FR2601044A1 - METHOD FOR DEPOSITING A PROTECTIVE LAYER AND PIECE PROVIDED WITH SUCH A LAYER - Google Patents
METHOD FOR DEPOSITING A PROTECTIVE LAYER AND PIECE PROVIDED WITH SUCH A LAYER Download PDFInfo
- Publication number
- FR2601044A1 FR2601044A1 FR8703313A FR8703313A FR2601044A1 FR 2601044 A1 FR2601044 A1 FR 2601044A1 FR 8703313 A FR8703313 A FR 8703313A FR 8703313 A FR8703313 A FR 8703313A FR 2601044 A1 FR2601044 A1 FR 2601044A1
- Authority
- FR
- France
- Prior art keywords
- titanium
- layer
- nickel
- alloy
- cobalt
- 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.)
- Granted
Links
- 239000010410 layer Substances 0.000 title claims abstract description 26
- 239000011241 protective layer Substances 0.000 title claims abstract description 13
- 238000000034 method Methods 0.000 title claims description 12
- 238000000151 deposition Methods 0.000 title claims description 10
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 40
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 26
- 239000010936 titanium Substances 0.000 claims abstract description 26
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 26
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 25
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 20
- 239000010941 cobalt Substances 0.000 claims abstract description 15
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 15
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 15
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052804 chromium Inorganic materials 0.000 claims description 12
- 239000011651 chromium Substances 0.000 claims description 12
- 229910045601 alloy Inorganic materials 0.000 claims description 11
- 239000000956 alloy Substances 0.000 claims description 11
- 238000009713 electroplating Methods 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000001590 oxidative effect Effects 0.000 claims description 3
- 238000005137 deposition process Methods 0.000 claims 3
- 230000015572 biosynthetic process Effects 0.000 abstract description 4
- 230000003647 oxidation Effects 0.000 abstract description 3
- 238000007254 oxidation reaction Methods 0.000 abstract description 3
- 238000005246 galvanizing Methods 0.000 abstract description 2
- QTBSBXVTEAMEQO-UHFFFAOYSA-N Acetic acid Chemical compound CC(O)=O QTBSBXVTEAMEQO-UHFFFAOYSA-N 0.000 description 6
- KRHYYFGTRYWZRS-UHFFFAOYSA-N Fluorane Chemical compound F KRHYYFGTRYWZRS-UHFFFAOYSA-N 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- QAOWNCQODCNURD-UHFFFAOYSA-N Sulfuric acid Chemical compound OS(O)(=O)=O QAOWNCQODCNURD-UHFFFAOYSA-N 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 230000008021 deposition Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- KRVSOGSZCMJSLX-UHFFFAOYSA-L chromic acid Substances O[Cr](O)(=O)=O KRVSOGSZCMJSLX-UHFFFAOYSA-L 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- AWJWCTOOIBYHON-UHFFFAOYSA-N furo[3,4-b]pyrazine-5,7-dione Chemical compound C1=CN=C2C(=O)OC(=O)C2=N1 AWJWCTOOIBYHON-UHFFFAOYSA-N 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
- C25D5/10—Electroplating with more than one layer of the same or of different metals
- C25D5/12—Electroplating with more than one layer of the same or of different metals at least one layer being of nickel or chromium
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
- C25D5/10—Electroplating with more than one layer of the same or of different metals
- C25D5/12—Electroplating with more than one layer of the same or of different metals at least one layer being of nickel or chromium
- C25D5/14—Electroplating with more than one layer of the same or of different metals at least one layer being of nickel or chromium two or more layers being of nickel or chromium, e.g. duplex or triplex layers
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
- C25D5/48—After-treatment of electroplated surfaces
- C25D5/50—After-treatment of electroplated surfaces by heat-treatment
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Electroplating Methods And Accessories (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Physical Vapour Deposition (AREA)
- Electroplating And Plating Baths Therefor (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
Abstract
UNE PIECE DE TITANE OU D'ALLIAGE AU TITANE EST MUNIE D'UNE COUCHE PROTECTRICE PAR LES ETAPES DE : A.METALLISER PAR GALVANISATION UNE COUCHE DE NICKEL OU COBALT SUR LA SURFACE DE LA PIECE,B.METALLISER PAR GALVANISATION UNE COUCHE DE CHROME SUR LA COUCHE DE NICKEL OU COBALT, ETC.TRAITER THERMIQUEMENT LA PIECE METALLISEE A UNE TEMPERATURE DE 700C SOUS VIDE. LA COUCHE RESULTANTE CONFERE A LA PIECE UNE BONNE RESISTANCE A L'OXYDATION ET A LA FORMATION DE PHASE ALPHA.A PART OF TITANIUM OR TITANIUM ALLOY IS PROVIDED WITH A PROTECTIVE LAYER BY THE STEPS OF: A. METALLIZING BY GALVANIZATION A NICKEL OR COBALT LAYER ON THE SURFACE OF THE PART, B. METALLIZING BY GALVANIZING A CHROME LAYER ON THE NICKEL OR COBALT LAYER, ETC. THERMALLY TREAT THE METALIZED PART AT A TEMPERATURE OF 700C UNDER VACUUM. THE RESULTING LAYER PROVIDES THE PART WITH GOOD RESISTANCE TO OXIDATION AND TO THE FORMATION OF THE ALPHA PHASE.
