CN115122243B - Coating thickness removal method with controllable coating thickness - Google Patents
Coating thickness removal method with controllable coating thickness Download PDFInfo
- Publication number
- CN115122243B CN115122243B CN202210884179.6A CN202210884179A CN115122243B CN 115122243 B CN115122243 B CN 115122243B CN 202210884179 A CN202210884179 A CN 202210884179A CN 115122243 B CN115122243 B CN 115122243B
- Authority
- CN
- China
- Prior art keywords
- thickness
- coating
- sand
- coating thickness
- blowing
- 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.)
- Active
Links
- 239000011248 coating agent Substances 0.000 title claims abstract description 178
- 238000000576 coating method Methods 0.000 title claims abstract description 178
- 238000000034 method Methods 0.000 title claims abstract description 69
- 239000004576 sand Substances 0.000 claims abstract description 108
- 238000007664 blowing Methods 0.000 claims abstract description 102
- 230000008569 process Effects 0.000 claims abstract description 33
- 238000005498 polishing Methods 0.000 claims abstract description 14
- 238000012360 testing method Methods 0.000 claims description 19
- 230000007704 transition Effects 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 14
- 229910052593 corundum Inorganic materials 0.000 claims description 13
- 239000010431 corundum Substances 0.000 claims description 12
- 238000005507 spraying Methods 0.000 claims description 12
- 239000007921 spray Substances 0.000 claims description 6
- 230000002596 correlated effect Effects 0.000 claims description 3
- 238000005524 ceramic coating Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000009499 grossing Methods 0.000 description 4
- 230000000875 corresponding effect Effects 0.000 description 3
- 238000005488 sandblasting Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000007517 polishing process Methods 0.000 description 2
- 238000004381 surface treatment Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 244000137852 Petrea volubilis Species 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/04—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C9/00—Appurtenances of abrasive blasting machines or devices, e.g. working chambers, arrangements for handling used abrasive material
Abstract
The invention relates to a coating thickness removing method with controllable coating thickness, wherein the coating comprises a full coating thickness area and a thinning area, the full coating thickness area and the thinning area have different coating thicknesses, and the coating thickness removing method sequentially comprises the following steps: s10: determining the number of sand blowing cycles based on the difference delta T between the thickness of the thinned area and the target thickness and the sand blowing process parameters; s20: blowing sand to the thinning area based on the number of sand blowing cycles until the difference between the thickness of the thinning area and the target thickness is less than or equal to the coating removal thickness of single sand blowing; s30: the coating thickness of the thinned region is treated by polishing until reaching a target thickness. By the coating thickness removing method with controllable coating thickness, the coating thickness is removed controllably and accurately while ensuring the accuracy and repeatability of the coating thickness aiming at the condition that the surfaces of the same component or product have different coating thicknesses.
Description
Technical Field
The invention relates to the technical field of surface treatment, in particular to a coating thickness removing method with controllable coating thickness.
Background
Parts or products such as turbine blades of gas turbines generally require a coating of a certain thickness for surface protection to ensure that the surface quality of the parts or products meets the corresponding requirements, thereby ensuring the mechanical properties of the parts or products during use. When there is a gradient coating thickness requirement in a component or product, i.e., when there is a large thickness difference between the full coating thickness region and the thinned region in the coating, a removal process for the corresponding coating thickness is required.
Currently, conventional ceramic coating removal methods based on coating thickness requirements mainly include coating program control process methods for design thinning, conventional sanding or similar removal by sanding tools, and the like. The coating program control process method is suitable for the condition that the thickness difference between the full coating thickness area and the thickness of the thinning area in the coating is smaller, for example, the thickness of the full coating thickness area is 2-3 times that of the thickness of the thinning area. However, if the ratio of this thickness difference exceeds 5 times, it is difficult to obtain a coating having a smooth transition and to obtain a relatively thin coating region. At the same time, the desired removal criteria are also difficult to achieve by conventional surface sanding or grinding tools because the surface of the coating becomes smoother and smoother after the coating has been removed to some extent, resulting in less and less removal. In addition, the manually controlled sanding process does not guarantee the accuracy and repeatability of the coating thickness.
The matters in the background section are only those known to the public and do not, of course, represent prior art in the field.
Disclosure of Invention
The technical problem to be solved by the invention is that when the gradient coating thickness requirements exist in parts such as turbine blades of a gas turbine and products, and when larger thickness differences exist between a full coating thickness region and a thinning region, the coating thickness removal method in the prior art cannot realize the accurate control and repeatability of the coating thickness removal.
