Protective coating

 

(57) Abstract:

A method of producing a coating on a substrate includes pre-plating, chrome plating or siliconefree substrate and subsequent electrolysis or betalactamase coating by deposition of the metal matrix M1from baths containing particles rAlM2for codeposition of particles with the matrix, where M1at least one element selected from the group consisting of Ni, Co and Fe, and M2at least one element selected from the group consisting of Y, Si, Ti, HF, TA, Nb, MT, PT and rare earth elements. The method provides for additional heat treatment before or after deposition of M1rl2. In the preferred embodiment, may Latinoamericana substrate. The technical result is to increase the resistance to oxidation and thermal fatigue. 9 C.p. f-crystals, 4 Il.

The present invention relates to the provision of protective coatings on substrates. Such coatings are applied to constituent elements that are exposed to high temperature environments, in particular, where especially likely are corrosion and/or erosion. The main, but not required unities is osobennosti on constituent elements, made of a superalloy, for example, the shafts of a gas turbine, rims, discs, constituting the elements of the combustion chamber, the blades of the stator and the blades of the turbine runner and the guide vanes. The invention also relates to such details and to equipment and vehicles or fixed installations, including such details.

For a long time believed that the constituent elements of the gas turbine, in particular their internal elements in the vicinity of the combustion chamber and downstream, must have high strength and corrosion resistance at high temperature.

It is known that to ensure sufficient limit at high temperatures are elements made of heavy-duty material having a structure capable of withstanding the load. Typical used superalloy, depending on the requirements for specific uses are super alloys based on Ni, Co and Fe (examples are such alloys, which are known under factory marks IN100, IN718, IN738, MAR-M002, MAR-M247, CMSX-4, PWA 1480 and RWA 1484). Super alloys based on Fe and Co often represent uprochnennykh Cr, Co, Fe, Mo, W or Ta, and are often reinforced solid solution or precipitation hardening alloy. Precipitation hardening alloys based on Ni is widely used for the constituent elements of the gas turbine, and they often have to obtain the second phase precipitated in the respective heat treatment, Al, Ti or Nb. Examples of the dispersion-hardened superalloys based on Ni, used for the constituent elements of the gas turbine are such that known under factory marks INCO713, B-1900, IN100, MAR-M200 and MAR-M247. Examples of superalloys based on Co are MAR-M509 and Haynes188, and examples of superalloys based on Fe are Incoloy 802 and Incoloy 903. Elements of a gas turbine made of superalloys, are sometimes subjected to the pressure treatment or casting, and emergency operating conditions can be directly solidified or may exist in the form of a monocrystalline structure.

As the heavy-duty alloy are generally unable to withstand corrosive oxidizing atmosphere during maintenance, in practice it is customary to cover the elements made from high-alloy, corrosion-resistant material.

When servicing is formed designed to protect material surface layer of Al2O3that is, due to thermal expansion and contraction, is prone to flaking. It gradually recover through the diffusion of Al from the outside, and in the end, when no more Al in a quantity sufficient to replace the debonded material at a specific site, an element made of heavy-duty alloy will be subject to rapid corrosion. Chromium and silicon, together or singly, and separately or in addition to aluminum, can also diffuse into heavy-duty alloy forming the surface layer, including chromide or silicides. Although will continue to be a reference, mainly, to the plating, it should be understood that such a reference should be interpreted as alternative related mutatismutandis to the plating and/or sililirovanie.

Another practical application is the coating of heavy-duty alloy deposited layer, for example, MCrAlY, MCrAlHf, MCrAlYHf, MCrAlYHfSi the/SUB>O3from the surface and thus increases the service life of a constituent element. These deposited materials can be applied by plasma spraying; or by coprecipitation process, for example a process that we have described in our patent GB-B-2167446. Usually taken to cover an element of these materials so as to obtain a layer thickness of from 75 to 200 microns or more. The coating processes are costly and components having a coating thickness specified order, have a service life sufficient to justify such costs. However, when the load on the components continue to increase, it becomes increasingly undesirable to cover elements such as the impeller blades, deconstructionism materials.