Description
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L'invention a pour objet des couches protectrices, et en particulier des couches protectrices pour le titanie et des alliages au titane Certaines pièces de rnoteurs à turbine à gaz. telles que les aubes de compresseur, sont fréquemment far.riquees en alliage au titane. De tels 5 alliages sont bien adaptes pour des pieces soumises, en fonctionnement, a des températures allant de températures bien Inférleures à OC Jusqu'à des températures d'environ 500'C. Cela signifie que les alliages peuvent être utilisés dans tous les étages d'un compresseur de moteur à turbine à gaz à flux axial, excepté dans les étages haute pression. 10 Cependant, d'autres alliages à base de fer ou de nickel doivent être utilisés dans les étages haute pression à cause des hautes températures qui sont susceptibles d'y régner. L'utilisation de tels alliages n'est pas souhaitable a cause du handicap de poids qu'ils présentent par rapport aux alliages au titane. Il existe cependant des alliages au titane à haute 15 résistance, disponibles actuellement, qui peuvent supporter des températures supérieures à 5(0'C.. Malheureusement, à ces températures, les alliages tendent a s'oxyder et à se calaminer en surface, de mrnme qu'à devenir sujets à une formation de phase alpha due The subject of the invention is protective layers, and in particular protective layers for titanium and titanium alloys. Certain parts of gas turbine engines. such as compressor blades, are frequently expensive in titanium alloy. Such alloys are well suited for parts subjected, in use, to temperatures ranging from temperatures well inert to OC up to temperatures of about 500 ° C. This means that the alloys can be used in all stages of an axial flow gas turbine engine compressor, except in the high pressure stages. However, other alloys based on iron or nickel must be used in the high pressure stages because of the high temperatures that are likely to prevail. The use of such alloys is undesirable because of the weight handicap they have compared to titanium alloys. However, there are currently available high strength titanium alloys which can withstand temperatures above 5 ° C. Unfortunately, at these temperatures, the alloys tend to oxidize and scale on the surface. even to become subject to an alpha phase formation due to
à l'absorption d'oxygène.to the absorption of oxygen.
C'est donc urYobjet de la présente invention que de prevoir une couche protectrice pour le titane et pour des alliages au titane qui rendent le titane ou les alliages au titane moins sujets au calaminage de surface et à la formation de phase alpha a des températures élevées que ceux qui ont été obtenus jusqu'alors. Selon la présente invention, un procédé pour revêtir un pièce faite de titane ou d'alliage au titane d'une couche protectrice comprend les It is therefore the object of the present invention to provide a protective layer for titanium and for titanium alloys which make titanium or titanium alloys less prone to surface scaling and alpha phase formation at elevated temperatures. than those that have been obtained until then. According to the present invention, a method for coating a piece made of titanium or titanium alloy with a protective layer comprises the
étapes de.steps of.
a) déposer une couche de nickel ou cobalt à la surface de la pièce 10o fait d'alliage au titane; b) déposer une couche de chrome sur ladite couche de base de nickel ou cobalt; et, c) traiter thermiquement la pièce de titane ou d'alliage au titane ainsi recouverte dans des conditions non oxydantes pour provoquer au 15 moins une interdiffusion entre lesdites couches de nickel ou cobalt et de chrome, et entre ladite couche de nickel ou cobalt et la surface de ladite a) depositing a layer of nickel or cobalt on the surface of the piece 10o made of titanium alloy; b) depositing a layer of chromium on said base layer of nickel or cobalt; and, c) heat treating the titanium or titanium alloy piece thus coated under non-oxidizing conditions to cause at least one interdiffusion between said nickel or cobalt and chromium layers, and between said nickel or cobalt layer and the surface of said
pièce de titane ou d'alliage au titane. piece of titanium or titanium alloy.
