CN117604463A - Coating device and coating method for turbine blade - Google Patents
Coating device and coating method for turbine blade Download PDFInfo
- Publication number
- CN117604463A CN117604463A CN202311705335.9A CN202311705335A CN117604463A CN 117604463 A CN117604463 A CN 117604463A CN 202311705335 A CN202311705335 A CN 202311705335A CN 117604463 A CN117604463 A CN 117604463A
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- edge plate
- protection box
- crankshaft
- guide
- plate protection
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- 238000000576 coating method Methods 0.000 title claims abstract description 53
- 239000011248 coating agent Substances 0.000 title claims abstract description 46
- 230000008021 deposition Effects 0.000 claims abstract description 30
- 239000000919 ceramic Substances 0.000 claims abstract description 17
- 238000001704 evaporation Methods 0.000 claims abstract description 11
- 230000008020 evaporation Effects 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 claims description 18
- 230000008569 process Effects 0.000 claims description 17
- 238000005507 spraying Methods 0.000 claims description 4
- 238000005137 deposition process Methods 0.000 abstract description 5
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 238000000151 deposition Methods 0.000 description 24
- 238000005240 physical vapour deposition Methods 0.000 description 7
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 6
- 239000012720 thermal barrier coating Substances 0.000 description 6
- 229910010293 ceramic material Inorganic materials 0.000 description 4
- 239000013078 crystal Substances 0.000 description 4
- 230000001012 protector Effects 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 239000000956 alloy Substances 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 229910052786 argon Inorganic materials 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000004576 sand Substances 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000007664 blowing Methods 0.000 description 2
- 239000011247 coating layer Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005328 electron beam physical vapour deposition Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 238000007740 vapor deposition Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/28—Vacuum evaporation by wave energy or particle radiation
- C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/50—Substrate holders
- C23C14/505—Substrate holders for rotation of the substrates
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/54—Controlling or regulating the coating process
- C23C14/541—Heating or cooling of the substrates
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/54—Controlling or regulating the coating process
- C23C14/542—Controlling the film thickness or evaporation rate
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a coating device and a coating method for turbine blades, wherein the coating device comprises a first edge plate protection box and a second edge plate protection box, and guide blades are clamped between the first edge plate protection box and the second edge plate protection box; the end face, far away from the guide blade, of the first edge plate protection box is connected with an elastic connecting rod assembly, and the elastic connecting rod assembly is connected with a rotating shaft; the end face, far away from the guide blade, of the second edge plate protection box is connected with a crankshaft, the outer contour of the crankshaft is abutted against an elastic thimble assembly, and the elastic thimble assembly is fixed in the deposition chamber; the outer contour of the crankshaft comprises a protruding part and a groove part, and when the crankshaft rotates along with the rotating shaft, the two ends of the guide vane incline at different angles; ceramic ingots are arranged below the guide blades, and an evaporation gun and a preheating gun are arranged in the deposition chamber. The guide vane realizes multi-degree-of-freedom rotation in the coating deposition process, the inner surface of the left edge plate, the inner surface of the right edge plate and the outer surface of the vane body of the guide vane can be uniformly coated, the edge plate of the vane is heated uniformly, and the service life of the coating of the edge plate of the vane is prolonged.
Description
Technical Field
The invention belongs to the technical field of aviation turbine blade spraying, and relates to a coating device and a coating method for turbine blades.
Background
As modern aircraft engines have higher thrust to weight ratios, the engine turbine component operating temperatures will be higher and the high pressure turbine blades will be used at higher temperatures. At present, domestic and foreign researches show that the service temperature and service life of the hot end part of the engine can be remarkably improved by coating a layer of thermal barrier coating on the outer surface of the high-temperature alloy turbine blade. The thermal barrier coating prepared by the electron beam-physical vapor deposition technology (EB-PVD for short) has a typical columnar crystal structure and higher strain tolerance and erosion resistance, so that the thermal barrier coating is widely applied to high-performance aeroengine turbine blades and becomes an essential technology for preparing the thermal barrier coating of the aeroengine turbine blades.
