EP1705261A1 - Method of depositing a wear-resistant coating by thermal spraying - Google Patents
Method of depositing a wear-resistant coating by thermal spraying Download PDFInfo
- Publication number
- EP1705261A1 EP1705261A1 EP06111543A EP06111543A EP1705261A1 EP 1705261 A1 EP1705261 A1 EP 1705261A1 EP 06111543 A EP06111543 A EP 06111543A EP 06111543 A EP06111543 A EP 06111543A EP 1705261 A1 EP1705261 A1 EP 1705261A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- coating
- alloy
- projection
- wear
- cuniin
- 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.)
- Withdrawn
Links
Images
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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/172—Copper alloys
- F05D2300/1723—Nickel-Copper alloy, e.g. Monel
Definitions
- the subject of the invention is a thermal spraying method for depositing an anti-wear coating on a mechanical part and, more particularly, a gas turbine engine part made of titanium or titanium alloy such as a fan blade or a fan blade. turbomachine compressor.
- Blower or compressor blades are a good example of parts subject to wear during turbine operation. These vanes are embedded by their feet in grooves of suitable shape, formed on the periphery of rotating disks, hereinafter referred to as compressor disks or blower.
- the blade roots move in said grooves under the effect of centrifugal force and vibrations.
- the shape of the blade roots is adjusted to that of the grooves to allow such relative movements.
- the observed wear is all the more important that the blade roots and the discs of the blower or the compressor are made of titanium or titanium alloy. Indeed, the coefficient of friction titanium / titanium is quite high.
- anti-wear coatings which are copper-nickel alloys (CuNi), copper-aluminum alloys (CuAI) or even copper-nickel-indium alloys (CuNiIn). It is generally preferred to use the latter type of alloy (CuNiIn) because it has better mechanical properties at high temperatures.
- Plasma projection To deposit these alloys on the blade roots, one usually uses a thermal projection method called plasma projection. This method can be implemented using a plasma gun such as that described in the application US 3,145,287 . Plasma spraying involves bringing alloy powder to a plasma torch producing a gas jet at a very high temperature: more than 2,000 ° C. The projection speed of the particles is, in turn, between 100 and 400 m / s.
- microstructure of the plasma spray deposited coating has a very high porosity and oxidation, which affect the mechanical properties of the coating.
- this coating adheres poorly on titanium or its alloys. So, in practice, there is a chipping rapid coating that poorly withstands the stresses to which it is subjected during the operation of the turbine.
- a second type of thermal spraying is also used to deposit anti-wear coatings: the HVOF type thermal spraying for "High Velocity Oxy Fuel", which consists of taking advantage of the combustion of oxygen and a combustible gas such as propane, propylene, hydrogen, or methylacetylene propadiene, to heat and propel grains of alloy powder melted at a very high speed.
- the temperatures reached with this process are between 1500 and 2000 ° C and the projection speeds between 300 and 700 m / s.
- An example of HVOF projection base nickel alloy deposition is described in the patent application US5,518,683 .
- the object of the invention is to propose a new deposition process making it possible to deposit anti-wear coatings which are more resistant to the stresses to which they are subjected than the coatings obtained by the existing processes.
- the subject of the invention is a process for depositing, by thermal spraying, an alloy of copper, nickel and indium, as an anti-wear coating, on a mechanical part, characterized in that said thermal spray coating type said AC-HVAF, for "Activated Combustion High Velocity Air Fuel".
- a coating of copper alloy, nickel and indium is deposited because this type of coating is mechanically very resistant to high temperatures.
- the thermal projection type called AC-HVAF is a known technique which has the main difference with the projection HVOF mentioned above, the use of a mixture of air and a combustible gas such as propane (instead of a mixture of oxygen and gas) that is burned to heat and propel an alloy powder at a very high speed.
- the projection speed of the fused alloy particles is substantially between 600 and 800 m / s and the temperatures reached vary between 800 and 1500 ° C.
- the temperatures reached during an AC-HVAF type projection are lower than those reached during a HVOF or plasma type projection. This limits the oxidation of the projected particles.
- the projection speeds that can be obtained with the AC-HVAF process are higher than the speeds obtained by plasma or HVOF projection.
- the time between the moment when the particles are projected and the one where they reach the part to be coated, during which the particles are particularly sensitive to oxidation is decreased. This again results in a reduction in the oxidation of the coating.
- the high kinetic energy of the particles projected onto the part to be coated allows, on the one hand, a better attachment of these particles on this part and, on the other hand, to obtain a more compact coating which has a porosity less than that obtained with the methods used until now.
- the structure of the coating obtained is unitary and non-lamellar.
- the reduction of the porosity and the quantity of oxide in the coating does not result in a concrete reduction of the number of potential failure initiators in the microstructure of the coating. This results in a better resistance to mechanical stresses and more particularly to compressive stresses to which the coating is subjected. Since, moreover, the coating is more compact and adheres better to the part which it covers, it is practically seen that the flaking problems occur less rapidly during operation of the gas turbine, and that the lifetime of the coating of the invention is much better than that of known coatings.
- thermal projection AC-HVAF is by nature a more economical method than the plasma projection.
- said coating is copper base alloy.
- said coating is copper base alloy comprising from 30% to 42% of nickel, by weight, and from 2% to 8% of indium, by mass.