Les couches de nickel ou cobalt et de chrome peuvent être appliquées par toute méthode appropriée. Nous préférons les appliquer 20 par galvanoplastie, auquel cas il est necessaire de corroder la surface de la pièce en alliage au titane ou en titane avant d'effectuer la galvanoplastie. Le degré de corrosion nécessaire peut être obtenu par une corrosion anodique de la surface de la pièce dans un mélange d'acide acétique et d'acide fluorhydrique. D'autres procédés de dépôt des 25 couches de nickel ou cobalt et de chrome peuvent cependant être employés si on le souhaite. Ainsi, les couches peuvent être déposées par des techniques telles que le dépôt en phase gazeuse par procéde Nickel or cobalt and chromium layers may be applied by any suitable method. We prefer to apply them by electroplating, in which case it is necessary to corrode the surface of the titanium or titanium alloy part before electroplating. The degree of corrosion required can be achieved by anodic corrosion of the surface of the workpiece in a mixture of acetic acid and hydrofluoric acid. Other methods of depositing the nickel or cobalt and chromium layers can, however, be employed if desired. Thus, the layers can be deposited by techniques such as process gas deposition.
physique ou telles que le dépôt autocatalytique. physical or such as autocatalytic deposition.
Bien que l'étape de traitement thermique en vue de provoquer 30 l'interdiffusion puisse être effectuée dans toute atmosphère non oxydante et qui n'ait pas d'effet dommageable sur la pièce recouverte de Although the heat treatment step to cause interdiffusion can be carried out in any non-oxidizing atmosphere and which has no detrimental effect on the coated piece of
la couche protectrice, nous préférons effectuer cette étape sous vide. the protective layer, we prefer to perform this step under vacuum.
3 26010443 2601044
Pour démontrer l'efficacité de la présente invention, on a recouvert une pièce de test faite d'un alliage au titane suivant le procéde de la présente invention et on l'a soumise ensuite à des tests dans un environnement à haute température. Plus spécifiquement, une aiguille de 5 50 mm de long et de 7 mm de diamètre, faite d'un alliage disponible sur le marché sous la référence Ti53315, a d'abord été corrodée anodiquement dans un melange contenant 97,5 % en volume d'acide acétique et 12,5 % en volume d'acide fluorhydrique, avec un courant d'une Intensité de 1,8 A/m2 et à une température de 40-50'C pendant 10 une minute. L'alliage Ti5331S est produit par Imperial Metal Industries et contient, en poids: 5,5 % d'aluminium, 3,5 % d'étain, 3 % de zirconium To demonstrate the effectiveness of the present invention, a test piece made of a titanium alloy was coated according to the process of the present invention and then subjected to testing in a high temperature environment. More specifically, a needle 50 mm long and 7 mm in diameter, made of an alloy available on the market under the reference Ti53315, was first corroded anodically in a mixture containing 97.5% by volume. acetic acid and 12.5% by volume hydrofluoric acid, with a current of an Intensity of 1.8 A / m2 and a temperature of 40-50 ° C for one minute. The Ti5331S alloy is produced by Imperial Metal Industries and contains, by weight: 5.5% aluminum, 3.5% tin, 3% zirconium
et 1 % de niobium, le reste étant du titane. and 1% niobium, the remainder being titanium.