Referring to FIG. 1, the existing deposition principle for EB-PVD equipment is: the guide vane 107 to be coated is installed between the vane large-edge plate outer surface protection box 108 and the vane small-edge plate outer surface protection box 109, the installed guide vane 107 is clamped on the equipment rotating shaft 102 in the equipment loading chamber 101, the equipment rotating shaft 102 is driven to move and continuously rotate through the equipment motor, so that the guide vane 107 is driven to move to the equipment deposition chamber 103 in the horizontal direction, and the movement is stopped when the guide vane is positioned right above the ceramic ingot 104. Starting a high-pressure device of the equipment, releasing a light spot by a preheating gun 106 to preheat a continuously rotating guide blade 107 to a process temperature, releasing a high-intensity light spot by an evaporating gun 105 to bombard a ceramic material ingot 104 to generate a material ingot steam block 110, vertically rising the ceramic material ingot steam block 110, and forming a columnar crystal thermal barrier coating on the outer surface of the continuously rotating guide blade 107.
Under the traditional tooling system, the EB-PVD coating equipment can realize continuous rotation of the blade body, and the blade body and the ceramic material ingot steam clusters form a vertical angle, so that the outer surface of the blade body can obtain typical columnar crystal structures, and the heat-resistant temperature of the blade can be effectively improved. The included angle between the surface of the blade edge plate and the ceramic steam cluster is smaller, the blade edge plate is basically in a parallel state, the EB-PVD technology has a linear illumination effect, the coating on the surface of the edge plate parallel to the direction of the ceramic steam cluster forms a cluster-shaped structure, and the thickness and the quality of the coating on the edge plate are poor, so that the coating on the edge plate is peeled off early in the thermal shock examination and test run processes.
Disclosure of Invention
The invention aims to solve the problems of poor thickness and poor coating quality of a coating layer of a flange plate at two ends of a blade and poor uniformity in the prior art, and the coating layer of the flange plate is peeled off too early in the thermal shock examination and test process.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme:
a coating apparatus for a turbine blade, comprising a first and a second platform protection box, the first and second platform protection boxes sandwiching a guide blade;
the end face, far away from the guide blade, of the first edge plate protection box is connected with an elastic connecting rod assembly, and the elastic connecting rod assembly is connected with a rotating shaft;
the end face, far away from the guide blade, of the second edge plate protection box is connected with a crankshaft, the outer contour of the crankshaft is abutted against an elastic thimble assembly, and the elastic thimble assembly is fixed in the deposition chamber;
the outer contour of the crankshaft comprises a protruding part and a groove part, and when the crankshaft rotates along with the rotating shaft, the guide blades incline at different angles;
ceramic ingots are arranged below the guide blades, and an evaporation gun and a preheating gun are arranged in the deposition chamber.
The invention further improves that:
the protruding portions and the groove portions are circumferentially spaced along the outer contour of the crankshaft.
The joint of any convex part and the adjacent concave groove part is in smooth transition.
The outer surfaces of the protruding part and the groove part are cambered surfaces.
The elastic connecting rod assembly comprises a connecting rod, the connecting rod is connected with the rotating shaft, and one end, far away from the rotating shaft, of the connecting rod is connected with a first spring;
the first spring is connected with the end face of the first edge plate protection box, which is far away from the guide blade.
The first spring is welded with the first edge plate protection box.
The elastic thimble assembly comprises a thimble, and the thimble is abutted with the outer contour of the crankshaft;
the end part of the thimble, which is far away from the crankshaft, is connected with a second spring;
the second spring is fixed in the deposition chamber.
The second spring and the thimble are axially arranged in the thimble barrel, and the thimble can axially move along the thimble barrel;
the thimble barrel is connected with a screw rod, and the screw rod is fixed in the deposition chamber.
The upper end and the lower end of the screw rod are connected with the top and the bottom of the deposition chamber through positioning nuts.