In order to solve the technical problems, the technical scheme adopted by the invention is to provide a coating thickness removing method with controllable coating thickness, wherein the coating comprises a full coating thickness area and a thinning area, the full coating thickness area and the thinning area have different coating thicknesses, and the coating thickness removing method sequentially comprises the following steps:
s10: determining the number of sand blowing cycles based on the difference delta T between the thickness of the thinned area and the target thickness and the sand blowing process parameters;
S20: blowing sand to the thinning area based on the number of sand blowing cycles until the difference between the thickness of the thinning area and the target thickness is less than or equal to the coating removal thickness of single sand blowing;
s30: the coating thickness of the thinned region is treated by polishing until reaching a target thickness.
The redundant coating thickness is removed to the maximum extent through repeated sand blowing, and then the thinning area after sand blowing is polished, so that the design requirement of great coating thickness difference on the same component or product is realized.
According to one aspect of the invention, the coating thickness removal method further comprises: the full-coat thickness region is masked prior to blowing. The full-coating thickness region is shielded before sand blasting is performed on the thinning region, so that the thickness of the full-coating thickness region can be prevented from being influenced, and the surface accuracy of the full-coating thickness region is ensured.
According to one aspect of the invention, the step S10 includes: and determining the coating removal thickness T of the thinning area by single sand blowing based on the difference delta T between the thickness of the thinning area and the target thickness and the sand blowing technological parameter, and calculating the sand blowing circulation times C of the thinning area, wherein C is an integer obtained by delta T/T or an integer rounded upwards. The thickness of the coating removed by single sand blowing and the times of sand blowing circulation are calculated, so that the thinning area can be accurately blown with sand for multiple times.
According to one aspect of the invention, the step S20 includes: and blowing sand to the thinning area according to the coating removal thickness t of the single sand blowing, wherein the sand blowing times are C-1 times. The redundant coating thickness can be removed accurately by blowing sand to the maximum extent through C-1 times of sand blowing.
According to one aspect of the invention, the step S10 includes: the thickness of the coating in the thinned region is measured using a thickness gauge. The coating thickness of the thinned region is measured by a coating thickness gauge to be compared with a target thickness for the next step.
According to one aspect of the present invention, the step S30 includes: and testing whether the thickness of the coating of the thinned area after polishing meets the requirement or not by using a thickness gauge. And checking whether the thickness requirement of the thinning area is met through a thickness gauge so as to better adjust and control the polishing treatment.
According to one aspect of the invention, the coating thickness removal method further comprises: and metallographic testing whether the thickness of the coating of the thinned area after polishing meets the requirement. And checking whether the thickness requirement of the thinning area is met through a metallographic test again so as to more accurately adjust and control the grinding treatment.
According to one aspect of the present invention, in the step S30, the coating thickness of the thinned region is processed by hand sanding up to a target thickness. The polishing process and the coating thickness can be controlled and adjusted more accurately and flexibly by manual polishing.
According to one aspect of the invention, the step S10 includes: setting sand blowing technological parameters, performing multiple sand blowing tests by using sand materials of preset materials, and carrying out average calculation on the coating removal thickness before and after each sand blowing to obtain the coating removal thickness t of the single sand blowing. By setting the sand blowing technological parameters and performing sand blowing tests for multiple times to determine the coating removal thickness of single sand blowing, the coating removal amount of single sand blowing can be accurate and uniform, so that the coating surface with high surface consistency can be obtained after multiple times of sand blowing.
According to one aspect of the invention, the blowing process parameters are set such that the coating removal thickness T of the single blow is positively correlated with the difference Δt between the thickness of the thinned region and the target thickness. T can be adjusted and revised according to the requirement of deltat, so that single sand blowing can be controlled and flexibly adjusted.
According to one aspect of the invention, the sand material of the predetermined material is white corundum sand, and the sand blowing process parameters comprise: the mesh number of the white corundum sand, the sand blowing pressure, the spraying distance, the spraying angle and the moving speed of the spray gun. The determination of the sand blowing process parameters can enable the control of the sand blowing process to be more accurate, and the sand blowing process parameters can be adjusted at any time according to the needs, so that the sand blowing process parameters can be suitable for processing different coating thicknesses of various different types of parts or products.
According to one aspect of the invention, the white corundum sand has a sand mesh number of 90 or 200 mesh type, a sand blowing pressure of 1.5-2.0 bar, a spraying distance of 80-120 mm, a spraying angle of 30-60 degrees and a spray gun moving speed of 10-50 mm/s. The sand blowing process parameters are obtained through multiple sand blowing tests, so that the sand blowing efficiency can be improved, and the method is suitable for the thickness treatment of the coating on the ceramic surface.