L'aiguille a été ensuite rincée avant d'être métallisee par galvanisation avec du nickel sur une épaisseur de 20-25 g La 15 galvanoplastie a effectuee dans un bain de Watts modifieé pendant une période de 20 minutes, a une température de 50C et avec un courant d'une intensité de 4, 5 A/m2. Apres un autre rinçage, l'aiguille a eété métallisée par galvanisation avec du chrome sur une épaisseur de 1-2 It La galvanoplastie a éte effectuée dans un bain contenant 375 20 grammes/litre d'acide chromique, et 2,5 grammes/litre d'acide sulfurique pendant une période de 5 minutes, à une température de 49'C et avec un courant d'une densité de 20,7 A/m2. L'aiguille munie de ses couches metallsees de nickel et de chrome a eté ensuite rincéee et séchée avant d'être chauffée à une température de 700'C pendant une 25 heure sous vide pour provoquer un certain degré d'lnterdiffusion des couches de nickel et de chrome, de même que pour garantir un certain degré d'interdiffuslon entre la couche de nickel et l'alliage au titane de l'aiguille en vue de produire une liaison interface effective entre The needle was then rinsed before being galvanized with nickel to a thickness of 20-25 g. The electroplating was performed in a modified Watts bath for a period of 20 minutes, at a temperature of 50.degree. a current of an intensity of 4.5 A / m2. After another rinse, the needle was metallized by galvanizing with chromium to a thickness of 1-2 It electroplating was carried out in a bath containing 375 20 grams / liter of chromic acid, and 2.5 grams / liter sulfuric acid for a period of 5 minutes, at a temperature of 49 ° C and with a current of a density of 20.7 A / m2. The needle with its metallised layers of nickel and chromium was then rinsed and dried before being heated at a temperature of 700 ° C for one hour under vacuum to cause some degree of diffusion of the nickel layers. of chromium, as well as to ensure a certain degree of interdiffuslon between the nickel layer and the titanium alloy of the needle in order to produce an effective interface connection between
l'aiguille et les couches.the needle and the layers.
L'aiguille a ensuite été chauffée dans l'air à une température de 650'C pendant une période de 1000() heures en vue d'estimer la qualite des couches appliquées soumises à de hautes températures pendant une longue période. On a-découvert, en sectionnant l'aiguille, qu'il ne s'était produit qu'une oxydation superficielle de la surface de l'aiguille d'alliage au titane et qu'il n'y avait pas de trace de formation de phase alpha. Bien que dans l'exemple décrit ci-dessus, la pièce de test ait été The needle was then heated in air at a temperature of 650 ° C for a period of 1000 () hours to estimate the quality of the applied layers subjected to high temperatures for a long time. It was discovered by cutting the needle that there was only superficial oxidation of the surface of the titanium alloy needle and that there was no evidence of alpha phase. Although in the example described above, the test piece has been
une aiguille faite d'un alliage au titane métallisé avec du nickel et du chrome, on comprendra que le procede selon la présente invention est applicable à la protection du titane ou d'autres alliages au titane et qu'une couche de cobalt pourrait être substituée à la couche de nickel si 10 on le souhaitait. a needle made of a titanium alloy metallized with nickel and chromium, it will be understood that the method according to the present invention is applicable to the protection of titanium or other titanium alloys and that a layer of cobalt could be substituted to the nickel layer if desired.
La présente invention offre donc un procédé intéressant pour protéger des effets de l'oxydation et de la formation de phase alpha des pièces de titane et d'alliages au titane qui sont soumises à des températures ambiantes élevées The present invention thus provides an interesting method for protecting the effects of oxidation and alpha phase formation of titanium and titanium alloys which are subjected to high ambient temperatures.
2 6 0 1 0 4 42 6 0 1 0 4 4
Claims (6)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8608926A GB2188942B (en) | 1986-04-11 | 1986-04-11 | Protective coating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2601044A1 true FR2601044A1 (en) | 1988-01-08 |
| FR2601044B1 FR2601044B1 (en) | 1991-08-23 |
Family
ID=10596077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR878703313A Expired - Fee Related FR2601044B1 (en) | 1986-04-11 | 1987-03-11 | METHOD FOR DEPOSITING A PROTECTIVE LAYER AND PART PROVIDED WITH SUCH A LAYER |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS62243757A (en) |
| DE (1) | DE3708869A1 (en) |
| FR (1) | FR2601044B1 (en) |