Another problem with coatings having a layer thickness of this procedure lies in the fact that they are in the terms of service, becoming gradually more and more extreme in most modern gas turbines subject to thermo-mechanical fatigue cracking, and this is highly undesirable, particularly if the coating is applied on the thin-walled hollow element, such is ne USA N A-4933239 described plasma sputtering of the deposited layer of 25.4 μm CoCrAlYSiHf on heavy-duty alloy Ni. After plasma spraying the coating has been subjected steklotarnoj processing, aluminiowa sealing grout mixture and, ultimately, carried out stage of diffusion and precipitation during heat treatment. In the description of the patent States that the preferred method of applying CoCrAlYSiHf coating is plasma spraying, but in the description there is also a General conclusion that the deposited coating can be applied, for example, by plasma spraying, electron beam emission, deposition, electrolytic coating, spray, or by coating of pulp.

I believe that one of the reasons the operation is blasting in the previous field is that MCrAlY in the state after deposition is not sufficiently smooth.

In addition, when elyuminirovanie significantly changed the morphology of the deposited layer, and the aluminum is prone to completely diffuse through the deposited layer in a substrate of a heavy-duty alloy.

Another problem is the difficulty of ensuring that the key elements of Y, Si, and Hf, originally present in the deposited layer were secured relative activities in the e aimed at resolving the problems of the prior art.

In accordance with the first aspect of the present invention is provided a method of producing a coating on a substrate, which includes a plating, chrome plating or siliconefree substrate and the deposition on the treated substrate by electrolytic or bezelektrodnogo deposition of the metal matrix M1from baths containing particles CrAlM2to Coosada particles with the matrix, with M1is Ni or Co, or Fe, or two, or all of these elements, and M2is Y, Si, Ti, Hf, Ta, Nb, Mn, Pt, rare earth element, or two or more of these elements.

One of the advantages of the present invention is that it does not include as essential features of the method of coating the stage shot peening. Another advantage is that key elements such as Y, Si, and Hf, can be located close to the outer surface of the final product. Another advantage is that M1CrAlM2should not be subject to additional elyuminirovanie, and in the final product is achieved significantly better morphology.

The substrate can be aluminiowe in accordance with one of the many different processes is adenia from the vapor phase or the plating flame spraying, the spraying or electrodeposition. The substrate preferably aluminium way compacted plating. Chrome plating or siliconefree can be similarly performed using the above equivalent processes.

In a preferred embodiment, the substrate is subjected to Latinoamericano. It may include the deposition of the platinum layer, for example by deposition before or after plating. Deposited platinum layer may have a thickness of about 5 or about 10 microns. Instead together with platinum or platinum can be used palladium or ruthenium.

Before deposition of M1CrAlM2in the coating process can include a heat treatment. In a particularly preferred embodiment, regardless of whether include or not cooked before coprecipitation M1CrAlM2after coprecipitation M1CrAlM2carry out a heat treatment to cause the desired degree of homogenization and diffusion between the coating obtained by elyuminirovanie, and M1CrAlM2the coating. The plating is a preferred sealing the plating at approximately 900oC for about 6 hours the fusion processing at ~ 1100oC for about 1 hour in vacuum, and then the coating is subjected to hardening during aging at ~ 870oC for approximately 16 hours in a vacuum. Alternative or in addition an element after deposition of M1CrAlM2on the layer obtained after plating, may be subjected to heat treatment at ~ 1100oC for about 1 hour in vacuum.

We found that the layer M1CrAlM2provides a particularly suitable material for the subsequent deposition of a layer of thermal insulation material, for example zirconium dioxide, which can be stabilised (for example, lime or oxide of yttrium).

Heat-shielding material may be applied in the form colonializing material. Thermal barrier layer preferably has a thickness of more than 25 μm and may have a thickness of between 100 and 250 microns.

thermal barrier layer is applied preferably by coating by deposition from the vapor using electron beams or plasma spraying in the air.

In this invention, during the deposition of M1CrAlM2mm preferred current density is less than 5, more preferably less than 3 and most preferably less than h the mA/cm2, can serve as an example a current density of about 1 mA/cm2.

At relatively low current densities used in this invention, we have noticed a tendency that the structure of the particles on the floor in a state after deposition differs from the structure of particles in the bath, while preferably includes particles of smaller size (for example, when applying the powder with a particle size of <15 μm particle size >10 μm is not deposited preferably so how is preferably deposited particle size <10 μm). This is particularly surprising since according to theory, based on Faraday's law and the Stokes equation (see Transactions of the Institure of Metal Finishing, the title of the article: "The Production of Multi-Component Alloy Costings by Particle Co-Deposition", J. Foster et al., pp. 115-119, vol. 63, No. 3-4, 1985), by adoption of appropriate current density and stirring, the larger the particle size, the smaller the volume of the tub needed to achieve a specified fraction of the powder included in the coverage in the state after deposition. Therefore, it can be expected that there will be preferable to precipitate particles of larger size, but we found that at relatively low current densities is reversed.