- a copper base alloy comprising from 34% to 38% nickel by weight and from 4% to 6% indium by weight.
- CuNiIn coatings are interesting coatings because they are mechanically very resistant to high temperatures.
- the applicant company found that the melting temperatures of CuNiIn alloys were much lower than the temperatures reached during a plasma projection, and lower than those reached during a HVOF type projection. On the contrary, the temperatures reached during an AC-HVAF projection appear to be of the same order as the melting temperatures of CuNiIn alloys. Thus, it is found that using the AC-HVAF process, it is possible to melt a CuNiIn alloy avoiding unnecessary oxidation, linked to too high temperatures. The AC-HVAF process is therefore particularly suitable for depositing CuNiIn coatings.
- a layer of lubricating varnish comprising, for example, molybdenum disulphide (MoS 2 ) and an organic resin is deposited on the CuNiIn wear-resistant coating after it has been deposited.
- MoS 2 molybdenum disulphide
- the CuNiIn coatings have a high roughness and it is recommended to cover it with a layer of varnish with a low coefficient of friction, to promote sliding and limit wear.
- the CuNiIn coating and lubricant layer gives completely satisfactory results in terms of protection of the part and durability of the coating.
- a part cited herein is a titanium compressor or turbine engine fan blade
- the process of the invention can be used to coat any type of part, be it or not in titanium or in one of its alloys.
- the method can be used to coat at least one of two gas turbine parts, whatever they are, that may be in contact with each other.
- the graph of FIG. 1 represents on the abscissa the projection speeds in m / s and on the ordinate the projection temperatures in ° C. obtained with different thermal projection methods. On this graph are plotted temperature and velocity ranges, plasma, HVOF and AC-HVAF projections. Moreover, the range of melting temperatures of a CuNiIn alloy is shown.
- the thickness of the deposited coating was 165 microns but greater thicknesses could have been obtained without particular difficulty.
- the porosity of the coating measured was less than 1%.
- the micrograph of FIG. 2 was made on a CuNiIn coating deposited by AC-HVAF, in accordance with the invention, while the micrograph of FIG. 3 was carried out on a CuNiIn coating obtained by plasma spraying.
- the oxides and porosities appear as black spots among the coating layer 2 deposited on the substrate 1.
- FIG. 3 To simulate the mechanical stresses at which a fan blade is subjected in use, a device similar to that of FIG. 3 has been made in which a mechanical part 10 which replaces the blade is mounted at its foot 14 inside. a groove 15 defined between two uprights 16a and 16b held in position between two jaws 18. The assembly thus produced is similar to a dovetail assembly. The uprights 16a and 16b here replace the fan disk. The foot 14 of the part 10 has two surfaces 14a and 14b in contact with the uprights 16a and 16b. A cyclic traction force F was exerted on the part 10. The evolution of the force F as a function of time is represented in FIG.
Abstract
Description
L'invention a pour objet un procédé de dépôt par projection thermique d'un revêtement anti-usure sur une pièce mécanique et, plus particulièrement, une pièce de turbine à gaz réalisée en titane ou en alliage de titane comme une aube de soufflante ou de compresseur de turbomachine.The subject of the invention is a thermal spraying method for depositing an anti-wear coating on a mechanical part and, more particularly, a gas turbine engine part made of titanium or titanium alloy such as a fan blade or a fan blade. turbomachine compressor.
Les aubes de soufflante ou de compresseur sont un bon exemple de pièces sujettes à l'usure lors du fonctionnement de la turbine. Ces aubes sont encastrées par leur pied dans des rainures de forme adaptée, ménagées à la périphérie de disques mobiles en rotation, ci-après dénommés disques de compresseur ou de soufflante.Blower or compressor blades are a good example of parts subject to wear during turbine operation. These vanes are embedded by their feet in grooves of suitable shape, formed on the periphery of rotating disks, hereinafter referred to as compressor disks or blower.
Lors du fonctionnement du turboréacteur, les pieds d'aube se déplacent dans lesdites rainures sous l'effet de la force centrifuge et des vibrations. La forme des pieds d'aube est ajustée à celle des rainures pour permettre de tels déplacements relatifs. Les surfaces des pieds d'aube qui viennent en appui contre le bord desdites rainures, sous l'effet de la force centrifuge, subissent des contraintes de compression significatives (qui sont généralement cycliques). Ces contraintes combinées au mouvement vibratoire endommagent et usent lesdites surfaces. L'usure constatée est d'autant plus importante que les pieds d'aube et les disques de la soufflante ou du compresseur sont réalisés en titane ou en alliage de titane. En effet, le coefficient du frottement titane/titane est assez élevé.During operation of the turbojet engine, the blade roots move in said grooves under the effect of centrifugal force and vibrations. The shape of the blade roots is adjusted to that of the grooves to allow such relative movements. The surfaces of the blade roots which abut against the edge of said grooves, under the effect of the centrifugal force, undergo significant compressive stresses (which are generally cyclic). These constraints combined with the vibratory movement damage and wear said surfaces. The observed wear is all the more important that the blade roots and the discs of the blower or the compressor are made of titanium or titanium alloy. Indeed, the coefficient of friction titanium / titanium is quite high.