A coating method for a turbine blade, comprising the steps of:
connecting two ends of the guide blade with a first edge plate protection box and a second edge plate protection box respectively;
the first edge plate protection box is sequentially connected with the elastic connecting rod assembly and the rotating shaft, and the second edge plate protection box is connected with the crankshaft;
the rotating shaft advances into the deposition chamber, when the crankshaft contacts with the elastic thimble assembly, the advancing is stopped, and when the rotating shaft rotates, the protruding part and the groove part alternately contact with the elastic thimble assembly;
when the bulge part is contacted with the elastic thimble assembly, the end part of the guide blade, which is close to the elastic thimble assembly, is inclined upwards, and when the groove part is contacted with the elastic thimble assembly, the end part of the guide blade, which is close to the elastic connecting rod assembly, is inclined upwards, and the two ends of the guide blade are repeatedly inclined upwards and downwards in circumferential rotation, so that the rotation with multiple degrees of freedom is generated;
in the rotation process of the guide vane, the evaporation gun, the preheating gun and the ceramic ingot are started to finish spraying.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a coating device for turbine blades, wherein an elastic connecting rod assembly and an elastic thimble assembly are respectively added at two sides of a first edge plate protection box and a second edge plate protection box, a crankshaft is added at the end face of the second edge plate protection box, in the rotating process of a rotating shaft, as the outer contour of the crankshaft comprises a protruding part and a groove part, the outer contour of the crankshaft has a height difference, in the rotating process, the angle between a guide blade and the rotating shaft is always in an inclined state, when different positions of the crankshaft are contacted with the elastic thimble assembly, the guide blade is inclined to different degrees, when the protruding part is contacted with the elastic thimble assembly, the end part of the guide blade, which is close to the elastic thimble assembly, is inclined upwards, when the groove part is contacted with the elastic thimble assembly, the end part of the guide blade is inclined upwards, so that the guide blade can be inclined up and down repeatedly in the circumferential rotation, in the inclined process, the inner side walls of two surfaces of the guide blade can form a certain included angle with steam groups generated by a ceramic ingot at the bottom, in the continuous rotation, the guide blade can realize the deposition process of multiple degrees, the left surface of the guide blade, the inner surface of the guide blade body and the inner surface of the blade body of the blade can be coated with the surface of the left edge plate and the inner surface of the blade can be uniformly coated, and the surface of the guide blade can be coated, and the surface of the left edge blade can be coated, and the surface of the surface can be coated, and the surface can be coated uniformly, and the surface can be coated, and the heated.
Furthermore, in the invention, the joint of any convex part and the adjacent concave groove part is in smooth transition, so that the uniformity and transition of angles in the angle rotation process are ensured, and the spray uniformity is further improved.
Furthermore, in the invention, the outer surfaces of the convex part and the groove part are cambered surfaces, so that the multi-degree-of-freedom rotation process can be uniformly transited all the time, and the spraying uniformity is ensured.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a prior EB-PVD equipment deposition coating apparatus;
FIG. 2 is a schematic diagram of an EB-PVD deposition coating apparatus with multiple degrees of freedom rotation according to the present invention;
FIG. 3 is a schematic cross-sectional view of a crankshaft of the present invention;
FIG. 4 is a schematic view of a thimble barrel according to the present invention;
FIG. 5 is a schematic view of a thimble according to the present invention;
FIG. 6 is a view of the coating texture at the trailing edge plate of the prior art device deposited coating;
FIG. 7 shows the structure of the coating at the edge plate after the deposition of the coating by the device of the present invention.
The device comprises a device loading chamber 101, a device rotating shaft 102, a device depositing chamber 103, a material ingot crucible 104, an evaporation gun 105, a preheating gun 106, a guide blade to be coated 107, a guide blade large flange plate outer surface protection box 108, a blade small flange plate outer surface protection box 109 and a material ingot steam block 110;
wherein: 1-a rotating shaft; 2-connecting rods; 3-a first spring; 4-a first edge plate protection box; 5-a second flange plate protection box; 6-a crankshaft; 7-thimble; 8-a thimble barrel; 9-a second spring; 10-screw rod; 11-positioning a nut; 12-a deposition chamber; 13-an evaporation gun; 14-preheating a gun; 15-ceramic material ingot; 16-guide vanes; 17-a boss; 18-groove portion.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the embodiments of the present invention, it should be noted that, if the terms "upper," "lower," "horizontal," "inner," and the like indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, or the azimuth or the positional relationship in which the inventive product is conventionally put in use, it is merely for convenience of describing the present invention and simplifying the description, and does not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the term "horizontal" if present does not mean that the component is required to be absolutely horizontal, but may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between 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.