One option M1clytie attended Ni, a thin layer of Ni may be caused to or on the upper surface of soosazhdenie material or directly on the aluminum floor before the stage coprecipitation. The layer of Nickel may have a thickness of about 2 microns.

Preferably, the metal matrix material and soosazhdenie particles form a layer of thickness less than 50 μm, or more preferably a thickness of less than 25 microns. In a particularly preferred embodiment, the layer may be a thickness of about 15 μm. However, the layer may have a thickness of less than 15 μm, about 12 μm, or 10 μm or less than these values. For most applications it is preferable that the layer had a thickness of 5 μm or more; more preferably it has a thickness of 10 μm or more. However, for some applications, the layer may have a thickness of more than 15 μm.

The deposition preferably takes place when loading baths less than 40 g of particles per liter. Preferably use a boot bath of about 30 g/l or less than 30 g/l more preferably use the volume of the tub about 20 g/l or less than 20 g/L. In a particularly preferred embodiment, use the volume of the tub about 10 g/l, but can be considered a lower load, for example about 1 g/L. This is"ptx2">

The particles can be spherical and can be formed when using a sprayer, such as a nozzle. Preferably, the particles in the bath consisted of a powder with a particle size of < 15 μm < 12 μm or < 10 μm.

According to one preferred variant of the granulometric composition in the bath consists of 25% of particles of size between 15 and 13 μm, 45% of particles with a size between 12 and 10 μm and 30% of particles less than 10 microns. Surprisingly and unexpectedly, we have found that the coating at relatively low current densities leads to preferential deposition of small particles; when in the bath use powder with this distribution by size, you get the following granulometric composition of the coating in the ratio after deposition of M1CrAlM2(as weight percent of the powder quantity in the electrolytic coating): 45% of particles < 10 μm, 55% of particles with size between 10 and 12 microns, and 0% between 12 and 15 microns.

Superior coverage achievable using methods that include purification step and, preferably, purification stage includes the stage of deposition.

In a particularly preferred embodiment, the precipitated layer of protective material M1CrAlM2that includes t; 15 μm, thanks purification, if desired, can be applied essentially continuous monolayer of particles with a size 12 or 10 μm (largest particle size in the state after deposition, respectively 12 or 10 μm). In another preferred method, wanting to provide a double layer or a triple layer having essentially a thickness of 10, 12, 15, or 20 μm, you can use the powder size from 4 to 8 μm.

Thus, we need only a relatively small or a small number of M1CrAlM2to ensure the presence of useful elements, such as Y, Si or Hf, which helps to prevent delamination of the Al2O3. This is particularly desirable for the constituent elements of gas turbines such as blades of the impeller turbines, since the total thickness and therefore the weight of the coating materials on the substrate (for example, the blade of the impeller) can be reduced without reducing the degree of corrosion protection. Therefore, the blade of the impeller becomes more durable and able to withstand torque or drag forces, resulting in improved performance of the gas turbine.

Aluminides layer may initially have a thickness of from 30 the t 10 to 50 μm, aluminides layer will have an inner diffusion zone with low Al concentration and a thickness of from 10 to 20 μm and an edge area (surface layer) with a higher concentration of Al and a thickness of from 20 to 40 μm. The thickness of layer M1CrAlM2heat treatment essentially no effect. The ratio of the thickness aluminide layer to the thickness of layer M1CrAlM2is preferably between 4:1 (for example, when the total thickness 50 μm) and 1: 1 (for example, when the total thickness of 110 μm). When include thermal barrier layer, the total thickness of the layer is increased; this layer may have a thickness in the range from 100 to 250 μm.

In another embodiment, the substrate, on which is applied aluminiowe material, includes heavy-duty alloy, which gives an element of the gas turbine.

The substrate includes any substrate, washed gas presents the components of the gas turbine, for example the profile of the wing, tail section blades of a gas turbine or outer rim blades of the gas turbine.

After coprecipitation aoademy material may consist of more than 40% (by volume) of particles, and in some applications, the specified content may exceed 45%.

Choi is an inert gas, usually up in one area and usually down in the second zone, while the substrate during coprecipitation feature in the second zone. The substrate (or an element of which forms a part) can rotate around an axis which is horizontal or has a horizontal element during coprecipitation. Can be used a device for deposition, which is described in our patent GB-B-2182055.

In some circumstances it may be desirable to rotate the substrate around the first axis having a horizontal component element, and around a second axis which is directed first. The cycle of rotation around the first axis may include periods of high angular velocity and periods of reduced angular velocity. The second axis may be perpendicular to the first axis and/or may intersect the first axis. The cycle of rotation around the first axis can alternately stop and resume. When the substrate is rotated around one axis only, with horizontal cutting element, the cycle of rotation may include periods of high angular velocity and periods of low angular velocity, and the rotation can alternately stop and resume. Manipulation of the substrate can profcom of the present invention is provided a method of manufacturing or repair a constituent element of the gas turbine, which includes coating the substrate constituent element in accordance with the first aspect of the invention.

In accordance with a third aspect of the present invention is provided with an element of a gas turbine or a gas turbine, comprising an element made or repaired in accordance with the second aspect of the invention.

In accordance with the fourth aspect of the present invention provided on the vehicle or stationary installation including the gas turbine in accordance with a third aspect of the invention. The vehicle according to this aspect of the invention may include, for example, aircraft or vehicle for the transportation by water or land.

The invention can be implemented in various ways, and one way of coating will be described by example with reference to the accompanying schematic drawings, in which:

Fig. 1 is a perspective view of the device for coating;

Fig. 2 is a view of the device on the side;

Fig. 3 is a view of the device front; and

Fig. 4 represents a perspective view of the clamping device, in which pocut protective material way, which includes deposition on them two or three layers of material. First, the blade is subjected to the surface elyuminirovanie and then apply the coating when using the device for the implementation of co-precipitation, shown in Fig.

As an optional third stage then put a layer of thermal insulation material.

The device shown in Fig., includes a vessel or container 1 having the upper part 2 in the form of a parallelepiped and a downward conical bottom part 3 in the form of an inverted pyramid, which is beveled to one side face 4 was a continuation of one side face 5 of the upper part.

The vessel 1 contains a partition 6, which lies in a vertical plane parallel to the side edges 4 and 5 of the vessel, and carries out communication in the side edges 7 and 8 with adjacent vertical and inclined surfaces of the vessel. Thus, the partition divides the vessel on a large working area 9 and a lower zone of return 11. In its bottom wall 6 ends by a horizontal edge 12 above the bottom of the vessel to obtain the relationship 13 between the working area 9 and area 12 return. The upper part of the partition wall 6 ends horizontal Croix air 15, which is attached to an air pump (not shown). In the working area 9 installed clamping device 21, which is fixed to the workpiece, causing the floor, while the clamping device 21 is installed so that the workpiece in the vessel can be moved in a manner described in more detail below.

When the device is used for applying electrolytic coating, for application of voltage to the workpiece installed in the mounting bracket 21, relative to the anode, which is summed up in the work area, provided with current conductors.

When this device is used for co-precipitation of the coating on the treated parts of the workpiece installed in the mounting bracket 21, which is located in the vessel as shown in Fig. Before or after the location of the fixture in the vessel is filled up to level 17 above the top edge 14 of the partition 6 with a solution for a coating containing particles that need Coosada. In the hole for air intake 15 serves the air, and it rises up in the area of return of 11, taking the solution and particles. In the upper part of the zone return wasurerareta, and flowing down past the workpiece located in the mounting bracket 21. In the lower part of the working area 9 of the particles have a tendency to sedimentation and slide down the inclined sides of the vessel in the direction of the relationship 13, where again they are caught in the solution and circulate again.

When the particles are moving down in the working area 9, collide with the workpiece, they have a tendency to deposition on the workpiece, where they begin to penetrate into the metal, which is simultaneously applied electric floor.

As shown in Fig. 4 and as described in the patent GB-B-2254338 covered the workpiece is set in the clamping device 251, which hung in the vessel 1. Clamping device of Fig. 2 and 3 is shown in a simplified form, but not included in Fig. 1 for reasons of clarity. Clamping device 21 includes a deck 22, which is installed on the top of the vessel 1, a reliable support 23 in the direction of one end and a pair of guide devices 24 at the other end. The guide devices 24 have the facial guides, which moves the slider 25, which carries the upright support 26, which passes up through a hole 27 in the deck 22 and engages with derivada in the movement of the vertical shaft 32, bearing bevel gear 33 which engages with the wheel 34 mounted on one end of the spindle 35 is mounted in the support 23. The other end of the spindle 35 is attached by means of a universal connection 36 to one end of the shaft 37, the other end of which moves through the spherical bearing 38 in the slide 25.