According to one aspect of the invention, the coating further comprises a transition region, wherein the transition region connects the full-thickness region and the thinned region, and the coating thickness of the transition region is between the coating thickness of the full-thickness region and the coating thickness of the thinned region. The arrangement of the transition zone can realize uniform transition from a full coating thickness zone to a thinning zone, so that a part or a product can obtain a smoother coating surface, thereby having better physical properties.
According to the embodiment of the invention, the thickness of the coating is controlled by providing the coating thickness removing method, the thickness of the coating is removed by firstly carrying out controllable sand blasting treatment on the thinning area, and then manually polishing the surface of the coating of the thinning area after sand blasting, so that the problems that the removal of the coating thickness is uncontrollable and the design thickness requirement is not met when the thickness difference between the full coating thickness area and the thickness of the thinning area is large in the prior art are solved, the accuracy of the surface of the coating of the thinning area is improved, the labor and time cost of manual polishing treatment are reduced, and meanwhile, the process difficulty of coating thinning is solved.
Drawings
A further understanding of the invention will be provided by the accompanying drawings, which form a part hereof, and which together with examples serve to explain, without limitation, the invention. In the drawings:
FIG. 1 shows a schematic representation of coating thickness according to one embodiment of the invention; and
FIG. 2 shows a flow chart of a coating thickness removal method with controllable coating thickness according to one embodiment of the invention.
Detailed Description
Hereinafter, only certain exemplary embodiments are briefly described. As will be recognized by those of skill in the pertinent art, the described embodiments may be modified in various different ways without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature and not as restrictive.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, and may be mechanically connected, electrically connected, or may communicate with each other, for example; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is less level than the second feature.
The following disclosure provides many different embodiments, or examples, for implementing different features of the invention. In order to simplify the present disclosure, components and arrangements of specific examples are described below. They are, of course, merely examples and are not intended to limit the invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples, which are for the purpose of brevity and clarity, and which do not themselves indicate the relationship between the various embodiments and/or arrangements discussed. In addition, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.
The embodiments of the present invention will be described below with reference to the accompanying drawings, and it should be understood that the embodiments described herein are for illustration and explanation of the present invention only, and are not intended to limit the present invention.
FIG. 1 illustrates a schematic diagram of coating thickness according to one embodiment of the invention. As shown in fig. 1, the surface of the component or product 100 has a coating 200 thereon, wherein the coating 200 is divided into three regions according to the thickness, and the three regions are sequentially arranged from left to right in fig. 1: full coating thickness region 210, transition region 220, and thinned region 230. Wherein the transition region 220 connects the full-thickness region 210 and the thinned region 230, the transition region 220 has a slope shape between the full-thickness region 210 and the thinned region 230, and the transition region 220 has a coating thickness between the full-thickness region 210 and the thinned region 230, which can smoothly transition.
According to one embodiment of the invention, the coating 200 includes a full coating thickness region 210 and a thinned region 230, the full coating thickness region 210 and the thinned region 230 having different coating thicknesses. Typically, the thickness of the full-thickness region 210 is more than twice the thickness of the thinned region 230. In this embodiment there is no transition zone 220, in other words, the transition from the full-coat zone 210 perpendicular to the surface of the part or product 100 to the thinned zone 230, so that there are only two coating zones of different thickness on the surface of the part or product 100, namely full-coat zone 210 and thinned zone 230, respectively.
According to one embodiment of the invention, the component or product 100 is a blade of a gas turbine. The blades of gas turbines are important components of gas turbines, and their working environment generally requires the blades to have high mechanical strength. The blade is usually made of aluminum alloy, titanium alloy, nickel alloy, iron-based stainless steel, etc., so that the surface of the blade needs a coating to resist corrosion, and the surface of the blade also usually requires a certain surface roughness. As shown in FIG. 1, a coating 200 having a gradient thickness is provided on the blade 100. According to one embodiment of the invention, the coating 200 is a ceramic coating, which is a porous coating to protect the metal surface of the blade from corrosion.
FIG. 2 shows a flow chart of a coating thickness removal method with controllable coating thickness according to one embodiment of the invention.
As shown in fig. 2, the coating thickness removing method sequentially includes the following steps, in which:
In step S10: the number of blowing cycles is determined based on the difference Δt between the thickness of the thinned region 230 and the target thickness and the blowing process parameters. The difference DeltaT is defined as the thickness deviation based on the coating thickness requirement, and is generally greater than or equal to 100um. According to an embodiment of the present invention, the step S10 further includes: the thickness of the coating in the thinned region 230 is measured using a thickness gauge. The coating thickness of the thinned region 230 measured by the thickness gauge is compared with a target thickness, thereby obtaining a difference Δt.