The invention is described in further detail below with reference to the attached drawing figures:
referring to fig. 2, an embodiment of the present invention discloses a coating apparatus for a turbine blade, including a first platform protector 4 and a second platform protector 5, wherein the first platform protector 4 and the second platform protector 5 sandwich a guide blade 16; the end face, far away from the guide blade 16, of the first edge plate protection box 4 is connected with an elastic connecting rod assembly, and the elastic connecting rod assembly is connected with the rotating shaft 1; the end face, far away from the guide blade 16, of the second edge plate protection box 5 is connected with the crankshaft 6, the outer contour of the crankshaft 6 is abutted against an elastic thimble assembly, and the elastic thimble assembly is fixed in the deposition chamber 12; the outer contour of the crankshaft 6 comprises a protruding part 17 and a groove part 18, and when the crankshaft 6 rotates along with the rotating shaft 1, the two ends of the guide vane 16 incline at different angles; ceramic ingots 15 are arranged below the guide blades 16, and an evaporation gun 13 and a preheating gun 14 are arranged in the deposition chamber 12.
Referring to fig. 3, further, in the embodiment of the present invention, the protruding portions 17 and the groove portions 18 are circumferentially spaced along the outer contour of the crankshaft 6, the connection between any one of the protruding portions 17 and the adjacent groove portion 18 is in smooth transition, and the outer surfaces of the protruding portions 17 and the groove portion 18 are all cambered surfaces, so that the angle is uniform and excessive in the angular rotation process, and the spray uniformity is further improved.
Further, in the embodiment of the invention, the elastic connecting rod assembly comprises a connecting rod 2, the connecting rod 2 is connected with the rotating shaft 1 through a bolt, one end of the connecting rod 2, which is far away from the rotating shaft 1, is welded with one end of a first spring 3, the other end of the first spring 3 is welded with a first edge plate protection box 4, and the first spring 3 is connected with the connecting rod 2 and the first edge plate protection box 4 through argon arc welding.
Further, in the embodiment of the invention, the first edge plate protection box 4 and the second edge plate protection box 5 are fixed with the guide vane 16 through high-temperature alloy wires, and the crankshaft 6 is fixed on the end face of the second edge plate protection box 5, which is far away from the guide vane 16, through argon arc welding.
Referring to fig. 4 to 5, in a further embodiment of the present invention, the elastic thimble assembly includes a second spring 9 and a thimble 7 that are axially connected, where the second spring 9 is fixed inside the thimble barrel 8, the inside of the thimble barrel 8 includes two communicating chambers, the thimble barrel 8 is fixed in the first chamber, the thimble 7 is located in the first chamber and is abutted with the second spring 9, the other end extends out of the thimble barrel 8 after penetrating through the second chamber, a structure located outside the thimble barrel 8 is connected with the crankshaft 6, and an end portion of the thimble 7 located in the first chamber is clamped at a joint between the first chamber and the second chamber, so that the thimble 7 always moves along the second chamber under the action of the second spring 9.
Further, the thimble barrel 8 is welded on the screw 10, and the screw 10 is connected with the top and bottom of the deposition chamber 12 through the positioning nuts 11 at the upper end and the lower end.
In this embodiment, the rotating shaft 1 drives the rotating shaft 1 to continuously rotate until the rotating shaft 6 is pushed into the deposition chamber 12, when the crankshaft 6 moves until the rotating shaft contacts the thimble 7, at this time, the thimble 7 is driven by the elastic force of the second spring 9, the contact surface between the thimble 7 and the crankshaft 6 increases, when the highest point a of the crankshaft 6 (i.e. the highest point of the protruding portion 17) contacts the thimble 7, the guiding vane 16 is driven to continuously rotate while the second flange protection box 5 is inclined upwards due to the height difference of the crankshaft 6, a certain included angle is formed between the inner surface of the left flange plate of the guiding vane 16 and the steam mass generated by the ceramic ingot 15, and when the lowest point b of the crankshaft 6 (i.e. the lowest point of the groove portion 18) contacts the thimble 7, the second flange protection box 5 is inclined downwards, and the inner surface of the right flange plate of the guiding vane 16 forms a certain included angle with the steam mass generated by the ceramic ingot 15, and the guiding vane is driven by continuously repeating the height difference of the crankshaft 6, so that the multi-degree of freedom rotation of the guiding vane is realized in the coating deposition process.
The inner surface of the right edge plate of the guide vane 16 and the inner surface of the left edge plate of the guide vane 16 described in this embodiment are both left and right sides distinguished based on the view angle in fig. 1.