| GB (1) | GB2188942B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3032725A1 (en) * | 2015-02-12 | 2016-08-19 | Snecma | METHOD FOR DEPOSITING A COATING AGAINST EROSION ON A METAL PIECE |
| WO2017085400A1 (en) * | 2015-11-19 | 2017-05-26 | Safran Helicopter Engines | Aircraft engine part comprising an erosion protective coating and process for manufacturing such a part |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3716937C1 (en) * | 1987-05-20 | 1987-11-26 | Mtu Muenchen Gmbh | Process for the production of wear protection layers on surfaces of components made of titanium or titanium-based alloys |
| US4904352A (en) * | 1988-01-13 | 1990-02-27 | Microdot Inc. | Electrodeposited multilayer coating for titanium |
| CA2185818A1 (en) * | 1994-03-17 | 1995-09-21 | Karel Hajmrle | Low friction cobalt-based coatings for titanium |
| US5922478A (en) * | 1997-04-30 | 1999-07-13 | Masco Corporation | Article having a decorative and protective coating |
| DE19962641B4 (en) * | 1999-12-23 | 2012-04-19 | Erlus Aktiengesellschaft | Method for producing a microstructure on a metallic surface and microstructured metallic surface |
| US20070261965A1 (en) * | 2003-11-07 | 2007-11-15 | Jorg Heller | Coating of Substrates |
| US7726121B2 (en) | 2004-08-06 | 2010-06-01 | Yamaha Hatsudoki Kabushiki Kaisha | Engine part |
| ATE487813T1 (en) * | 2006-09-11 | 2010-11-15 | Inncoa Gmbh | METHOD FOR HARDENING GALVANIC CHROME LAYERS |
| JP2009074141A (en) * | 2007-09-21 | 2009-04-09 | Komatsu Ltd | Alloy plating layer forming method and structural component |
| DE102008019296A1 (en) * | 2008-04-16 | 2009-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Process for producing a fire protection for titanium component bodies of an aircraft gas turbine and titanium component body for an aircraft gas turbine |
| CN110512109B (en) * | 2019-09-20 | 2021-09-03 | 西安稀有金属材料研究院有限公司 | Preparation method of graphene reinforced titanium-based composite material |
| CN116555854B (en) * | 2023-04-12 | 2023-11-14 | 广州三孚新材料科技股份有限公司 | Golf club head and preparation method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2900715A (en) * | 1956-05-28 | 1959-08-25 | Steel Improvement & Forge Co | Protection of titanium |
| US2921888A (en) * | 1956-10-26 | 1960-01-19 | Vertol Aircraft Corp | Electroplating titanium ano titanium alloys |
| DE2118364A1 (en) * | 1970-04-20 | 1971-10-28 | Superior Plating Co | Process for hard chrome plating a titanium substrate |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3691029A (en) * | 1971-03-05 | 1972-09-12 | Superior Plating Co | Chrome plating of titanium |
| JPS5817838B2 (en) * | 1978-10-05 | 1983-04-09 | 上村工業株式会社 | Corrosion resistant plating method |
| US4284688A (en) * | 1978-12-21 | 1981-08-18 | Bbc Brown, Boveri & Company Limited | Multi-layer, high-temperature corrosion protection coating |
| DE3321231C2 (en) * | 1983-06-11 | 1985-10-31 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Process for the production of wear protection layers on the surfaces of components made of titanium or titanium-based alloys |
-
1986
- 1986-04-11 GB GB8608926A patent/GB2188942B/en not_active Expired - Fee Related
-
1987
- 1987-03-11 FR FR878703313A patent/FR2601044B1/en not_active Expired - Fee Related
- 1987-03-18 DE DE19873708869 patent/DE3708869A1/en not_active Withdrawn
- 1987-03-19 JP JP62065521A patent/JPS62243757A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2900715A (en) * | 1956-05-28 | 1959-08-25 | Steel Improvement & Forge Co | Protection of titanium |
| US2921888A (en) * | 1956-10-26 | 1960-01-19 | Vertol Aircraft Corp | Electroplating titanium ano titanium alloys |
| DE2118364A1 (en) * | 1970-04-20 | 1971-10-28 | Superior Plating Co | Process for hard chrome plating a titanium substrate |
Non-Patent Citations (1)
| Title |
|---|
| METAL FINISHING, vol. 77, no. 11, novembre 1979, page 24; I. RAJAGOPAL et al.: "Plating of reactive metals" * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3032725A1 (en) * | 2015-02-12 | 2016-08-19 | Snecma | METHOD FOR DEPOSITING A COATING AGAINST EROSION ON A METAL PIECE |
| WO2017085400A1 (en) * | 2015-11-19 | 2017-05-26 | Safran Helicopter Engines | Aircraft engine part comprising an erosion protective coating and process for manufacturing such a part |
| RU2718032C2 (en) * | 2015-11-19 | 2020-03-30 | Сафран Хеликоптер Энджинз | Aircraft engine part, comprising coating for erosion protection, and method of making such part |
| US10753006B2 (en) | 2015-11-19 | 2020-08-25 | Safran Helicopter Engines | Aircraft engine part including a coating for protection against erosion, and a method of fabricating such a part |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2188942A (en) | 1987-10-14 |
| JPS62243757A (en) | 1987-10-24 |
| GB2188942B (en) | 1990-04-04 |
| FR2601044B1 (en) | 1991-08-23 |
| DE3708869A1 (en) | 1987-10-22 |
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