In step S20: and blowing sand to the thinning area 230 based on the number of blowing cycles until a difference between the thickness of the thinning area 230 and the target thickness is less than or equal to a coating removal thickness of a single blowing sand. That is, if the thickness of the thinned area 230 cannot withstand the thickness removal amount of the once-blown sand after the once-blown sand, the once-blown sand should not be performed, and the blowing of the sand should be finished after the last time-blown sand.
In step S30: the coating thickness of the thinned region 230 is processed by polishing to a target thickness. According to one embodiment of the present invention, the coating thickness of the thinned region 230 may be processed by hand sanding to a target thickness. Optionally, the blown thinned area 230 is subjected to a fine smooth sanding process using sandpaper. For example, a 800-1000 mesh sandpaper is used to smooth the surface of the blown sand to remove the coating to the target thickness and desired surface condition of the coating.
According to one embodiment of the present invention, the coating thickness removing method further includes: the full coating thickness region 210 is masked prior to blowing. Optionally, a full coating thickness area 210 on the part or product 100 is masked using tape or a fixture so that the coated surface of the area is protected from the blowing of sand.
According to one embodiment of the present invention, the step S10 includes: the coating removal thickness T of the thinned region 230 for a single shot is determined based on the difference Δt between the thickness of the thinned region 230 and the target thickness and the shot process parameters. Optionally, setting a sand blowing process parameter with reference to the difference Δt, calculating a coating removal thickness T of a single shot through a plurality of controllable sand blowing tests using a sand of a predetermined material, wherein t=10 to 15um. Specifically, a plurality of sand blowing tests are carried out, and angles of two connected sand blowing tests are identical in size and opposite in direction. The coating removal thickness t of a single blow is calculated by calculating the coating removal thickness before and after each blow.
And, the step S10 includes: the number of sand blowing cycles C to the thinned region 230 is calculated, wherein, first, the ratio Δt/T of the difference Δt between the thickness of the thinned region 230 and the target thickness to the coating removal thickness T of the single shot is calculated to obtain an integer or a fraction. When deltaT/T is an integer, taking the integer as the number of times C of sand blowing circulation; when Δt/T is a decimal, the number of blowing cycles C is an integer with the value of Δt/T rounded up, and c=2, 3,4 … …
According to one embodiment of the present invention, the step S20 includes: and (3) blowing the sand to the thinning area 230 according to the thickness t of the coating removed by the single sand blowing, wherein the number of times of sand blowing is C-1. Alternatively, after the end of the multiple blowing, the coating removal thickness may reach a value of 2 Δt/3 to Δt according to the test calculation.
According to an embodiment of the present invention, the step S30 includes: a thickness gauge is used to test whether the coating thickness of the thinned region 230 after the sanding process (e.g., a manual sanding process) meets the requirements. Wherein the thickness meets the requirements that the measured thickness of the coating falls within the thickness tolerance of the thinned region 230, alternatively, the thickness tolerance is 700-800 um for the full coating thickness 210 and 100-150 um for the thinned region 230.
According to one embodiment of the present invention, the coating thickness removing method further includes: metallographic testing whether the thickness of the coating in the thinned region 230 after polishing meets the requirement. Metallographic testing quantitatively checks the coating thickness from a metallographic anatomical perspective, while smoothing (e.g., by hand) such as sanding only serves to assist in smoothing to control the thickness with a small reduction in thickness. The thickness requirement of the thinning area 230 is checked by a thickness gauge and a metallographic test so as to better adjust and control the polishing process to obtain a flat, smooth and high-precision thinning area 230.
According to one embodiment of the invention, the blowing process parameters are set such that the coating removal thickness T of the single blow is positively correlated with the difference Δt between the thickness of the thinned region and the target thickness. For example, if the difference Δt is large, a large coating removal thickness T may be employed as desired, such as by increasing the blowing pressure, decreasing the blowing speed to achieve a high coating removal thickness. Thus, the number of times of sand blowing circulation can be effectively controlled.
According to one embodiment of the invention, the sand material of the preset material is white corundum sand, and the white corundum sand is used for carrying out a plurality of sand blowing tests. The white corundum sand is optionally Al2O3 white corundum sand of F90-F200. The sand blowing process parameters comprise: the mesh number of the white corundum sand, the sand blowing pressure, the spraying distance, the spraying angle and the moving speed of the spray gun. Those skilled in the art will recognize that the variety of the blowing process parameters is not limited thereto, and that some other blowing process parameters may be included during specific operations, and the blowing process parameters of the present embodiment are merely illustrative.
