CN115961233A - A frock clamp for hot spraying gas turbine blade - Google Patents
A frock clamp for hot spraying gas turbine blade Download PDFInfo
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- CN115961233A CN115961233A CN202211677107.0A CN202211677107A CN115961233A CN 115961233 A CN115961233 A CN 115961233A CN 202211677107 A CN202211677107 A CN 202211677107A CN 115961233 A CN115961233 A CN 115961233A
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- blade
- gas turbine
- base
- blade base
- head tank
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- 238000005507 spraying Methods 0.000 title claims description 34
- 238000000034 method Methods 0.000 claims abstract description 13
- 238000010030 laminating Methods 0.000 claims abstract description 4
- 238000001816 cooling Methods 0.000 claims description 27
- 238000003466 welding Methods 0.000 claims 2
- 238000004891 communication Methods 0.000 claims 1
- 239000012720 thermal barrier coating Substances 0.000 abstract description 16
- 238000000576 coating method Methods 0.000 abstract description 11
- 238000007751 thermal spraying Methods 0.000 abstract description 9
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 4
- 230000001788 irregular Effects 0.000 abstract description 2
- 239000011248 coating agent Substances 0.000 description 9
- 239000007921 spray Substances 0.000 description 8
- 238000005457 optimization Methods 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000013178 mathematical model Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention relates to the technical field of thermal spraying coatings, in particular to a tool clamp for thermal spraying of a turbine blade of a gas turbine. Offer the constant head tank that corresponds and matches with gas turbine blade tongue-and-groove above the blade base constant head tank, the screw hole is processed respectively to the side of blade base constant head tank, left side baffle, the backplate, the right side baffle, preceding baffle is corresponding with the side of blade base constant head tank respectively, and process out the hole that corresponds respectively with blade base constant head tank side separately, and be connected through the side of fixing bolt with blade base constant head tank, the edge of four baffles realizes laminating completely through this fixed mode. The invention is used for preparing the thermal barrier coating for the outer surface of the blade body of the turbine blade of the gas turbine with plane, cambered surface and irregular curved surface integrated into a whole and with non-concentric whole parts, solves the key technology of independent manufacture of the heavy gas turbine in China, and can effectively and stably control the performance and quality of the thermal barrier coating and improve the production efficiency.
Description
Technical Field
The invention relates to the technical field of thermal spraying coatings, in particular to a tool clamp for thermal spraying of a turbine blade of a gas turbine.
Background
The turbine blade of the gas turbine is taken as a key part of the gas turbine, is always an important mark of the level of the gas turbine due to high use temperature and high manufacturing difficulty, and the heat protection technology of the turbine blade of the gas turbine is always mastered by foreign companies such as GE, mitsubishi and the like. In recent 20 years, china is always dedicated to research and application of thermal barrier coatings for combustion engines. Because the turbine blade of the heavy-duty gas turbine has large curvature and complex profile, and the uniformity control difficulty of the coating thickness is large, in order to solve the problem, the automatic spraying process of the thermal barrier coating for the turbine blade needs to be researched, and the generation and optimization of the track of the spray gun are the key technologies. At present, a mathematical model of the coating accumulation rate is established domestically, the complex curved surface of the turbine blade is partitioned, the variance between the coating thickness of discrete points of the curved surface and the ideal coating thickness is taken as an objective function, and the spraying track optimization is carried out on each area, so that the spraying track optimization of the complex curved surface of the turbine blade is realized. However, if the thermal barrier coating for the turbine blade is to be prepared, the spraying process and the tooling fixture must be combined to ensure the accurate positioning and stable rotation of the blade in the spraying process.