The embodiment also discloses a coating method for the turbine blade, which is designed according to the structural characteristics of the EB-PVD equipment and the coating deposition principle, and can realize multi-degree-of-freedom rotation of the blade.
The method comprises the following specific steps:
step 1, blowing sand and cleaning:
the gas flow path surface of the guide vane 16 is activated by adopting a sand blowing process, and the guide vane 16 and the device are cleaned by using a cleaning agent, so that the influence of residual sand and external pollutants on the coating structure and the binding force is avoided.
Step 2, fixing a positioning screw rod and a thimble barrel device:
before the coating is deposited, a deposition chamber 12 is opened, a screw rod 10 is supported in the deposition chamber 12 through a positioning nut 11, the screw rod 10 is ensured to be stable and firm, an assembled thimble 7, a second spring 9 and a thimble barrel 8 are welded on the positioning screw rod 10 through argon arc welding, and the welding height of the thimble barrel 8 is determined through early process test data.
Step 3, clamping the blade:
firstly, a guide blade 16 to be processed is arranged between a first edge plate protection box 4 and a second edge plate protection box 5, the guide blade 16 is firmly fixed by utilizing a high-temperature alloy wire, the first spring 3 is fixed by the first edge plate protection box 4, the first spring 3 is connected with a connecting rod 2, and the connecting rod 2 is firmly fixed with a rotating shaft 1 through a bolt.
Step 4, in the concrete process of the thermal barrier coating:
charging: after the device with the guide blades 16 is connected with the rotating shaft 1, the rotating device of the equipment is started, and whether the rotation of the device is normal or not is checked;
delivering the blade: after the guide vane 16 is sent into the deposition chamber 12 through the rotating shaft 1, the crankshaft 6 is contacted with the thimble 7, the thimble 7 is driven by the elastic force of the second spring 9, the contact surface between the thimble 7 and the crankshaft 6 is increased, when the crankshaft 6 continuously rotates, the guide vane 16 is driven to continuously rotate and simultaneously repeatedly incline up and down due to the height difference between the protruding part 17 and the groove part 18 in the outer contour of the crankshaft 6, and the guide vane 16 realizes multi-degree-of-freedom rotation in the coating deposition process.
Vacuumizing: the deposition chamber 12 is evacuated and after reaching the process requirements, the guide vanes 16 are heated, and after reaching the process temperature, evaporation of the ceramic crucible 15 is started and deposition of the coating is started.
And (3) depositing a coating: driven by the device, the first edge plate protection box 4 and the second edge plate protection box 5 of the guide vane 16 are inclined downwards repeatedly, the guide vane 16 continuously rotates, the guide vane 16 realizes multi-degree-of-freedom rotation in the coating deposition process, ceramic ingots 15 can be uniformly coated on the inner surfaces of the left edge plate, the right edge plate and the outer surface of the blade body of the guide vane 16 in the form of gas-phase steam clusters, and the thickness of the coating is controlled by controlling the time for evaporating the ceramic ingots and the consumption of the ceramic ingots.
And (3) cooling: the device is withdrawn to the loading chamber, when the parts are vacuum cooled to below 300 ℃, air is filled into the loading chamber, the oven door is opened, the device is taken out and disassembled, the coating of the outer surface of the blade body and the inner surface of the edge plate is fully coated, and the non-coating areas of the outer side of the left edge plate and the outer side of the right edge plate are effectively protected to form the guide vane 16.
The device has simple structure, realizes the multi-degree-of-freedom rotation of the blade through the interaction of the positioning rod and the crankshaft and the driving of the equipment rotating shaft in the device in the use process, thereby improving the coating structure of the blade edge plate.
The coated tissue of the blade edge region of the guide vane 16 was examined and the examination result is shown in FIG. 6. Compared with the coating structure of the flange coated by the vapor deposition traditional coating device in FIG. 7, the ceramic surface layer of the flange part in FIG. 6 has a typical columnar crystal structure, and the coating structure is obviously improved.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. 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 (10)
1. Coating device for a turbine blade, characterized by comprising a first and a second rim plate protection box (4, 5), the first and second rim plate protection boxes (4, 5) sandwiching a guide blade (16);
the end face, far away from the guide blade (16), of the first edge plate protection box (4) is connected with an elastic connecting rod assembly, and the elastic connecting rod assembly is connected with a rotating shaft (1);
the end face, far away from the guide blade (16), of the second edge plate protection box (5) is connected with a crankshaft (6), the outer contour of the crankshaft (6) is abutted against an elastic thimble assembly, and the elastic thimble assembly is fixed in the deposition chamber (12);
the outer contour of the crankshaft (6) comprises a protruding part (17) and a groove part (18), and when the crankshaft (6) rotates along with the rotating shaft (1), the guide blades (16) incline at different angles;
ceramic ingots (15) are arranged below the guide blades (16), and an evaporation gun (13) and a preheating gun (14) are arranged in the deposition chamber (12).
2. A coating device for a turbine blade according to claim 1, characterized in that the raised portions (17) and the recessed portions (18) are circumferentially spaced along the outer contour of the crankshaft (6).
3. A coating device for a turbine blade according to claim 2, characterized in that the junction of any one of the projections (17) with an adjacent recess (18) is smoothly transitioned.
4. A coating device for a turbine blade according to claim 1, characterized in that the outer surfaces of the raised portion (17) and the recessed portion (18) are cambered surfaces.
5. A coating device for a turbine blade according to claim 1, characterized in that the elastic linkage assembly comprises a linkage (2), the linkage (2) being connected to the shaft (1), the end of the linkage (2) remote from the shaft (1) being connected to a first spring (3);
the first spring (3) is connected with the end face of the first edge plate protection box (4) far away from the guide blade (16).
6. A coating device for a turbine blade according to claim 5, characterized in that the first spring (3) is welded to the first flange plate protection box (4).
7. A coating apparatus for a turbine blade according to claim 1, characterized in that said elastic thimble assembly comprises a thimble (7), said thimble (7) being in abutment with the outer contour of the crankshaft (6);
the end part of the thimble (7) far away from the crankshaft (6) is connected with a second spring (9);
the second spring (9) is fixed in the deposition chamber (12).
8. A coating device for turbine blades according to claim 6, characterized in that the second spring (9) and the ejector pin (7) are axially arranged in an ejector pin barrel (8), the ejector pin (7) being axially movable along the ejector pin barrel (8);
the thimble barrel (8) is connected with a screw rod (10), and the screw rod (10) is fixed in the deposition chamber (12).
9. A coating device for turbine blades according to claim 8, characterized in that the upper and lower ends of the screw (10) are connected to the top and bottom of the deposition chamber (12) by means of a positioning nut (11).
10. A coating method for a turbine blade, comprising the steps of:
two ends of the guide blade (16) are respectively connected with the first edge plate protection box (4) and the second edge plate protection box (5);
the first edge plate protection box (4) is sequentially connected with the elastic connecting rod assembly and the rotating shaft (1), and the second edge plate protection box (5) is connected with the crankshaft (6);
the rotating shaft (1) is pushed into the deposition chamber (12), when the crankshaft (6) is in contact with the elastic thimble assembly, pushing is stopped, and when the rotating shaft (1) rotates, the protruding part (17) and the groove part (18) are alternately in contact with the elastic thimble assembly;
when the bulge (17) is in contact with the elastic thimble assembly, the end part of the guide vane (16) close to the elastic thimble assembly is inclined upwards, and when the groove part (18) is in contact with the elastic thimble assembly, the end part of the guide vane (16) close to the elastic connecting rod assembly is inclined upwards, and the two ends of the guide vane (16) are repeatedly inclined upwards and downwards in circumferential rotation to generate multi-degree-of-freedom rotation;
in the process of rotating the guide vane (16), the evaporation gun (13), the preheating gun (14) and the ceramic ingot (15) are started to finish spraying.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311705335.9A CN117604463A (en) | 2023-12-12 | 2023-12-12 | Coating device and coating method for turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311705335.9A CN117604463A (en) | 2023-12-12 | 2023-12-12 | Coating device and coating method for turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117604463A true CN117604463A (en) | 2024-02-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311705335.9A Pending CN117604463A (en) | 2023-12-12 | 2023-12-12 | Coating device and coating method for turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117604463A (en) |
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2023
- 2023-12-12 CN CN202311705335.9A patent/CN117604463A/en active Pending
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