According to one embodiment of the invention, the mesh number of the white corundum sand is 90 or 200 meshes, the sand blowing pressure is 1.5-2.0 bar, the spraying distance is 80-120 mm, the spraying angle is 30-60 degrees, and the manually controlled moving speed of the spray gun is 10-50 mm/s. Alternatively, when the difference Δt is large, a large parameter (e.g., increasing the blowing pressure, decreasing the gun movement speed) is used to achieve a high coating removal thickness T. Those skilled in the art can know that the embodiment only provides the reference experimental sand blowing process parameters for the case that the coating is ceramic, the selection and setting of the sand blowing process parameters are not invariable, and the corresponding adjustment and revision can be made through the sand blowing test according to the single coating removal thickness t, the difference of coating materials, the difference of requirements and the like, so that the best coating removal effect can be realized through controllable multiple sand blowing, and the selection and setting are all within the protection scope of the invention.
The invention provides a coating thickness removing method with controllable coating thickness, which has the following advantages that:
When the gradient coating thickness requirement exists in the component or the product, the thickness of the redundant ceramic coating is removed to the maximum extent by adopting controllable sand blowing, and then the thinned surface after sand blowing is subjected to smoothing treatment, so that the thickness of a thinned area is greatly reduced, the requirement of controllable coating thickness removal is efficiently met, the design requirement of great difference value of the ceramic coating thickness on the same component or the product is successfully met, and the controllable removal of the coating of other similar products meets the thickness requirement of the thinned area and has great reference value;
Greatly saves the man-hour of manual smoothing treatment. The time for smooth polishing by sand paper is reduced to between 30 and 60 minutes for 1.5 to 2 hours; meanwhile, the process limitation that the smoother the manual polishing is, the smaller the removal amount is solved;
According to the controllable coating thickness removing method, controllable sand blowing is introduced, so that the coating thickness after surface treatment is uniform, and the color difference is small.
Finally, it should be noted that the above-mentioned embodiments are only preferred embodiments of the present invention, and not limiting the present invention, and although the present invention has been described in detail with reference to the above-mentioned embodiments, it will be apparent to those skilled in the art that modifications may be made to the technical solutions described in the above-mentioned embodiments, or equivalents may be substituted for some of the technical features thereof. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (12)
1. A coating thickness removal method with controllable coating thickness, characterized in that the coating comprises a full coating thickness region and a thinned region, the full coating thickness region and the thinned region have different coating thicknesses, and the coating thickness removal method sequentially comprises:
s10: determining the number of sand blowing cycles based on the difference delta T between the thickness of the thinned area and the target thickness and the sand blowing process parameters;
S20: blowing sand to the thinning area based on the number of sand blowing cycles until the difference between the thickness of the thinning area and the target thickness is less than or equal to the coating removal thickness of single sand blowing;
s30: the coating thickness of the thinned region is treated by polishing to a target thickness, wherein,
The step S10 includes: and determining the coating removal thickness T of the thinning area by single sand blowing based on the difference delta T between the thickness of the thinning area and the target thickness and the sand blowing technological parameter, and calculating the sand blowing circulation times C of the thinning area, wherein C is an integer obtained by delta T/T or an integer rounded upwards.
2. The coating thickness removal method according to claim 1, further comprising: the full-coat thickness region is masked prior to blowing.
3. The coating thickness removal method according to claim 1, wherein the step S20 includes: and blowing sand to the thinning area according to the coating removal thickness t of the single sand blowing, wherein the sand blowing times are C-1 times.
4. A coating thickness removal method according to claim 3, wherein said step S10 comprises: the thickness of the coating in the thinned region is measured using a thickness gauge.
5. The method of claim 4, wherein the step S30 includes: and testing whether the coating thickness of the polished thinned area meets the requirement of the target thickness by using a thickness gauge.
6. The coating thickness removal method according to claim 5, further comprising: and metallographic testing whether the coating thickness of the thinned area after polishing meets the requirement of the target thickness.
7. The coating thickness removal method according to claim 1, wherein in the step S30, the coating thickness of the thinned region is processed by hand sanding up to a target thickness.
8. The coating thickness removal method according to claim 1, wherein the step S10 includes: setting sand blowing technological parameters, performing multiple sand blowing tests by using sand materials of preset materials, and carrying out average calculation on the coating removal thickness before and after each sand blowing to obtain the coating removal thickness t of the single sand blowing.
9. The coating thickness removal method of claim 8, wherein the blowing process parameters are set such that the single blow coating removal thickness T is positively correlated with the difference Δt between the thickness of the thinned region and the target thickness.
10. The coating thickness removal method according to claim 8, wherein the sand material of the predetermined material is white corundum sand, and the blowing process parameters include: the mesh number of the white corundum sand, the sand blowing pressure, the spraying distance, the spraying angle and the moving speed of the spray gun.