Disclosure of Invention
In order to solve the problems and realize the preparation of the thermal barrier coating for the turbine blade of the gas turbine, the invention aims to provide the tool clamp for thermally spraying the turbine blade of the gas turbine, which can ensure that the turbine blade of the gas turbine is accurately positioned and stably rotates along with a rotating workbench in the spraying process, realize the preparation of the thermal barrier coating for the turbine blade of the gas turbine, realize the effective protection of a blade tenon through the tool clamp and improve the production efficiency.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the utility model provides a frock clamp for hot spraying gas turbine blade, set up the constant head tank that corresponds and mate with gas turbine blade tongue-and-groove above the blade base constant head tank, 2 screw holes have been processed respectively to 4 sides of blade base constant head tank, the left side baffle, the backplate, the right side baffle, preceding baffle is corresponding with 4 sides of blade base constant head tank respectively, and process 2 holes that correspond respectively with blade base constant head tank side separately, and be connected through 4 sides of fixing bolt and blade base constant head tank, the edge of four baffles realizes laminating completely through this fixed mode.
According to the tool clamp for thermally spraying the gas turbine blade, the blade base positioning groove and the four baffles form an inner cavity of a hollow structure, the tenon of the gas turbine blade is arranged in the inner cavity, the blade positioning pin is welded on the upper end surface of the blade base positioning groove and is positioned through the blade positioning pin and the positioning groove on the blade base positioning groove, the lower part of the blade positioning pin is provided with an external thread, the upper part of the blade positioning pin is inserted into a positioning hole at the bottom of the tenon of the gas turbine blade, two third threaded holes are machined in the upper end surface of the blade base positioning groove, and the blade base positioning groove is connected with the lower part of the blade positioning pin through the third threaded holes; the positioning groove is processed in the blade base positioning groove according to the shape of the mortise of the gas turbine blade, and the positioning groove is connected with the mortise of the gas turbine blade.
According to the tool clamp for thermally spraying the turbine blade of the gas turbine, the blade tenon is arranged in the inner cavity of the tool clamp and is positioned through the blade positioning pin and the blade base positioning groove; the blade locating pin sets up at blade base constant head tank up end, and the blade base constant head tank is connected with the base through the screw hole.
A frock clamp for hot spraying gas turbine blade, the pedestal mounting is on commercial swivel work head, the bottom of blade base constant head tank sets up on the base through the chassis, the blade base constant head tank is fixed through welded mode and chassis, circular screw hole is processed out to blade base constant head tank bottom surface, the base design is two-layer parallel disc from top to bottom, be the fretwork design between the two-layer disc, and weld through vertical cylinder, the upper disc processing with the first screw hole in the center that the chassis of blade base constant head tank corresponds completely and be located the through-hole of first screw hole both sides, the bolt passes the through-hole of upper disc in proper order, the chassis carries out threaded connection with the blade base constant head tank, evenly process out the second screw hole in 4 directions of lower disc, the revolving stage face that the second screw hole and commercial swivel work head top are worn to locate by the bolt carries out threaded connection.
A frock clamp for hot spraying gas turbine blade, the first screw hole in center of upper disc, the centre bore on chassis, the central screw hole of blade base constant head tank are corresponding from bottom to top in proper order, the one end processing external screw thread of cooling tuber pipe, the other end processing taper shape of cooling tuber pipe, the external screw thread end of cooling tuber pipe is connected with the central screw hole of blade base constant head tank bottom surface through the first screw hole of base upper disc, the centre bore on chassis, the soft forced air cooling pipe is connected to the taper shape end of cooling tuber pipe.
The tool clamp for thermally spraying the turbine blade of the gas turbine is characterized in that the cooling air pipe is connected with the lower end face of the positioning groove of the blade base through an external thread.
According to the tool clamp for thermally spraying the turbine blade of the gas turbine, the inner part of the positioning groove of the blade base is processed according to the size of the blade mortise, so that the blade mortise is stably connected with the positioning groove of the blade base; meanwhile, a first circular threaded hole is formed in the bottom surface of the positioning groove of the blade base and is connected with a cooling air pipe.
The design idea of the invention is as follows:
the invention adopts a modularized design idea, designs independent supporting structures and accessories aiming at the shapes and the sizes of all parts from the rabbet to the mortise of the turbine blade of the gas turbine, adopts a screw fixing mode to combine all the parts into a complete tool clamp, ensures the turbine blade to be accurately and stably positioned, has high matching degree with the turbine blade, is flexible, adjustable and easy to replace all the parts, can adjust the sizes of the accessories according to the requirements of different types of blades, and expands the application range of the tool clamp. Through the effective cooperation of series of accessories such as left side baffle, backplate, right side baffle, preceding baffle, blade locating pin, blade base constant head tank, fixing bolt, cooling air pipe, base, can be connected turbine blade and commercial swivel work head are firm, extension combustion engine turbine blade rotation range, improve positioning accuracy.
The invention has the advantages and beneficial effects that:
1. the invention relates to a tooling fixture for thermally spraying a turbine blade of a gas turbine, which comprises a left baffle, a rear baffle, a right baffle, a front baffle, a blade positioning pin, a blade base positioning groove, a fixing bolt, a cooling air pipe and a base.
2. The gas turbine blade is connected with the table top of the commercial thermal spraying rotary workbench through the tool clamp of the turbine blade, so that the gas turbine blade and the commercial thermal spraying rotary workbench rotate coaxially, the turbine blade can rotate at a constant speed and be positioned accurately, the positioning accuracy can reach 1 degree, and the gas turbine blade is linked with a commercial spraying manipulator to ensure the uniformity of the coating of the turbine blade.
3. The invention is used for preparing the thermal barrier coating for the outer surface of the blade body of the turbine blade of the gas turbine with plane, cambered surface and irregular curved surface integrated into a whole and with non-concentric whole parts, solves the key technology of independent manufacture of the heavy gas turbine in China, and can effectively and stably control the performance and quality of the thermal barrier coating and improve the production efficiency.
Drawings
FIG. 1 is a schematic diagram of the overall configuration of an automated thermal barrier coating spray system for a gas turbine blade according to the present invention; in the figure, 11 commercial rotary tables; 12 a tooling fixture for thermal spraying of a gas turbine blade; 13 a gas turbine blade; 14 a plasma torch; 15 spray robot for commercial use.
2-3 are schematic views of tooling fixtures for thermally spraying gas turbine blades in accordance with the present invention; fig. 2 is an exploded view, and fig. 3 is an assembled view. In the figure, 21 left baffle; 22 a rear baffle; 23 right baffle plate; 24 a front baffle; 25 blade positioning pins; 26 blade base positioning slots; 27 fixing a bolt; 28 cooling the air pipe; 29 a base; 30 a chassis; 31 a first threaded hole; a 32 cylinder; 33 positioning grooves; 34 through holes; 35 a second threaded hole; 36 third threaded hole.
Detailed Description
The tooling fixture for thermally spraying a gas turbine blade according to the present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, the present invention preferably implements the application of a tooling fixture for thermal spraying of gas turbine blade thermal barrier coatings, and the automated thermal barrier coating system for gas turbine blades includes a commercial rotary table 11, a tooling fixture 12 for thermal spraying of gas turbine blades, a gas turbine blade 13, a plasma spray gun 14, a commercial spray robot 15, described in detail below:
the gas turbine blade 13 is connected with the commercial rotary worktable 11 through the tool clamp 12 for thermally spraying the gas turbine blade, so that the gas turbine blade 13 is ensured to be accurately positioned and stably rotate, the plasma spray gun 14 is connected with the commercial spraying manipulator 15, the plasma spray gun 14 is linked with the commercial rotary worktable 11, an automatic spraying system of a thermal barrier coating for the gas turbine blade is formed, and the gas turbine blade 13 is sprayed through the plasma spray gun 14.
