CN114182250A - Preparation method of large-thickness CoNiCrAlY sealing coating of turbine outer ring and CoNiCrAlY sealing coating - Google Patents
Preparation method of large-thickness CoNiCrAlY sealing coating of turbine outer ring and CoNiCrAlY sealing coating Download PDFInfo
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- 238000000576 coating method Methods 0.000 title claims abstract description 136
- 239000011248 coating agent Substances 0.000 title claims abstract description 132
- 238000007789 sealing Methods 0.000 title claims abstract description 35
- 238000002360 preparation method Methods 0.000 title claims abstract description 22
- 238000010288 cold spraying Methods 0.000 claims abstract description 67
- 239000000843 powder Substances 0.000 claims abstract description 59
- 239000000956 alloy Substances 0.000 claims abstract description 42
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 42
- 239000000463 material Substances 0.000 claims abstract description 27
- 238000000151 deposition Methods 0.000 claims abstract description 24
- 230000008021 deposition Effects 0.000 claims abstract description 17
- 238000000034 method Methods 0.000 claims description 46
- 239000007921 spray Substances 0.000 claims description 38
- 239000007789 gas Substances 0.000 claims description 35
- 238000005507 spraying Methods 0.000 claims description 35
- 230000008569 process Effects 0.000 claims description 31
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 18
- 239000002245 particle Substances 0.000 claims description 15
- 239000000758 substrate Substances 0.000 claims description 14
- 238000005498 polishing Methods 0.000 claims description 12
- 238000000227 grinding Methods 0.000 claims description 9
- 239000001307 helium Substances 0.000 claims description 9
- 229910052734 helium Inorganic materials 0.000 claims description 9
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 9
- 238000004140 cleaning Methods 0.000 claims description 7
- 238000005516 engineering process Methods 0.000 abstract description 8
- 230000007797 corrosion Effects 0.000 abstract description 6
- 238000005260 corrosion Methods 0.000 abstract description 6
- 239000010410 layer Substances 0.000 description 39
- 238000000635 electron micrograph Methods 0.000 description 5
- 230000000052 comparative effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 3
- 239000011247 coating layer Substances 0.000 description 3
- 244000137852 Petrea volubilis Species 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000005137 deposition process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 238000010290 vacuum plasma spraying Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
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- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000001493 electron microscopy Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007749 high velocity oxygen fuel spraying Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
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- 238000005086 pumping Methods 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
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- 238000005488 sandblasting Methods 0.000 description 1
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- 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
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
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- Materials Engineering (AREA)
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- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention discloses a preparation method of a large-thickness CoNiCrAlY sealing coating of a turbine outer ring and the CoNiCrAlY sealing coating, which comprise the following steps: pretreating the surface of a base material; preparing CoNiCrAlY alloy powder; carrying out cold spraying on the CoNiCrAlY alloy powder on the surface of a base material, and depositing to form a CoNiCrAlY precoating layer; cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a first coating; and cold spraying CoNiCrAlY alloy powder on the first coating to form a CoNiCrAlY precoating layer through deposition, then cold spraying the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a second coating, and repeating the operation until the CoNiCrAlY sealing coating with the thickness of 1.5-2 mm is obtained. According to the preparation method of the large-thickness CoNiCrAlY sealing coating of the turbine outer ring, the CoNiCrAlY sealing coating which is compact in coating, large in thickness, good in bonding strength, high in high temperature resistance and good in corrosion resistance is prepared on the surface of the high-temperature alloy base material by using a cold spraying technology.
Description
Technical Field
The invention relates to the field of aeroengine turbine outer rings, in particular to a preparation method of a large-thickness CoNiCrAlY seal coating of a turbine outer ring. In addition, the invention also relates to a CoNiCrAlY sealing coating obtained by the preparation method.