11. The method for removing a coating thickness according to claim 10, wherein the white corundum sand has a mesh size of 90 or 200 mesh, a blowing pressure of 1.5 to 2.0bar, a spraying distance of 80 to 120mm, a spraying angle of 30 to 60 °, and a spray gun moving speed of 10 to 50mm/s.
12. The coating thickness removal method of any one of claims 1 to 11, wherein the coating further comprises a transition region, wherein the transition region connects the full-thickness region and the thinned region, and wherein the coating thickness of the transition region is between the coating thickness of the full-thickness region and the coating thickness of the thinned region.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210884179.6A CN115122243B (en) | 2022-07-25 | 2022-07-25 | Coating thickness removal method with controllable coating thickness |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210884179.6A CN115122243B (en) | 2022-07-25 | 2022-07-25 | Coating thickness removal method with controllable coating thickness |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115122243A CN115122243A (en) | 2022-09-30 |
| CN115122243B true CN115122243B (en) | 2024-04-30 |
Family
ID=83385608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210884179.6A Active CN115122243B (en) | 2022-07-25 | 2022-07-25 | Coating thickness removal method with controllable coating thickness |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115122243B (en) |
Citations (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06344160A (en) * | 1993-06-04 | 1994-12-20 | Xerox Corp | Method of reducing thickness of film by laser beam machining |
| CN101745604A (en) * | 2008-12-10 | 2010-06-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Technical method for removing burnt-on sand in groove of ceramic core |
| WO2010083658A1 (en) * | 2009-01-24 | 2010-07-29 | 西门子公司 | Method reducing recrystallization of surface of ni-base superalloy and production thereof |
| CN102787290A (en) * | 2012-06-19 | 2012-11-21 | 中国航空工业集团公司北京航空材料研究院 | Preparation method of high-temperature abradable sealing coating |
| CN103170746A (en) * | 2011-12-26 | 2013-06-26 | 富泰华工业（深圳）有限公司 | Coating removing device and coating removing method thereof |
| CN106269632A (en) * | 2016-08-10 | 2017-01-04 | 中国人民解放军第五七九工厂 | A kind of minimizing technology of aerial motor spare part coating |
| CN107620026A (en) * | 2016-07-14 | 2018-01-23 | 沈阳黎明国际动力工业有限公司 | A kind of HVAF technique of pure alumina coating |
| CN107876355A (en) * | 2017-11-09 | 2018-04-06 | 中国航发湖南动力机械研究所 | The optimize technique of strain gauge installation method |
| CN207372989U (en) * | 2017-11-09 | 2018-05-18 | 上海凯奔航空技术有限公司 | A kind of aircraft wheel hub automatic sand-aerating machine |
| CN108333105A (en) * | 2018-04-03 | 2018-07-27 | 中铁山桥集团有限公司 | A kind of coating anti-slipping property energy method of inspection for steel bridge high-strength bolt joint face |
| CN207771610U (en) * | 2017-12-18 | 2018-08-28 | 中国航发贵州黎阳航空动力有限公司 | A kind of double angle automation sand-aerating apparatus |
| CN109175368A (en) * | 2018-10-29 | 2019-01-11 | 首都航天机械有限公司 | A kind of cleaning method of selective laser fusing forming alloy complex inner cavity |
| CN109317377A (en) * | 2018-11-22 | 2019-02-12 | 中国航发沈阳黎明航空发动机有限责任公司 | The compatible coating coating of low temperature multiband and repair method in engine tail nozzle part |
| CN109722618A (en) * | 2017-10-26 | 2019-05-07 | 沈阳黎明国际动力工业有限公司 | A kind of supersonic flame spraying technique of cobalt chromium tungsten wear-resistant coating |
| CN110340286A (en) * | 2019-07-16 | 2019-10-18 | 中国航发北京航空材料研究院 | A kind of preparation method of high surface finish titanium investment precision casting |
| CN110735145A (en) * | 2019-11-28 | 2020-01-31 | 中国航发沈阳黎明航空发动机有限责任公司 | method for removing NiCrAlYSi/YSZ thermal barrier coating of high-pressure turbine blade |
| CN111188004A (en) * | 2018-11-15 | 2020-05-22 | 沈阳黎明国际动力工业有限公司 | Process method for repairing flap slide rail abrasion by supersonic spraying |
| CN111250368A (en) * | 2018-11-15 | 2020-06-09 | 沈阳黎明国际动力工业有限公司 | Preparation process of polyphenyl ester sealing coating for aero-engine case parts |
| CN112496870A (en) * | 2020-11-25 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for pretreating surface of substrate before high-speed jet flow additive repair |