Pour protéger les pieds d'aube, il est connu d'utiliser des revêtements anti-usure qui sont des alliages cuivre nickel (CuNi), les alliages cuivre aluminium (CuAI) ou encore des alliages cuivre nickel indium (CuNiIn). On préfère généralement utiliser ce dernier type d'alliage (CuNiIn) car il présente de meilleures caractéristiques mécaniques à hautes températures.To protect the blade roots, it is known to use anti-wear coatings which are copper-nickel alloys (CuNi), copper-aluminum alloys (CuAI) or even copper-nickel-indium alloys (CuNiIn). It is generally preferred to use the latter type of alloy (CuNiIn) because it has better mechanical properties at high temperatures.
Pour déposer ces alliages sur les pieds d'aube, on utilise habituellement une méthode de projection thermique dite projection plasma. Cette méthode peut être mise en oeuvre à l'aide d'un pistolet à plasma tel que celui décrit dans la demande
La microstructure du revêtement déposé par projection plasma présente toutefois une porosité et une oxydation très élevées, qui affectent les propriétés mécaniques du revêtement. En outre, ce revêtement adhère mal sur le titane ou ses alliages. Ainsi, dans la pratique, on constate un écaillage rapide du revêtement qui supporte mal les contraintes auxquelles il est soumis lors du fonctionnement de la turbine.The microstructure of the plasma spray deposited coating, however, has a very high porosity and oxidation, which affect the mechanical properties of the coating. In addition, this coating adheres poorly on titanium or its alloys. So, in practice, there is a chipping rapid coating that poorly withstands the stresses to which it is subjected during the operation of the turbine.
On utilise également pour déposer des revêtements anti-usure, un second type de projection thermique : la projection thermique de type dit HVOF pour « High Velocity Oxy Fuel » qui consiste à mettre à profit la combustion d'oxygène et d'un gaz combustible tels que le propane, le propylène, l'hydrogène, ou le méthylacétylène propadiène, pour chauffer et propulser des grains de poudre d'alliage fondus à très grande vitesse. Les températures atteintes avec ce procédé sont comprises entre 1500 et 2 000°C et les vitesses de projection entre 300 et 700 m/s. Un exemple de dépôt d'alliage de base nickel réalisé par projection HVOF est décrit dans la demande de brevet
Bien que la durée de vie des dépôts obtenus avec un procédé HVOF est meilleure que celle des dépôts réalisés par projection plasma, on constate néanmoins un écaillage rapide du revêtement dans des conditions usuelles de fonctionnement de la turbomachine.Although the lifetime of the deposits obtained with a HVOF process is better than that of the deposits made by plasma spraying, there is nevertheless a rapid peeling of the coating under normal operating conditions of the turbomachine.
L'invention a pour but de proposer un nouveau procédé de dépôt permettant de déposer des revêtements anti-usure plus résistants aux contraintes auxquelles ils sont soumis, que les revêtements obtenus par les procédés existants.The object of the invention is to propose a new deposition process making it possible to deposit anti-wear coatings which are more resistant to the stresses to which they are subjected than the coatings obtained by the existing processes.
Pour atteindre ce but, l'invention a pour objet un procédé de dépôt par projection thermique d'un alliage de cuivre, de nickel et d'indium, en tant que revêtement anti-usure, sur une pièce mécanique, caractérisé en ce qu'on dépose ledit revêtement par projection thermique de type dit AC-HVAF, pour « Activated Combustion High Velocity Air Fuel ».To achieve this object, the subject of the invention is a process for depositing, by thermal spraying, an alloy of copper, nickel and indium, as an anti-wear coating, on a mechanical part, characterized in that said thermal spray coating type said AC-HVAF, for "Activated Combustion High Velocity Air Fuel".
On dépose un revêtement en alliage de cuivre, de nickel et d'indium car ce type de revêtement est mécaniquement très résistants à hautes températures.A coating of copper alloy, nickel and indium is deposited because this type of coating is mechanically very resistant to high temperatures.
La projection thermique de type dit AC-HVAF est une technique connue qui a pour principale différence avec la projection HVOF pré-citée, l'utilisation d'un mélange d'air et d'un gaz combustible comme le propane (au lieu d'un mélange d'oxygène et de gaz) que l'on brûle pour chauffer et propulser une poudre d'alliage à très grande vitesse. Avec la projection AC-HVAF, la vitesse de projection des particules d'alliage fusionnées est sensiblement comprise entre 600 et 800 m/s et les températures atteintes varient entre 800 et 1 500°C.The thermal projection type called AC-HVAF is a known technique which has the main difference with the projection HVOF mentioned above, the use of a mixture of air and a combustible gas such as propane (instead of a mixture of oxygen and gas) that is burned to heat and propel an alloy powder at a very high speed. With the projection AC-HVAF, the projection speed of the fused alloy particles is substantially between 600 and 800 m / s and the temperatures reached vary between 800 and 1500 ° C.
Les températures atteintes lors d'une projection de type AC-HVAF sont inférieures à celles atteintes lors d'une projection de type HVOF ou plasma. On limite ainsi l'oxydation des particules projetées.The temperatures reached during an AC-HVAF type projection are lower than those reached during a HVOF or plasma type projection. This limits the oxidation of the projected particles.