Background
The turbine outer ring is used as an important hot end part of an aeroengine and is directly contacted with high-temperature gas, and the service condition is very harsh. Usually, CoNiCrAlY with excellent high-temperature fuel gas oxidation resistance and corrosion resistance is adopted as a high-temperature sealing coating. The application of the CoNiCrAlY coating can effectively reduce the blade tip clearance, improve the engine pressure ratio and the turbine efficiency and reduce the oil consumption; on the other hand, the turbine outer ring can be well protected, and the turbine outer ring has important effects of improving the performance and prolonging the service life of the engine.
The service performance of the CoNiCrAlY high-temperature seal coating is closely related to the preparation process of the CoNiCrAlY high-temperature seal coating, and the preparation technology of the coating mainly Adopts Plasma Spraying (APS), supersonic flame spraying (HVOF) and vacuum plasma spraying (VPS/LPPS), wherein the VPS technology is the first-choice processing technology for preparing the CoNiCrAlY high-temperature seal coating due to the fact that the prepared coating is compact, less oxidized and high in bonding strength. However, in the process of preparing the sealing coating, the technology needs to undergo the processes of vacuumizing, substrate preheating, cooling after spraying, vacuum atmosphere quitting and the like, so that the method has low production efficiency and high cost, large thermal stress can be generated in the coating deposition process, the risk of coating cracking is increased, and the preparation of the large-thickness (more than 1.5mm) coating is particularly difficult, and the characteristics become the application bottleneck of preparing the large-thickness sealing coating by adopting the VPS technology. Although improved processes have appeared in recent years, the preparation of large thickness seal coatings can be achieved by repeating the steps of sand blasting, vacuum pumping, transferred arc cleaning, spraying, and diffusion heat treatment to relieve the stress of the coating and improve the bonding strength. But the process is complex, the production efficiency is low, the cost is high, and the product quality is difficult to control.
Disclosure of Invention
The invention provides a preparation method of a large-thickness CoNiCrAlY sealing coating of a turbine outer ring and the CoNiCrAlY sealing coating, and aims to solve the technical problems of complex process, low production efficiency, high cost and difficult product quality control in the preparation of the CoNiCrAlY high-temperature sealing coating by vacuum plasma spraying.
The technical scheme adopted by the invention is as follows:
a preparation method of a large-thickness CoNiCrAlY seal coating of a turbine outer ring comprises the following steps:
pretreating the surface of a base material;
preparing CoNiCrAlY alloy powder;
carrying out cold spraying on the CoNiCrAlY alloy powder on the surface of a base material, and depositing to form a CoNiCrAlY precoating layer;
cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a first coating;
and cold spraying CoNiCrAlY alloy powder on the first coating to form a CoNiCrAlY precoating layer through deposition, then cold spraying the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a second coating, and repeating the operation until the CoNiCrAlY sealing coating with the thickness of 1.5-2 mm is obtained.
Further, in the cold spraying process of the slope section at the edge of the CoNiCrAlY precoat layer, the spraying angle of the spray gun is 45-90 degrees.
Further, the spraying path is formed in a mode that one end, close to the inner circle of the outer ring of the turbine, of the slope section advances towards the other end of the slope section, one-pass cold spraying is completed, the outer ring of the turbine rotates in the circumferential direction for a certain distance, the spray gun moves to the end, close to the inner circle of the outer ring of the turbine, of the slope section, the next-pass cold spraying is conducted, and the operation is repeated until the slope section of the CoNiCrAlY precoat disappears.
Further, the cold spray process of the ramp segment at the edge of the CoNiCrAlY precoat comprises: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 3 MPa-5 MPa, the temperature of the accelerating gas is 500-1000 ℃, the moving speed of a spray gun is 50-1000 mm/s, and the powder feeding amount is 1-10 rpm.
Further, the thickness of the coating formed by cold spraying at one end of the slope section close to the inner circle of the outer ring of the turbine is larger than that of the coating formed by cold spraying at the other end of the slope section.