The shaft 37 carries many sharp protrusions, which are rigidly attached thereto, Fig. 4 shows only one sharp protrusion 39. The protrusion 39 is held in a plane containing the axis of the shaft 37, while the longitudinal axis of acute projection makes with the axis of the shaft 37 the corner . On the ledge 39 is installed and located at intervals along the entire line three blades of the gas turbine 42, which are coated, while the vertical axis blades extend in said plane and perpendicular to the longitudinal axis of the protrusion 39, whereupon the longitudinal axis of the blades make with the axis of the shaft 37 angles (90 - )o.

On deck 22 has an electronic control motor 43, which is connected by lines 44 and 45 to the motors 29 and 31. The controller 43 is designed to control the motor 31 in one direction only, but with a stop so that the shaft 37 is rotated around the horizontal axis (x-axis). Regi to rotate the reciprocating slide 25, and, thus, to impose on the rotation around the x-axis of oscillatory rotation around a rotational axis in the universal connection 36 (y-axis).

The angle and the parameters of the cycles performed by the motors 29 and 31, is chosen so that they match the workpiece, which is applied to the coating, to ensure that all surfaces are coated, sufficient time was faceup to obtain adequate load descending particles, which are included in covered metal, when they are deposited. One specific example of the coating and its production method will be described by way of example.

Example.

The coating was obtained on the blade of the gas turbine 42, having a wing profile 43, with the tail section 44 at one end and an outer rim 45 at the other end, at this site the tail section and the outer rim stretched at angles of approximately 70oto the axis of the cross section of the wing and tail section and the outer rim had end surface that stretched respectively at an angle of 30oand the 40oand the periphery of the rim. For blades of this geometry the angle is 70oC.

There was the intention to obtain the operation of the rest of the cobalt. To obtain such a coating bath filled with a cobalt solution for coating, containing 400 g/l CoSO47H2O, 15 g/l NaCl and 20 g/l of boric acid (H3BO3. The bath was maintained at a pH of 4.5 and a temperature of 45oC. Bath downloaded powder to a concentration of 10 g/l, and the powder had a size distribution of from 5 to 12 μm and consisted of 67.8 wt.% chromium, to 30.1 wt.% aluminum and 1.7 wt.% yttrium.

First, the profile of the wing and parts of the blades were subjected to elyuminirovanie through a process of compacted plating at 900oC for 6 hours under argon. Then aluminized layer was subjected to the subsequent diffusion for 1 hour at 1100oC in vacuum and hardening during aging for 16 hours at 870oC in vacuum.

Before COCrAlY coating material on the part of the tail section and an outer rim that was not going to apply the coating, put the model wax mask, and the remaining surface was subjected to typically the appropriate preparatory processing for applying cobalt coating.

The blade was attached to a push-off device 50, with its axis was directed at an angle of 20othe x-axis clamping device, which avora perpendicular to the axis x, angle 25owhen the duration of cycle 3 minutes. At the same time clamping device is rotated around the x axis in one direction and 360owhen the duration of cycle 10 minutes to complete a full turn. However, the rotation around the x-axis was interrupted by a 10-second periods stop moving 3-second periods of motion.

The coating was carried out at current density of 1.5 a/cm2over a period of time sufficient to obtain a coating thickness of 12 μm.

Received a coating of excellent quality, covering the profile of the wing and tail pad area and the outer rim, and having weights included powder, equal to 0.27. He deposited preferably particles of a small size and was essentially absent soosazhdenie particle size > 12 μm, particles of larger size are left in solution for coating (i.e., the size of which is between 12 and 15 µm). After removal of the coated blades from the fixture in the mask is removed.

Then the blade was subjected to heat treatment at 1100oC for 1 hour in vacuum.

Particularly preferred elements of M2are Y, Hf and Si.

1. A method of producing a coating on a substrate comprising applying the coating by deposition of the metal matrix M1from baths containing particles CrAlM2to Coosada particles with the matrix, where M1is at least one element selected from the group consisting of Ni, Co and Fe, and M2is at least one element selected from the group consisting of Y, Si, Ti, Hf, Ta, Nb, Mn, Pt and rare earth elements, characterized in that before the deposition is carried out by plating, chrome plating or siliconefree the substrate, and the deposition of conducting electrolysis or betalactamase.