En outre, les vitesses de projection susceptibles d'être obtenues avec le procédé AC-HVAF sont supérieures aux vitesses obtenues par projection plasma ou HVOF. Ainsi, le laps de temps entre le moment où les particules sont projetées et celui où elles atteignent la pièce à revêtir, durant lequel les particules sont particulièrement sensibles à l'oxydation, est diminué. Il en résulte, là encore, une diminution de l'oxydation du revêtement.In addition, the projection speeds that can be obtained with the AC-HVAF process are higher than the speeds obtained by plasma or HVOF projection. Thus, the time between the moment when the particles are projected and the one where they reach the part to be coated, during which the particles are particularly sensitive to oxidation, is decreased. This again results in a reduction in the oxidation of the coating.
De plus, l'énergie cinétique élevée des particules projetées sur la pièce à revêtir permet, d'une part, un meilleur accrochage de ces particules sur cette pièce et, d'autre part, d'obtenir un revêtement plus compact qui présente une porosité inférieure à celle obtenue avec les procédés utilisés jusqu'à présent. En particulier, la structure du revêtement obtenu est unitaire et non lamellaire.In addition, the high kinetic energy of the particles projected onto the part to be coated allows, on the one hand, a better attachment of these particles on this part and, on the other hand, to obtain a more compact coating which has a porosity less than that obtained with the methods used until now. In particular, the structure of the coating obtained is unitary and non-lamellar.
La diminution de la porosité et de la quantité d'oxyde dans le revêtement se traduit concrètement pas une diminution du nombre d'amorces de ruptures potentielles dans la microstructure du revêtement. Il en résulte une meilleure résistance aux contraintes mécaniques et plus particulièrement aux contraintes en compression auxquelles le revêtement est soumis. Comme, en outre, le revêtement est plus compact et adhère mieux à la pièce qu'il revêt, on constate pratiquement que les problèmes d'écaillage interviennent moins rapidement lors du fonctionnement de la turbine à gaz, et que la durée de vie du revêtement de l'invention est bien meilleure que celle des revêtements connus.The reduction of the porosity and the quantity of oxide in the coating does not result in a concrete reduction of the number of potential failure initiators in the microstructure of the coating. This results in a better resistance to mechanical stresses and more particularly to compressive stresses to which the coating is subjected. Since, moreover, the coating is more compact and adheres better to the part which it covers, it is practically seen that the flaking problems occur less rapidly during operation of the gas turbine, and that the lifetime of the coating of the invention is much better than that of known coatings.
Enfin, la projection thermique AC-HVAF est par nature un procédé plus économique que la projection plasma.Finally, the thermal projection AC-HVAF is by nature a more economical method than the plasma projection.
Avantageusement, ledit revêtement est en alliage de base cuivre.Advantageously, said coating is copper base alloy.
Avantageusement encore, ledit revêtement est en alliage de base cuivre comprenant de 30% à 42% de nickel, en masse, et de 2% à 8% d'indium, en masse.Advantageously, said coating is copper base alloy comprising from 30% to 42% of nickel, by weight, and from 2% to 8% of indium, by mass.
Avantageusement encore, on peut utiliser pour ledit revêtement un alliage de base cuivre comprenant de 34% à 38% de nickel, en masse, et de 4% à 6% d'indium, en masse.Advantageously, it is possible to use for said coating a copper base alloy comprising from 34% to 38% nickel by weight and from 4% to 6% indium by weight.
Comme on l'a déjà souligné, les revêtements CuNiIn sont des revêtements intéressants car ils sont mécaniquement très résistants à hautes températures.As already pointed out, CuNiIn coatings are interesting coatings because they are mechanically very resistant to high temperatures.
Lors de ses recherches visant à améliorer la durée de vie des revêtements anti-usure de ce type, la société demanderesse a constaté que les températures de fusion des alliages CuNiIn étaient très inférieures aux températures atteintes lors d'une projection plasma, et inférieures à celles atteintes lors d'une projection de type HVOF. Au contraire, les températures atteintes lors d'une projection AC-HVAF se révèlent du même ordre que les températures de fusion des alliages CuNiIn. Ainsi, on constate qu'en utilisant le procédé AC-HVAF, il est possible de fondre un alliage CuNiIn en évitant toute oxydation inutile, liée à des températures trop élevées. Le procédé AC-HVAF se révèle donc particulièrement bien adapté au dépôt de revêtements CuNiIn.In its efforts to improve the service life of anti-wear coatings of this type, the applicant company found that the melting temperatures of CuNiIn alloys were much lower than the temperatures reached during a plasma projection, and lower than those reached during a HVOF type projection. On the contrary, the temperatures reached during an AC-HVAF projection appear to be of the same order as the melting temperatures of CuNiIn alloys. Thus, it is found that using the AC-HVAF process, it is possible to melt a CuNiIn alloy avoiding unnecessary oxidation, linked to too high temperatures. The AC-HVAF process is therefore particularly suitable for depositing CuNiIn coatings.
Avantageusement, on dépose sur le revêtement anti-usure CuNiIn, après son dépôt, une couche de vernis lubrifiant comprenant par exemple du disulfure de molybdène (MoS2) et une résine organique. En effet, les revêtements CuNiIn présentent une rugosité élevée et il est recommandé de le recouvrir d'une couche de vernis à faible coefficient de frottement, pour favoriser le glissement et limiter l'usure. L'ensemble revêtement CuNiIn et couche de lubrifiant, donne des résultats entièrement satisfaisants en terme de protection de la pièce et de durée de vie du revêtement.Advantageously, a layer of lubricating varnish comprising, for example, molybdenum disulphide (MoS 2 ) and an organic resin is deposited on the CuNiIn wear-resistant coating after it has been deposited. Indeed, the CuNiIn coatings have a high roughness and it is recommended to cover it with a layer of varnish with a low coefficient of friction, to promote sliding and limit wear. The CuNiIn coating and lubricant layer gives completely satisfactory results in terms of protection of the part and durability of the coating.