| CN112536724A (en) * | 2020-11-09 | 2021-03-23 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic sand blowing process method for adjustable blade |
| WO2021114068A1 (en) * | 2019-12-10 | 2021-06-17 | 中国航发贵州黎阳航空动力有限公司 | Preparation method for tin coating on titanium alloy part of aircraft engine |
| CN113102206A (en) * | 2021-04-12 | 2021-07-13 | 西门子燃气轮机部件(江苏)有限公司 | Ceramic coating spraying method, device and computer readable medium |
| CN113211325A (en) * | 2021-05-07 | 2021-08-06 | 包头市威丰稀土电磁材料股份有限公司 | Method for preparing non-bottom-layer raw material of oriented silicon steel thin strip in physical sand blasting mode |
| CN113458978A (en) * | 2021-05-27 | 2021-10-01 | 中国航发南方工业有限公司 | Method for repairing sealing coating on inner surface of deep hole structure part |
| CN113756831A (en) * | 2021-09-15 | 2021-12-07 | 中国二十二冶集团有限公司 | Construction method for sand blowing and filling between main pipeline and sleeve |
| CN113957378A (en) * | 2021-10-22 | 2022-01-21 | 中国航发贵州黎阳航空动力有限公司 | Coating repair method for turbine blade |
| CN114318322A (en) * | 2021-10-27 | 2022-04-12 | 中国航发贵州黎阳航空动力有限公司 | Spraying method of NiCrAlY oxidation resistant coating for turbine blade |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1219728A1 (en) * | 2000-12-27 | 2002-07-03 | Siemens Aktiengesellschaft | Process for stripping a turbine blade |
-
2022
- 2022-07-25 CN CN202210884179.6A patent/CN115122243B/en active Active
Patent Citations (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06344160A (en) * | 1993-06-04 | 1994-12-20 | Xerox Corp | Method of reducing thickness of film by laser beam machining |
| CN101745604A (en) * | 2008-12-10 | 2010-06-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Technical method for removing burnt-on sand in groove of ceramic core |
| WO2010083658A1 (en) * | 2009-01-24 | 2010-07-29 | 西门子公司 | Method reducing recrystallization of surface of ni-base superalloy and production thereof |
| CN103170746A (en) * | 2011-12-26 | 2013-06-26 | 富泰华工业（深圳）有限公司 | Coating removing device and coating removing method thereof |
| CN102787290A (en) * | 2012-06-19 | 2012-11-21 | 中国航空工业集团公司北京航空材料研究院 | Preparation method of high-temperature abradable sealing coating |
| CN107620026A (en) * | 2016-07-14 | 2018-01-23 | 沈阳黎明国际动力工业有限公司 | A kind of HVAF technique of pure alumina coating |
| CN106269632A (en) * | 2016-08-10 | 2017-01-04 | 中国人民解放军第五七九工厂 | A kind of minimizing technology of aerial motor spare part coating |
| CN109722618A (en) * | 2017-10-26 | 2019-05-07 | 沈阳黎明国际动力工业有限公司 | A kind of supersonic flame spraying technique of cobalt chromium tungsten wear-resistant coating |
| CN107876355A (en) * | 2017-11-09 | 2018-04-06 | 中国航发湖南动力机械研究所 | The optimize technique of strain gauge installation method |
| CN207372989U (en) * | 2017-11-09 | 2018-05-18 | 上海凯奔航空技术有限公司 | A kind of aircraft wheel hub automatic sand-aerating machine |
| CN207771610U (en) * | 2017-12-18 | 2018-08-28 | 中国航发贵州黎阳航空动力有限公司 | A kind of double angle automation sand-aerating apparatus |
| CN108333105A (en) * | 2018-04-03 | 2018-07-27 | 中铁山桥集团有限公司 | A kind of coating anti-slipping property energy method of inspection for steel bridge high-strength bolt joint face |
| CN109175368A (en) * | 2018-10-29 | 2019-01-11 | 首都航天机械有限公司 | A kind of cleaning method of selective laser fusing forming alloy complex inner cavity |
| CN111188004A (en) * | 2018-11-15 | 2020-05-22 | 沈阳黎明国际动力工业有限公司 | Process method for repairing flap slide rail abrasion by supersonic spraying |
| CN111250368A (en) * | 2018-11-15 | 2020-06-09 | 沈阳黎明国际动力工业有限公司 | Preparation process of polyphenyl ester sealing coating for aero-engine case parts |
| CN109317377A (en) * | 2018-11-22 | 2019-02-12 | 中国航发沈阳黎明航空发动机有限责任公司 | The compatible coating coating of low temperature multiband and repair method in engine tail nozzle part |
| CN110340286A (en) * | 2019-07-16 | 2019-10-18 | 中国航发北京航空材料研究院 | A kind of preparation method of high surface finish titanium investment precision casting |
| CN110735145A (en) * | 2019-11-28 | 2020-01-31 | 中国航发沈阳黎明航空发动机有限责任公司 | method for removing NiCrAlYSi/YSZ thermal barrier coating of high-pressure turbine blade |