2. The method according to p. 1, characterized in that it further conduct heat treated aluminized, siliconized or chrome substrate in vacuum before and after coprecipitation M1CrAlM2moreover, if the heat treatment is carried out before coprecipitation, it is carried out at a temperature of about 1100oC for approximately 1 h, and if the heat treatment is carried out after coprecipitation, it is carried out at a temperature of about 1100oC for 1 h

3. The method according to one of the preceding paragraphs, characterized in that after coprecipitation M1CrAlM2dopolnitelnye fact, the coprecipitation M1CrAlM2carried out at a current density of less than 5 mA/cm2.

5. The method according to one of the preceding paragraphs, characterized in that during the deposition of the metal matrix material and the particles form a layer of thickness less than 50 microns.

6. The method according to one of the preceding paragraphs, characterized in that the deposition of the metal matrix material is carried out at a boot bath of less than 40 g particles/L.

7. The method according to one of the preceding paragraphs, characterized in that when elyuminirovanie, or chrome sililirovanie formed respectively aluminides, promeny or silicide layer thickness of from 30 to 60 μm.

8. The method according to p. 2 or any preceding paragraph, which is dependent to p. 2, characterized in that when elyuminirovanie, or chrome sililirovanie formed respectively aluminides, promeny or silicide layer after the heat treatment consists of an inner diffusion zone with a relatively low concentration of Al, Cr or Si with a thickness of 10 to 20 μm and an outer zone with a relatively high concentration of Al, Cr or Si with a thickness of 20 to 40 microns.

9. The method according to one of predshestvuyuschee, chromed or silicide and during coprecipitation is formed a second layer of M1CrAlM2moreover , the ratio of the thickness of the first layer to the thickness of the second is between 4 : 1 and 1 : 1.

10. The method according to one of the preceding paragraphs, characterized in that the substrate is chosen from the group consisting of shaft gas turbine, the rim of the disk, the constituent elements of the combustion chamber, the blades of the stator, the impeller blades of the turbine guide vanes, wing profile blade of a gas turbine, the tail section of the blades of the gas turbine and the outer rim blades of the gas turbine.

 

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EFFECT: improved and valuable properties of solution.

2 tbl, 1 ex

FIELD: metallurgy.

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FIELD: metallurgy.

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EFFECT: receiving of barrier plate of semiconductor element for prevention of copper diffusion applied in the capacity of electric wiring material.

13 cl, 7 dwg, 3 tbl, 4 ex

FIELD: metallurgy.

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FIELD: process engineering.

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3 cl, 1 tbl, 9 ex

FIELD: technological processes.

SUBSTANCE: invention relates to chemical application of metal coating of nickel-based alloys and can be used in machine building, instrument making and aircraft engineering for making corrosion-resistant, wear-resistant and decorative coatings. Method involves holding articles in an aqueous solution containing components at following ratio, mol/l: nickel salt 0.075-0.125; lead salt (0.6-1.2)·10-5; sodium hypophosphite 0.28-0.40; glycine 0.10-0.40; orthophosphoric acid 0.10-0.30; sodium tetraborate 0.05-0.10, wherein application of coating is performed at solution temperature 70-93 °C and pH 6.3-8.7. Application of coating can be performed on surface of items made of steel, copper and alloys thereof, aluminium and alloys thereof, plastic or fibre and tissue structures from natural or synthetic materials.

EFFECT: invention ensures production of high-quality nickel-phosphorus coating, containing from 5 to 8 % phosphorus, higher efficiency and low power consumption.

3 cl, 1 tbl, 9 ex

FIELD: metallurgy, namely chemical and heat treatment of refractory alloys, possibly used for applying protective coatings onto blades of gas-turbine engines.

SUBSTANCE: method comprises steps of applying onto inner and outer surfaces of parts diffusion aluminide coating in circulating gaseous medium; applying coating in low-active system at relation of reaction surfaces Fн/Fo = 0.3 - 0.7, where Fн - total surface of parts to be coated; Fo - total surface of saturating mixture; then applying onto outer surfaces of parts cladding coating, namely MeCrAlY, where Me - Ni, Co, NiCo by ion-plasma process or electron beam evaporation in vacuum.

EFFECT: improved fire and corrosion resistance of coating, increased resource of blades of gas-turbine engine.

1 cl, 1 ex, 1 tbl

 // 2246684
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