Bien que le seul exemple de pièce cité dans le présent mémoire soit une aube de compresseur ou de soufflante de turbomachine, en titane, il est clair que le procédé de l'invention peut être utilisé pour revêtir tout type de pièce, qu'elle soit ou non en titane ou en l'un de ses alliages. Par exemple, le procédé peut être utilisé pour revêtir au moins une pièce parmi deux pièces de turbine à gaz, quelles qu'elles soient, susceptibles d'être en contact l'une avec l'autre.Although the only example of a part cited herein is a titanium compressor or turbine engine fan blade, it is clear that the process of the invention can be used to coat any type of part, be it or not in titanium or in one of its alloys. For example, the method can be used to coat at least one of two gas turbine parts, whatever they are, that may be in contact with each other.
L'invention et ses avantages seront mieux compris à la lecture de la description détaillée qui suit, de modes de réalisation de l'invention, donnés à titre d'exemples non limitatifs. La description fait référence aux figures annexées sur lesquelles :
- la figure 1 est un graphique comparatif ;
- la figure 2 est une micrographie d'un revêtement CuNiIn déposé par projection AC-HVAF conformément au procédé de l'invention ;
- la figure 3 est une micrographie d'un revêtement CuNiIn déposé par projection plasma ;
- la figure 4 schématise un dispositif permettant de simuler les contraintes exercées sur un pied d'aube de soufflante en service ; et
- la figure 5 est un graphique représentant un cycle de variation de la force de traction exercée sur un pied d'aube de soufflante en service, en fonction du temps.
- Figure 1 is a comparative graph;
- FIG. 2 is a micrograph of an AC-HVAF sputtered CuNiIn coating according to the process of the invention;
- Figure 3 is a micrograph of a plasma sprayed CuNiIn coating;
- FIG. 4 schematizes a device making it possible to simulate the stresses exerted on a blade root of a fan in service; and
- Fig. 5 is a graph showing a cycle of variation of the pulling force exerted on a fan blade root in use as a function of time.
Le graphique de la figure 1 représente en abscisse les vitesses de projection en m/s et en ordonnée les températures de projection en °C obtenues avec différentes méthodes de projection thermique. Sur ce graphique, sont tracés des domaines de températures et de vitesses de projection, des projections plasma, HVOF et AC-HVAF. Par ailleurs, le domaine des températures de fusion d'un alliage CuNiIn, est représenté.The graph of FIG. 1 represents on the abscissa the projection speeds in m / s and on the ordinate the projection temperatures in ° C. obtained with different thermal projection methods. On this graph are plotted temperature and velocity ranges, plasma, HVOF and AC-HVAF projections. Moreover, the range of melting temperatures of a CuNiIn alloy is shown.
On constate sur ce diagramme que, conformément à ce qui a été précédemment décrit, les températures atteintes en projection AC-HVAF sont adaptées au domaine de fusion d'un alliage CuNiIn utilisé selon l'invention, et permettent de faire fondre cet alliage sans surchauffe inutile (surchauffe à éviter car elle favoriserait l'oxydation). Par ailleurs, on constate que de plus grandes vitesses de projection peuvent être obtenues par la projection AC-HVAF.It can be seen from this diagram that, according to what has been previously described, the temperatures attained in AC-HVAF projection are adapted to the melting range of a CuNiIn alloy used according to the invention, and make it possible to melt this alloy without overheating. unnecessary (overheating to avoid because it would promote oxidation). Furthermore, it can be seen that higher projection speeds can be obtained by the AC-HVAF projection.
Nous allons maintenant décrire un exemple de mise en oeuvre du procédé selon l'invention, selon lequel on a déposé un alliage CuNiIn sur une pièce en alliage de titane de type TA6V. Les conditions opératoires étaient les suivantes :
- Dispositif utilisé :
- torche AC-HVAF modèle SB-500 commercialisée par la société Uniquecoat Technologies.
- Poudre utilisée :
- Composition : alliage CuNiIn comprenant 36% en masse de Ni, 5% en masse de In, et un solde en Cu ;
- Taille des particules : 11 à 45 microns ;
- Chargement de la torche : 8kg/h ;
- Gaz transporteur : azote.
- Paramètres de fonctionnement de la torche :
- Gaz : propane ;
- Pression de l'air : 85 psi ;
Pression 1, propane : 74 psi- Pression 2 (0) de propane : 38 psi ;
- Pression du gaz transporteur : 41 psi ;
- Distance : 150 à 165 mm ;
- Taux de dépôt du revêtement : 45 microns par passage.
- Device used:
- AC-HVAF torch model SB-500 marketed by the company Uniquecoat Technologies.
- Powder used:
- Composition: CuNiIn alloy comprising 36% by weight of Ni, 5% by weight of In, and a balance of Cu;
- Particle size: 11 to 45 microns;
- Torch loading: 8kg / h;
- Carrier gas: nitrogen.
- Torch operating parameters:
- Propane gas ;
- Air pressure: 85 psi;
-
Pressure 1, propane: 74 psi - Propane pressure 2 (0): 38 psi;
- Carrier gas pressure: 41 psi;
- Distance: 150 to 165 mm;
- Coating Deposition Rate: 45 microns per pass.
Informations concernant la pièce revêtue :
- Préparation : sablage avec des particules d'oxyde d'aluminium de taille moyenne égale à 300 microns ;
- Température initiale : 29°C ;
- Variation de température : 50 à 95°C.
- Preparation: sandblasting with aluminum oxide particles of average size equal to 300 microns;
- Initial temperature: 29 ° C;
- Temperature variation: 50 to 95 ° C.
L'épaisseur du revêtement déposé était de 165 microns mais des épaisseurs supérieures auraient pu être obtenues sans difficulté particulière. La porosité du revêtement mesurée était quant à elle inférieure à 1%.The thickness of the deposited coating was 165 microns but greater thicknesses could have been obtained without particular difficulty. The porosity of the coating measured was less than 1%.
La micrographie de la figure 2 a été réalisée sur un revêtement CuNiIn déposé par AC-HVAF, conformément à l'invention, tandis que la micrographie de la figure 3 a été réalisée sur un revêtement CuNiIn obtenu par projection plasma.The micrograph of FIG. 2 was made on a CuNiIn coating deposited by AC-HVAF, in accordance with the invention, while the micrograph of FIG. 3 was carried out on a CuNiIn coating obtained by plasma spraying.
Les oxydes et les porosités apparaissent sous forme de tâches noires parmi la couche de revêtement 2 déposée sur le substrat 1.The oxides and porosities appear as black spots among the
Il apparaît clairement que la présence d'oxydes et de porosités est moindre dans le revêtement de la figure 2 que dans celui de la figure 3. Par ailleurs, on constate que le revêtement de la figure 2 présente une microstructure compacte et unitaire tandis que celle du revêtement de la figure 3 est lamellaire. Par conséquent le revêtement déposé avec le procédé de l'invention est moins sujet au délaminage (et donc à l'écaillage) que celui obtenu par projection plasma. Au final, la microstructure du revêtement de la figure 2 est mécaniquement plus résistante.It is clear that the presence of oxides and porosities is less in the coating of Figure 2 than in that of Figure 3. Furthermore, it is found that the coating of Figure 2 has a compact and unitary microstructure while that the coating of Figure 3 is lamellar. Consequently, the coating deposited with the process of the invention is less subject to delamination (and therefore to flaking) than that obtained by plasma spraying. In the end, the microstructure of the coating of FIG. 2 is mechanically more resistant.
Pour simuler les contraintes mécaniques auxquelles une aube de soufflante est soumise en service, on a réalisé un dispositif semblable à celui de la figure 3 dans lequel une pièce mécanique 10 qui remplace l'aube est montée au niveau de son pied 14 à l'intérieur d'une rainure 15 définie entre deux montants 16a et 16b maintenus en position entre deux mâchoires 18. L'assemblage ainsi réalisé est analogue à un assemblage à queue d'aronde. Les montants 16a et 16b remplacent ici le disque de soufflante. Le pied 14 de la pièce 10 présente deux surfaces 14a et 14b en contact avec les montants 16a et 16b. On a exercé une force de traction F cyclique sur la pièce 10. L'évolution de la force F en fonction du temps est représentée figure 5.To simulate the mechanical stresses at which a fan blade is subjected in use, a device similar to that of FIG. 3 has been made in which a
Le comportement d'un revêtement CuNiIn déposé par projection AC-HVAF selon l'invention a été testé pour 30 000 cycles de traction. Après 30 000 cycles, aucun écaillage et aucune usure n'ont été constatés. Avec un revêtement CuNiIn déposé par projection plasma, un écaillage apparaît entre 15 000 et 19 000 cycles.The behavior of an AC-HVAF sputtered CuNiIn coating according to the invention was tested for 30,000 tensile cycles. After 30,000 cycles, no flaking and no wear were observed. With a plasma sprayed CuNiIn coating, flaking appears between 15,000 and 19,000 cycles.
Ce test illustre l'amélioration significative en terme de durée de vie de revêtement, que l'invention permet d'obtenir.This test illustrates the significant improvement in terms of coating life, which the invention makes it possible to obtain.
Claims (8)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0502865A FR2883574B1 (en) | 2005-03-23 | 2005-03-23 | "THERMAL PROJECTION DEPOSITION METHOD OF ANTI-WEAR COATING" |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1705261A1 true EP1705261A1 (en) | 2006-09-27 |
Family
ID=34954892
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06111543A Withdrawn EP1705261A1 (en) | 2005-03-23 | 2006-03-22 | Method of depositing a wear-resistant coating by thermal spraying |
Country Status (6)
Country | Link |
---|---|
US (1) | US20060216429A1 (en) |
EP (1) | EP1705261A1 (en) |
JP (1) | JP2006266264A (en) |
CN (1) | CN1896312A (en) |
CA (1) | CA2540266A1 (en) |
FR (1) | FR2883574B1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2927997A1 (en) * | 2008-02-25 | 2009-08-28 | Snecma Sa | METHOD FOR TESTING A WAVE FOOT COATING |
FR2927998A1 (en) * | 2008-02-25 | 2009-08-28 | Snecma Sa | TESTING MACHINE FOR A WAVE FOOT COATING. |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4692462B2 (en) * | 2006-10-12 | 2011-06-01 | 株式会社Ihi | Sliding structure and film forming method |
DE202010018202U1 (en) * | 2010-02-18 | 2014-09-09 | Hydac Accessories Gmbh | Connecting device and use of a metallic material |
FR2978931B1 (en) | 2011-08-10 | 2014-05-09 | Snecma | METHOD FOR PRODUCING A PROTECTIVE REINFORCEMENT ON THE EDGE OF A BLADE |
US9689615B2 (en) * | 2012-08-21 | 2017-06-27 | Uop Llc | Steady state high temperature reactor |
US10029957B2 (en) * | 2012-08-21 | 2018-07-24 | Uop Llc | Methane conversion apparatus and process using a supersonic flow reactor |
US9707530B2 (en) * | 2012-08-21 | 2017-07-18 | Uop Llc | Methane conversion apparatus and process using a supersonic flow reactor |
US10160697B2 (en) * | 2012-08-21 | 2018-12-25 | Uop Llc | Methane conversion apparatus and process using a supersonic flow reactor |
US9656229B2 (en) * | 2012-08-21 | 2017-05-23 | Uop Llc | Methane conversion apparatus and process using a supersonic flow reactor |
US20160004744A1 (en) * | 2013-03-07 | 2016-01-07 | Brian Charles ERIKSSON | Top-k search using selected pairwise comparisons |
CN103276341B (en) * | 2013-05-08 | 2015-04-08 | 西安热工研究院有限公司 | Water turbine flow passage component wear-resistant coating spraying method |
CN104775052B (en) * | 2015-04-24 | 2016-11-30 | 吴丽清 | A kind of automobile water-based pump |
US10982310B2 (en) | 2018-04-09 | 2021-04-20 | ResOps, LLC | Corrosion resistant thermal spray alloy |
US11952916B2 (en) * | 2020-08-14 | 2024-04-09 | Rtx Corporation | Self-lubricating blade root/disk interface |
CN112267061A (en) * | 2020-10-13 | 2021-01-26 | 泗县金皖泵业有限公司 | Water pump impeller machining process for reducing hydraulic loss in water pump operation |
CN114703440B (en) * | 2022-04-02 | 2023-11-17 | 华东理工大学 | Nano oxide dispersion strengthening high-entropy alloy bonding layer and preparation method and application thereof |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3145287A (en) | 1961-07-14 | 1964-08-18 | Metco Inc | Plasma flame generator and spray gun |
US5271965A (en) * | 1991-01-16 | 1993-12-21 | Browning James A | Thermal spray method utilizing in-transit powder particle temperatures below their melting point |
EP0678590A1 (en) * | 1991-09-16 | 1995-10-25 | United Technologies Corporation | Anti-fretting coating |
US5518683A (en) | 1995-02-10 | 1996-05-21 | General Electric Company | High temperature anti-fretting wear coating combination |
US5601933A (en) * | 1994-03-17 | 1997-02-11 | Sherritt Inc. | Low friction cobalt based coatings for titanium alloys |
WO1997036692A1 (en) * | 1996-03-29 | 1997-10-09 | Metalspray, U.S.A., Inc. | Thermal spray systems |
US6245390B1 (en) * | 1999-09-10 | 2001-06-12 | Viatcheslav Baranovski | High-velocity thermal spray apparatus and method of forming materials |
US20010026845A1 (en) * | 1997-08-11 | 2001-10-04 | Drexel University | Method of applying corrosion, oxidation and/or wear-resistant coatings |
WO2003073804A2 (en) * | 2002-02-28 | 2003-09-04 | Snecma Services | Thermal spraying instrument |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3793195A (en) * | 1972-10-10 | 1974-02-19 | Gen Electric | Coated bearing surfaces |
US7141110B2 (en) * | 2003-11-21 | 2006-11-28 | General Electric Company | Erosion resistant coatings and methods thereof |
-
2005
- 2005-03-23 FR FR0502865A patent/FR2883574B1/en active Active
-
2006
- 2006-03-21 CA CA002540266A patent/CA2540266A1/en not_active Abandoned
- 2006-03-22 JP JP2006078590A patent/JP2006266264A/en not_active Withdrawn
- 2006-03-22 US US11/385,734 patent/US20060216429A1/en not_active Abandoned
- 2006-03-22 EP EP06111543A patent/EP1705261A1/en not_active Withdrawn
- 2006-03-23 CN CN200610065915.6A patent/CN1896312A/en active Pending
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3145287A (en) | 1961-07-14 | 1964-08-18 | Metco Inc | Plasma flame generator and spray gun |
US5271965A (en) * | 1991-01-16 | 1993-12-21 | Browning James A | Thermal spray method utilizing in-transit powder particle temperatures below their melting point |
EP0678590A1 (en) * | 1991-09-16 | 1995-10-25 | United Technologies Corporation | Anti-fretting coating |
US5601933A (en) * | 1994-03-17 | 1997-02-11 | Sherritt Inc. | Low friction cobalt based coatings for titanium alloys |
US5518683A (en) | 1995-02-10 | 1996-05-21 | General Electric Company | High temperature anti-fretting wear coating combination |
WO1997036692A1 (en) * | 1996-03-29 | 1997-10-09 | Metalspray, U.S.A., Inc. | Thermal spray systems |
US20010026845A1 (en) * | 1997-08-11 | 2001-10-04 | Drexel University | Method of applying corrosion, oxidation and/or wear-resistant coatings |
US6245390B1 (en) * | 1999-09-10 | 2001-06-12 | Viatcheslav Baranovski | High-velocity thermal spray apparatus and method of forming materials |
WO2003073804A2 (en) * | 2002-02-28 | 2003-09-04 | Snecma Services | Thermal spraying instrument |
Non-Patent Citations (2)
Title |
---|
FRIDRICI V ET AL: "Fretting wear behavior of a Cu-Ni-In plasma coating", SURFACE & COATINGS TECHNOLOGY ELSEVIER SWITZERLAND, vol. 163-164, 30 January 2003 (2003-01-30), pages 429 - 434, XP002340202, ISSN: 0257-8972 * |
WIELAGE B: "Abschlussbericht zum Forschungsvorhaben Herstellung SiC-haltiger Verbundschichten für hochbeanspruchte Bauteile und Werkzeuge mittels des HVOF-Verfahrens", 24 May 2001, LEHRSTUHL FÜR VERBUNDWERKSTOFFE, FAKULTÄT FÜR MASCHINENBAU UND VERFAHRENSTECHNIK, TECHNISCHE UNIVERSITÄT CHEMNITZ (DE), XP002389046 * |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2927997A1 (en) * | 2008-02-25 | 2009-08-28 | Snecma Sa | METHOD FOR TESTING A WAVE FOOT COATING |
FR2927998A1 (en) * | 2008-02-25 | 2009-08-28 | Snecma Sa | TESTING MACHINE FOR A WAVE FOOT COATING. |
WO2009112756A1 (en) * | 2008-02-25 | 2009-09-17 | Snecma | Method for testing the coating of a vane base |
WO2009112757A1 (en) * | 2008-02-25 | 2009-09-17 | Snecma | Device for testing the coating of a vane base |
US8387467B2 (en) | 2008-02-25 | 2013-03-05 | Snecma | Method for testing the coating of a vane base |
US8408068B2 (en) | 2008-02-25 | 2013-04-02 | Snecma | Device for testing the coating of a vane base |
RU2489702C2 (en) * | 2008-02-25 | 2013-08-10 | Снекма | Blade coating test setup |
RU2498265C2 (en) * | 2008-02-25 | 2013-11-10 | Снекма | Blade root coating test method |
Also Published As
Publication number | Publication date |
---|---|
JP2006266264A (en) | 2006-10-05 |
CA2540266A1 (en) | 2006-09-23 |
FR2883574A1 (en) | 2006-09-29 |
CN1896312A (en) | 2007-01-17 |
FR2883574B1 (en) | 2008-01-18 |
US20060216429A1 (en) | 2006-09-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1705261A1 (en) | Method of depositing a wear-resistant coating by thermal spraying | |
CA2844240C (en) | Method for producing a protective reinforcement of the leading edge of a vane | |
CA2196744C (en) | Thermal barrier coating with improved underlayer and pieces coated with said thermal barrier | |
FR2531491A1 (en) | ABRASIVE / ABRASIVE JOINT SYSTEM FOR ROTATING MACHINE | |
EP2917502B1 (en) | Rotor-stator assembly for a gas turgine engine | |
US6751863B2 (en) | Method for providing a rotating structure having a wire-arc-sprayed aluminum bronze protective coating thereon | |
CH634356A5 (en) | METAL PART HAVING A HARD COATING BASED ON CARBIDE. | |
EP1645724A2 (en) | Method of protection of contact surfaces between two metallic pieces | |
EP3017084A1 (en) | Process for preparing for removal a metal coating by thermal spraying on a substrate | |
CA2754263A1 (en) | Gas turbine blade and method of protecting same | |
FR2817921A1 (en) | Glide element for use in a compressor operating mechanism is made of at least one metal material and is provided on its plane surfaces with a plastic coating minimizing abrasion | |
EP1291494B1 (en) | Method for producing labyrinth seal tongues for movable parts in turbines | |
WO2011001117A1 (en) | Heat-protective coating for a turbine engine part, and method for producing same | |
FR2848575A1 (en) | POWDER MATERIAL FOR ABRADABLE SEAL | |
WO2014013190A1 (en) | Corrosion‑resistant abradable coating and method of manufacturing same | |
EP1600525B1 (en) | Process for making or repairing a coating on a metallic substrate | |
FR2979664A1 (en) | Annular part for stator of e.g. high-pressure turbine of turboshaft engine of aircraft, has porous abradable material coating covered with additional layer of non-porous refractory material, where additional layer includes lower thickness | |
EP2591138A1 (en) | Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns | |
EP4018009A1 (en) | Method for manufacturing an abradable sealing element, and abradable sealing element | |
FR3135487A1 (en) | BLADE FOR A TURBOMACHINE INCLUDING ANTI-WEAR PROTECTION | |
EP3963183A1 (en) | Method for coating an aircraft turbomachine component | |
FR2966167A1 (en) | METHOD FOR DEPOSITING OXIDATION PROTECTION COATING AND HOT CORROSION ON A SUPERALLIATION SUBSTRATE, COATING OBTAINED |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20060322 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20070328 |