| WO2021114068A1 (en) * | 2019-12-10 | 2021-06-17 | 中国航发贵州黎阳航空动力有限公司 | Preparation method for tin coating on titanium alloy part of aircraft engine |
| CN112536724A (en) * | 2020-11-09 | 2021-03-23 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic sand blowing process method for adjustable blade |
| CN112496870A (en) * | 2020-11-25 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for pretreating surface of substrate before high-speed jet flow additive repair |
| CN113102206A (en) * | 2021-04-12 | 2021-07-13 | 西门子燃气轮机部件(江苏)有限公司 | Ceramic coating spraying method, device and computer readable medium |
| CN113211325A (en) * | 2021-05-07 | 2021-08-06 | 包头市威丰稀土电磁材料股份有限公司 | Method for preparing non-bottom-layer raw material of oriented silicon steel thin strip in physical sand blasting mode |
| CN113458978A (en) * | 2021-05-27 | 2021-10-01 | 中国航发南方工业有限公司 | Method for repairing sealing coating on inner surface of deep hole structure part |
| CN113756831A (en) * | 2021-09-15 | 2021-12-07 | 中国二十二冶集团有限公司 | Construction method for sand blowing and filling between main pipeline and sleeve |
| CN113957378A (en) * | 2021-10-22 | 2022-01-21 | 中国航发贵州黎阳航空动力有限公司 | Coating repair method for turbine blade |
| CN114318322A (en) * | 2021-10-27 | 2022-04-12 | 中国航发贵州黎阳航空动力有限公司 | Spraying method of NiCrAlY oxidation resistant coating for turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115122243A (en) | 2022-09-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Beaucamp et al. | Finishing of additively manufactured titanium alloy by shape adaptive grinding (SAG) | |
| EP1345732B1 (en) | Method for smoothing the surface of a gas turbine blade | |
| EP3053702B1 (en) | Turbine blade tip repair | |
| CN101219528B (en) | Water jet stripping and recontouring of gas turbine buckets and blades | |
| EP0761386A1 (en) | Method of removing excess overlay coating from within cooling holes of aluminide coated gas turbine engine components | |
| CA2615620A1 (en) | Method and apparatus for increasing fatigue notch capability of airfoils | |
| US20110182499A1 (en) | Method for determining the surface coverage obtained by shot peening | |
| US20100269593A1 (en) | Process for producing a body provided with a slot as a test crack | |
| US7097540B1 (en) | Methods and apparatus for machining formed parts to obtain a desired profile | |
| KR20070115592A (en) | Law plasticity burnishing of coated titanium parts | |
| EP1354977A2 (en) | Method for repairing turbine engine components | |
| CN101772592B (en) | Process for producing metal member, structure member with thus produced metal member, and method of repairing metal member | |
| Hlaváč et al. | Shape distortion reduction method for abrasive water jet (AWJ) cutting | |
| CN106599406A (en) | Blade edge mechanical forming process method | |
| TWI572733B (en) | Partial spray refurbishment of sputtering targets | |
| CN115122243B (en) | Coating thickness removal method with controllable coating thickness | |
| EP0492323A2 (en) | Method for the surface-treatment of parts | |
| CN113366158A (en) | Cobalt chromium etching process | |
| US6568239B1 (en) | Test strip and method for confirming shot peening coverage | |
| Wildgoose et al. | Impacts of the Additive Manufacturing Process on the Roughness of Engine Scale Vanes and Cooling Channels | |
| CN110587485B (en) | Grinding and polishing contact force real-time planning method and system | |
| CN111922922A (en) | Shot peening strengthening deformation regulating and controlling method for large-curvature biconvex integral wall plate with ribs | |
| US6714900B1 (en) | Method for generating a shell mold for a casting | |
| CN114473213B (en) | Laser polishing method for tungsten carbide-based composite coating | |
| RU2607867C2 (en) | Adaptive treatment of cast blades |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 214203 No. 25 Huixing North Road, Yixing Economic and Technological Development Zone, Wuxi City, Jiangsu Province Applicant after: Siemens Energy Gas Turbine Components (Jiangsu) Co.,Ltd. Address before: 214203 No. 25 Huixing North Road, Yixing Economic and Technological Development Zone, Wuxi City, Jiangsu Province Applicant before: Siemens Gas Turbine Components (Jiangsu) Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant |