment of base material comprises sandblasting, ultrasonic washing, washed with de-ionized water and drying and processing.
4. according to the preparation method of the Thermal Barrier Coatings described in claim 1, it is characterized in that, in described step e), coating aftertreatment comprises stress relief annealing and sanding and polishing processing; Stress relief annealing temperature is controlled at below 450 DEG C, and the time is 2-3 hour; Sanding and polishing processing can be used abrasive band, and the roughness value of the substrate surface after polishing can reach 0.06 μ m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210283972.7A CN102776512B (en) | 2012-08-10 | 2012-08-10 | Method for preparing novel gradient thermal barrier coating |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210283972.7A CN102776512B (en) | 2012-08-10 | 2012-08-10 | Method for preparing novel gradient thermal barrier coating |
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| CN102776512A CN102776512A (en) | 2012-11-14 |
| CN102776512B true CN102776512B (en) | 2014-07-23 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102963061A (en) * | 2012-12-03 | 2013-03-13 | 上海理工大学 | Nano columnar crystal thermal barrier coating layer and preparation method thereof |
| CN105624602B (en) * | 2014-10-28 | 2018-11-02 | 北京美桥电子设备有限公司 | Y applied to aluminum-based base material3Al5O12Method for producing a coating |
| DE102016002630A1 (en) * | 2016-03-07 | 2017-09-07 | Forschungszentrum Jülich GmbH | Adhesive layer for bonding a high-temperature protective layer on a substrate, and method for producing the same |
| CN105929862A (en) * | 2016-04-13 | 2016-09-07 | 广州市尤特新材料有限公司 | Impurity control method for high-purity rotary target material |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1045425A (en) * | 1989-03-06 | 1990-09-19 | 联合工艺公司 | The aluminide coating of the enrichment yttrium that the confession ultrahigh temperature alloy is used |
| CN1243194A (en) * | 1998-06-12 | 2000-02-02 | 联合工艺公司 | Heat-barrier coating series |
| WO2004055245A3 (en) * | 2002-12-18 | 2004-09-02 | Siemens Ag | Method for the deposition of an alloy on a substrate |
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2012
- 2012-08-10 CN CN201210283972.7A patent/CN102776512B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1045425A (en) * | 1989-03-06 | 1990-09-19 | 联合工艺公司 | The aluminide coating of the enrichment yttrium that the confession ultrahigh temperature alloy is used |
| CN1243194A (en) * | 1998-06-12 | 2000-02-02 | 联合工艺公司 | Heat-barrier coating series |
| WO2004055245A3 (en) * | 2002-12-18 | 2004-09-02 | Siemens Ag | Method for the deposition of an alloy on a substrate |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140723 Termination date: 20160810 |