Further, the particle size of the CoNiCrAlY alloy powder is 5-100 μm.
Further, the cold spray process on the surface of the substrate comprises: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 2 MPa-5 MPa, the temperature of the accelerating gas is 400-1000 ℃, the moving speed of a spray gun is 50 mm/s-1000 mm/s, the powder feeding amount is 1-10 rpm, and the spraying angle is 90 degrees.
Further, the substrate surface pretreatment comprises: and carrying out coarse grinding and fine polishing on the surface of the base material, and cleaning the surface after the fine polishing.
Further, the thickness of the first coating is 0.1mm to 1 mm.
According to another aspect of the invention, the CoNiCrAlY seal coating obtained by the preparation method is also provided.
The invention has the following beneficial effects:
according to the preparation method of the large-thickness CoNiCrAlY sealing coating of the turbine outer ring, the CoNiCrAlY sealing coating which is compact in coating, large in thickness, good in bonding strength, high in high temperature resistance and good in corrosion resistance is prepared on the surface of the high-temperature alloy base material by using a cold spraying technology. The cold spraying process is not formed by one-time deposition, the spray gun circularly and continuously moves above the surface of the base material, high-speed CoNiCrAlY alloy powder particles impact the base body to be stacked layer by layer, and finally a CoNiCrAlY sealing coating with large thickness is formed on the surface of the base body. In the cold spraying process, cold spraying treatment is performed on the slope newly formed at the edge of the CoNiCrAlY precoating layer in a targeted manner, the slope of the CoNiCrAlY precoating layer is filled, and the method is repeated when each layer of CoNiCrAlY sealing coating is sprayed, so that the CoNiCrAlY sealing coating with large thickness, no slope and uniform thickness is obtained, and the limitation of other process methods is effectively avoided.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic illustration of the cold spray process of the CoNiCrAlY seal coating of the present invention;
FIG. 2 is an electron micrograph of a CoNiCrAlY seal coating according to preferred embodiment 1 of the present invention;
FIG. 3 is an electron micrograph of a CoNiCrAlY seal coating according to the preferred embodiment 2 of the present invention.
The reference numbers illustrate:
1. the initial position of the spray gun; 2. the position of a spray gun on the slope section; 3. a CoNiCrAlY precoat; 4. a substrate surface.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic illustration of the cold spray process of the CoNiCrAlY seal coating of the present invention; FIG. 2 is an electron micrograph of a CoNiCrAlY seal coating according to preferred embodiment 1 of the present invention; FIG. 3 is an electron micrograph of a CoNiCrAlY seal coating according to the preferred embodiment 2 of the present invention.
As shown in FIG. 1, the preparation method of the large-thickness CoNiCrAlY seal coating of the turbine outer ring of the embodiment comprises the following steps:
pretreating the surface of a base material;
preparing CoNiCrAlY alloy powder;
carrying out cold spraying on the CoNiCrAlY alloy powder on the surface of a base material, and depositing to form a CoNiCrAlY precoating layer;
cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a first coating;
and cold spraying CoNiCrAlY alloy powder on the first coating to form a CoNiCrAlY precoating layer through deposition, then cold spraying the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a second coating, and repeating the operation until the CoNiCrAlY sealing coating with the thickness of 1.5-2 mm is obtained.
According to the preparation method of the large-thickness CoNiCrAlY sealing coating of the turbine outer ring, the CoNiCrAlY sealing coating which is compact in coating, large in thickness, good in bonding strength, high in high temperature resistance and good in corrosion resistance is prepared on the surface of the high-temperature alloy base material by using a cold spraying technology. The cold spraying process is not formed by one-time deposition, the spray gun circularly and continuously moves above the surface of the base material, high-speed CoNiCrAlY alloy powder particles impact the base body to be stacked layer by layer, and finally a CoNiCrAlY sealing coating with large thickness is formed on the surface of the base body. In the cold spraying process, cold spraying treatment is performed on the slope newly formed at the edge of the CoNiCrAlY precoating layer in a targeted manner, the slope of the CoNiCrAlY precoating layer is filled, and the method is repeated when each layer of CoNiCrAlY sealing coating is sprayed, so that the CoNiCrAlY sealing coating with large thickness, no slope and uniform thickness is obtained, and the limitation of other process methods is effectively avoided.
Cold spray is an aerodynamic based process that uses a high pressure gas source to drive solid particles to a very high velocity to impact a substrate and deposit a coating. The cold spraying processing process does not involve melting-solidification process, the heat influence on deposited CoNiCrAlY alloy powder and a base material is obviously reduced, oxidation, phase change, deformation, cracking and the like can be effectively avoided, the deposition efficiency is high, and a large-thickness CoNiCrAlY sealing coating can be quickly sprayed, so that the method is suitable for manufacturing aviation parts. The deposition process is that CoNiCrAlY powder enters a nozzle of a spray gun from a powder feeding pipe through gas (nitrogen or helium) to be heated and accelerated, and finally high-speed particles are sprayed out from the nozzle to generate plastic deformation on the surface of a base material to achieve deposition and form a coating.
The CoNiCrAlY alloy powder particles are not uniform in speed when being ejected from the nozzle and are generally in Gaussian distribution, namely, the CoNiCrAlY alloy powder particles ejected from the center of the nozzle have high speed, and the CoNiCrAlY alloy powder particles ejected from the edge of the nozzle have low speed, so that the CoNiCrAlY alloy powder particles ejected from the edge of the nozzle are rebounded, the deposition efficiency is low, and a slope is formed. As the thickness of the coating increases, the slope becomes more pronounced making subsequent coating deposition more difficult until a triangular pyramidal shaped coating is finally formed. In addition, since the lance itself is angled, there is some angular deviation of the lance during the injection process, resulting in a slope at the edge of the CoNiCrAlY precoat on the surface of the deposited substrate. Therefore, the factors influence the integral coating uniformity of the CoNiCrAlY seal coating and influence the high temperature resistance and the corrosion resistance.
In the embodiment, in the cold spraying process of the slope section at the edge of the CoNiCrAlY precoat layer, the spraying angle of the spray gun is 45-90 degrees. In the cold spraying process of the slope section at the edge of the CoNiCrAlY precoating layer, the set spraying angle is 45-90 degrees relative to the slope section, and after the set spraying angle exceeds the range, the angle between the spray gun and the precoating layer is too large or too small, so that the deposition efficiency of particles is greatly reduced, and the deposition of a new coating is not facilitated.
In this embodiment, the spraying path is performed by moving one end of the inner circle of the outer ring of the turbine from the slope section to the other end of the slope section, so as to complete one-pass cold spraying, the outer ring of the turbine rotates in the circumferential direction for a certain distance, the spray gun moves to one end of the inner circle of the outer ring of the turbine at the slope section, and the next-pass cold spraying is performed, and the above operations are repeated until the slope section of the CoNiCrAlY precoat disappears. The outer ring of the turbine of the aircraft engine is pre-installed on the clamp, and then the clamp is installed on the rotary table so as to rotate through the clamp to drive the outer ring of the turbine to rotate circumferentially and then carry out cold spraying treatment.
Along with the thickening of the cold spraying coating, the edge of the CoNiCrAlY precoating layer is easy to form a slope based on the spraying characteristic of cold spraying, when the slope appears, the spraying angle and the spraying path of a spray gun are required to be adjusted, the spraying angle is 45-90 degrees, so that CoNiCrAlY alloy powder sprayed from the spray gun keeps a certain angle with the slope section, and the spraying is continued until the slope of the CoNiCrAlY precoating layer disappears. And then, adjusting the spraying angle of the spray gun again to ensure that the sprayed CoNiCrAlY alloy powder and the first coating are kept perpendicular to continue spraying, repeating the operations, and circumferentially rotating the outer ring of the turbine for one circle to fill and level all slopes, thereby obtaining the CoNiCrAlY coating with large thickness, no slopes and uniform thickness.
In this embodiment, the cold spraying process of the slope section at the edge of the CoNiCrAlY precoat layer includes: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 2MPa to 5MPa, and the temperature of the accelerating gas is 400 ℃ to 1000 ℃. Too low a pressure and temperature of the accelerating gas below this parameter range results in a lower speed of the CoNiCrAlY alloy powder, which cannot be deposited to form a coating. Too high a pressure and temperature of the accelerating gas, beyond which the speed of the CoNiCrAlY alloy powder is too high, causes erosion of the substrate surface and likewise no deposition of the coating. The moving speed of the spray gun is 50 mm/s-1000 mm/s, and the powder feeding amount is 1 rpm-10 rpm. Preferably, the moving speed of the spray gun is 200mm/s to 400mm/s and the moving speed of the spray gun is 300mm/s to 500 mm/s. And/or, preferably, the powder feeding amount is 2rpm to 3rpm and the powder feeding amount is 5rpm to 6 rpm.
In the embodiment, the thickness of the coating formed by cold spraying at one end of the slope section, which is close to the inner circle of the outer ring of the turbine, is larger than that of the coating formed by cold spraying at the other end of the slope section. Due to the non-uniform thickness of the CoNiCrAlY precoat layer of the newly created ramp section at the edge during cold spraying of the substrate surface, the thickness of the CoNiCrAlY precoat layer near the end of the inner circle of the turbine outer ring is smaller than the thickness of the CoNiCrAlY precoat layer at the end of the inner circle remote from the turbine outer ring. Therefore, when cold spraying is carried out on the slope section, more spraying is carried out on one end, close to the inner circle of the turbine outer ring, of the slope section, less spraying is carried out on one end, far away from the inner circle of the turbine outer ring, of the slope section, and the CoNiCrAlY sealing coating with uniform thickness is finally obtained by controlling different spraying amounts. Preferably, the speed of movement of the lances is slow at the end of the lance that is closer to the inner circle of the outer ring of the turbine, so that more CoNiCrAlY coating is deposited per unit area, and is increased at the end of the lance that is further from the inner circle of the outer ring of the turbine, so that less CoNiCrAlY coating is deposited per unit area. Alternatively, it may be preferable to use different powder delivery at both ends, i.e. more powder delivery near the end of the inner circle of the turbine outer ring, so that more CoNiCrAlY coating is deposited per unit area, and less powder delivery at the end of the inner circle remote from the turbine outer ring, so that less conicray coating is deposited per unit area, to obtain a CoNiCrAlY seal coating of uniform thickness.
In this example, the CoNiCrAlY alloy powder had a particle size of 5 μm to 100. mu.m. The CoNiCrAlY alloy powder has undersize granularity and is greatly influenced by shock waves at the outlet of the nozzle, so that the speed reduction effect of the powder is obvious, and the deposition of the CoNiCrAlY alloy is not facilitated. The CoNiCrAlY alloy powder has overlarge granularity, the CoNiCrAlY alloy powder has larger mass and poor acceleration effect, so that the kinetic energy is lower, and the deposition of the CoNiCrAlY alloy is also not facilitated. Optionally, the CoNiCrAlY alloy powder has a particle size of 5 μm to 50 μm.
In this embodiment, the cold spray process on the surface of the substrate includes: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 3 MPa-5 MPa, the temperature of the accelerating gas is 500-1000 ℃, the moving speed of a spray gun is 200 mm/s-500 mm/s, the powder feeding amount is 1-10 rpm, and the spraying angle is 90 degrees.
In this embodiment, the substrate surface pretreatment comprises: and carrying out coarse grinding and fine polishing on the surface of the base material, and cleaning the surface after the fine polishing. The surface of the base material is subjected to rough grinding and fine polishing through a grinding machine and/or abrasive paper to remove an oxide layer on the surface of the base material, and simultaneously, the surface of the base material after the fine polishing is subjected to alcohol cleaning or ultrasonic cleaning before cold spraying treatment to clean the surface so as to achieve better subsequent deposition effect.
In this embodiment, the thickness of the first coating layer is 0.1mm to 1 mm. The thickness of each coating is 0.1-1 mm, and multiple spraying and multiple thin spraying modes can greatly improve the uniformity of the CoNiCrAlY sealing coating. Preferably, at least 10 sprays are applied.
According to another aspect of the invention, the CoNiCrAlY seal coating obtained by the preparation method is also provided. The CoNiCrAlY sealing coating with compact coating, good bonding strength, high temperature resistance and good corrosion resistance is prepared on the surface of the high-temperature alloy substrate.
Examples
A high-pressure cold spray apparatus was purchased from Nippon plasma Kogyo Co.
Example 1
The preparation method of the large-thickness CoNiCrAlY sealing coating of the turbine outer ring comprises the following steps:
s1, performing coarse grinding and fine polishing on the surface of the base material of the GH625 turbine outer ring through a grinding machine and/or sand paper, and performing alcohol cleaning on the surface base material after the fine polishing before cold spraying treatment;
s2, loading CoNiCrAlY alloy powder with the particle size of 5-20 microns into a powder feeder container, packaging the powder feeder, fixing the outer ring of the turbine by using a clamp, and installing the clamp on a turntable;
s3, cold spraying CoNiCrAlY alloy powder on the surface of the base material by adopting a high-pressure cold spraying device, wherein the spraying path is formed by advancing along the end surface of the outer ring of the turbine from top to bottom, the outer ring of the turbine rotates on the turntable in the circumferential direction, and the cold spraying process comprises the following steps: adopting nitrogen as accelerating gas, wherein the pressure of the accelerating gas is 3.5MPa, the temperature of the accelerating gas is 920 ℃, the moving speed of a spray gun is 400mm/s, the powder feeding amount is 6rpm, the spraying angle is 90 degrees, and depositing to form a CoNiCrAlY precoating layer;
s4, cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer, the spraying path is that one end of the inner circle of the slope section close to the turbine outer ring advances towards the direction of the other end of the slope section, one pass of cold spraying is completed, the turbine outer ring rotates in the circumferential direction for a certain distance, the spray gun moves to the end of the inner circle of the slope section close to the turbine outer ring, the next pass of cold spraying is repeated until the slope section of the CoNiCrAlY precoating layer disappears, and a first coating is formed, wherein the cold spraying process comprises the following steps: nitrogen is used as accelerating gas, the pressure of the accelerating gas is 3.5MPa, the temperature of the accelerating gas is 920 ℃, the moving speed of the spray gun is gradually increased from 500mm/s of the moving speed of one end of a slope section close to the inner circle of the outer ring of the turbine to 800mm/s of the moving speed of the other end of the slope section, the powder feeding amount is 2rpm, and the spraying angle is 75 degrees;
s5; the CoNiCrAlY alloy powder is cold sprayed on the first coating, and the steps S3 and S4 are repeated to form a second coating, … …, and a tenth coating is formed until a CoNiCrAlY seal coating with the thickness of 1.8mm is obtained.
Example 2
The preparation method of the large-thickness CoNiCrAlY sealing coating of the turbine outer ring comprises the following steps:
s1, performing coarse grinding and fine polishing on the surface of the base material of the GH625 turbine outer ring through a grinding machine and/or sand paper, and performing alcohol cleaning on the surface base material after the fine polishing before cold spraying treatment;
s2, loading CoNiCrAlY alloy powder with the particle size of 5-20 microns into a powder feeder container, packaging the powder feeder, fixing the outer ring of the turbine by using a clamp, and installing the clamp on a turntable;
s3, cold spraying CoNiCrAlY alloy powder on the surface of the base material by adopting a high-pressure cold spraying device, wherein the spraying path is formed by advancing along the end surface of the outer ring of the turbine from top to bottom, the outer ring of the turbine rotates on the turntable in the circumferential direction, and the cold spraying process comprises the following steps: helium is used as accelerating gas, the pressure of the accelerating gas is 3.5MPa, the temperature of the accelerating gas is 700 ℃, the moving speed of a spray gun is 700mm/s, the powder feeding amount is 5rpm, the spraying angle is 90 degrees, and a CoNiCrAlY precoating layer is formed by deposition;
s4, cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer, the spraying path is that one end of the inner circle of the slope section close to the turbine outer ring advances towards the direction of the other end of the slope section, one pass of cold spraying is completed, the turbine outer ring rotates in the circumferential direction for a certain distance, the spray gun moves to the end of the inner circle of the slope section close to the turbine outer ring, the next pass of cold spraying is repeated until the slope section of the CoNiCrAlY precoating layer disappears, and a first coating is formed, wherein the cold spraying process comprises the following steps: helium is used as accelerating gas, the pressure of the accelerating gas is 3.5MPa, the temperature of the accelerating gas is 700 ℃, the moving speed of the spray gun is gradually reduced from the powder feeding amount of 3rpm at one end of a slope section close to the inner circle of the outer ring of the turbine to the powder feeding amount of 1rpm at the other end of the slope section, the moving speed is 600mm/s, and the spraying angle is 80 degrees;
s5, cold spraying CoNiCrAlY alloy powder on the first coating, and repeating the steps S3 and S4 to form a second coating, … … and a fourteenth coating until a CoNiCrAlY seal coating with the thickness of 1.7mm is obtained.
Comparative example 1
The differences from example 1 are: depositing a first coating layer in step S3; step S4 is not performed; cold spray coating is performed on the first coating in step S5, and step S3 is repeated to form a second coating, … …, and a tenth coating is formed until a CoNiCrAlY seal coating having a thickness of 1.8mm is obtained.
Comparative example 2
The differences from example 2 are: depositing a first coating layer in step S3; step S4 is not performed; cold spray coating is performed on the first coating in step S5, and step S3 is repeated to form a second coating, … …, and a fourteenth coating is formed until a CoNiCrAlY seal coating having a thickness of 1.7mm is obtained.
Measurements (vernier calipers) were made on the CoNiCrAlY seal coatings of examples 1 and 2, comparative examples 1 and 2 above, and the CoNiCrAlY seal coatings of examples 1 and 2 were examined by electron microscopy.
The CoNiCrAlY seal coatings of examples 1 and 2 were uniform in thickness and slope free; the CoNiCrAlY seal coating edges of comparative examples 1 and 2 both exhibited a slope of about 45 °.
As shown in FIG. 2 and FIG. 3, electron micrographs of the CoNiCrAlY seal coating of example 1 show that the CoNiCrAlY seal coating has a uniform thickness of about 2mm, is dense inside the coating, has no obvious cracks and void defects, and has good bonding with the substrate, no delamination, and high quality of the coating.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A preparation method of a large-thickness CoNiCrAlY seal coating of a turbine outer ring is characterized by comprising the following steps:
pretreating the surface of a base material;
preparing CoNiCrAlY alloy powder;
carrying out cold spraying on the CoNiCrAlY alloy powder on the surface of a base material, and depositing to form a CoNiCrAlY precoating layer;
cold spraying is carried out on the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a first coating;
and cold spraying CoNiCrAlY alloy powder on the first coating to form a CoNiCrAlY precoating layer through deposition, then cold spraying the slope section at the edge of the CoNiCrAlY precoating layer until the slope section of the CoNiCrAlY precoating layer disappears to form a second coating, and repeating the operation until the CoNiCrAlY sealing coating with the thickness of 1.5-2 mm is obtained.
2. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 1,
in the cold spraying process of the slope section at the edge of the CoNiCrAlY precoat layer, the spraying angle of the spray gun is 45-90 degrees.
3. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 2,
and the spraying path adopts the way that one end of the slope section, which is close to the inner circle of the outer ring of the turbine, moves towards the other end of the slope section to finish one-pass cold spraying, the outer ring of the turbine rotates for a certain distance in the circumferential direction, the spray gun moves to one end of the slope section, which is close to the inner circle of the outer ring of the turbine, the next-pass cold spraying is carried out, and the operation is repeated until the slope section of the CoNiCrAlY precoating layer disappears.
4. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 2,
the cold spray process of the ramp segment at the edge of the CoNiCrAlY precoat includes: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 3 MPa-5 MPa, the temperature of the accelerating gas is 500-1000 ℃, the moving speed of a spray gun is 50-1000 mm/s, and the powder feeding amount is 1-10 rpm.
5. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 3,
the thickness of the coating formed by cold spraying at one end of the slope section, which is close to the inner circle of the outer ring of the turbine, is larger than that of the coating formed by cold spraying at the other end of the slope section.
6. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 1,
the particle size of the CoNiCrAlY alloy powder is 5-100 mu m.
7. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 1,
the cold spraying process on the surface of the substrate comprises the following steps: nitrogen or helium is used as accelerating gas, the pressure of the accelerating gas is 2 MPa-5 MPa, the temperature of the accelerating gas is 400-1000 ℃, the moving speed of a spray gun is 50 mm/s-1000 mm/s, the powder feeding amount is 1-10 rpm, and the spraying angle is 90 degrees.
8. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 1,
the surface pretreatment of the substrate comprises:
and carrying out coarse grinding and fine polishing on the surface of the base material, and cleaning the surface after the fine polishing.
9. The method for preparing the large-thickness CoNiCrAlY seal coating of the outer ring of the turbine according to claim 1,
the thickness of the first coating is 0.1 mm-1 mm.
10. A CoNiCrAlY seal coating obtained by the method of preparation according to any one of claims 1 to 9.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4527507A (en) * | 1983-07-13 | 1985-07-09 | Honda Giken Kogyo Kabushiki Kaisha | Spray apparatus for applying a sharp-edged pattern of coating |
| US5110631A (en) * | 1985-11-12 | 1992-05-05 | Osprey Metals Limited | Production of metal spray deposits |
| US6623808B1 (en) * | 1999-02-23 | 2003-09-23 | Ford Global Technologies, Inc. | Spray deposition process |
| JP2013064365A (en) * | 2011-09-20 | 2013-04-11 | Hitachi Ltd | Member having abradable coating, and gas turbine |
| CN113215513A (en) * | 2021-05-11 | 2021-08-06 | 成都中科翼能科技有限公司 | Novel post-treatment process for abradable Al/BN sealing coating of gas turbine part |
-
2021
- 2021-12-08 CN CN202111488701.0A patent/CN114182250A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4527507A (en) * | 1983-07-13 | 1985-07-09 | Honda Giken Kogyo Kabushiki Kaisha | Spray apparatus for applying a sharp-edged pattern of coating |
| US5110631A (en) * | 1985-11-12 | 1992-05-05 | Osprey Metals Limited | Production of metal spray deposits |
| US6623808B1 (en) * | 1999-02-23 | 2003-09-23 | Ford Global Technologies, Inc. | Spray deposition process |
| JP2013064365A (en) * | 2011-09-20 | 2013-04-11 | Hitachi Ltd | Member having abradable coating, and gas turbine |
| CN113215513A (en) * | 2021-05-11 | 2021-08-06 | 成都中科翼能科技有限公司 | Novel post-treatment process for abradable Al/BN sealing coating of gas turbine part |
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