Referring to fig. 1, 2 and 3, preferably, the tooling fixture 12 for thermally spraying a turbine blade of a gas turbine according to the present invention includes a left side baffle 21, a rear baffle 22, a right side baffle 23, a front baffle 24, a blade positioning pin 25, a blade base positioning slot 26, a fixing bolt 27, a cooling air pipe 28 and a base 29, which are sequentially connected, and is specifically described as follows:
Offer the constant head tank 33 that corresponds and match with gas turbine blade 13 tongue-and-groove above the blade base constant head tank 26, 2 screw holes have been processed respectively to 4 sides of blade base constant head tank 26, left side baffle 21, backplate 22, right side baffle 23, preceding baffle 24 is corresponding with 4 sides of blade base constant head tank 26 respectively, and process 2 holes that correspond respectively with blade base constant head tank 26 side separately, and be connected through fixing bolt 27 and 4 sides of blade base constant head tank 26, the edge of four baffles realizes laminating completely through this fixed mode, guarantee the stability of tenon, prevent simultaneously that this region has the coating deposit.
The blade base positioning groove 26 and the four baffles form an inner cavity of a hollow structure in a surrounding mode, a tenon of the gas turbine blade 13 is arranged in the inner cavity, the blade positioning pin 25 is welded on the upper end face of the blade base positioning groove 26 and is positioned through the blade positioning pin 25 and the positioning groove 33 on the blade base positioning groove 26, an external thread is machined on the lower portion of the blade positioning pin 25, the upper portion of the blade positioning pin 25 is inserted into a positioning hole in the bottom of the tenon of the gas turbine blade 13 to position the tenon of the blade, two third threaded holes 36 are machined in the upper end face of the blade base positioning groove 26, and the blade base positioning groove 26 is connected with the lower portion of the blade positioning pin 25 through the third threaded holes 36; the positioning groove 33 is processed in the blade base positioning groove 26 according to the shape of the mortise of the gas turbine blade 13, the positioning groove 33 is connected with the mortise of the gas turbine blade 13, and the positioning and fixing of the gas turbine blade 13 are realized through the design of the two parts.
According to the tool clamp 12 for thermally spraying the turbine blade of the gas turbine, the blade tenon is arranged in the inner cavity of the tool clamp and is positioned through the blade positioning pin 25 and the blade base positioning groove 26; the blade positioning pin 25 is arranged on the upper end face of the blade base positioning groove 26, the blade base positioning groove 26 is connected with the base 29 through a threaded hole, and the cooling air pipe 28 is connected with the lower end face of the blade base positioning groove 26 through external threads; 2 screw holes are processed respectively to 4 sides of blade base constant head tank, and left side baffle 21, backplate 22, right side baffle 23, preceding baffle 24 pass through bolt and screw hole and closely laminate with blade base constant head tank 26, guarantee the stability of tenon, prevent that this region has the coating deposit simultaneously.
In this embodiment, the inside size according to the blade tongue-and-groove of blade base constant head tank 26 is processed, guarantees that blade tongue-and-groove and blade base constant head tank are connected firmly, prevents that the blade from taking place to remove at the rotation in-process. Meanwhile, a circular first threaded hole 31 is formed in the bottom surface of the vane base positioning groove 26 and connected with the cooling air duct 28. The turbine blade of the gas turbine can realize accurate positioning within the range of 0-360 degrees, is stable and safe in rapid rotation, and meets the requirement of preparing thermal barrier coatings for the turbine blade of the gas turbine.
The embodiment result shows that the tool clamp for thermally spraying the turbine blade of the gas turbine can realize accurate positioning within the range of 0-360 degrees in the spraying process of the turbine blade of the gas turbine, ensure the stability and safety of the blade in quick rotation, solve the key technical problems of large curvature, complex profile and large control difficulty of the uniformity of the thickness of the coating of the turbine blade of a heavy-duty gas turbine, realize the automatic preparation of the thermal barrier coating for the turbine blade of the gas turbine, effectively and stably control the performance and quality of the thermal barrier coating and improve the production efficiency.
Claims (7)
1. The utility model provides a frock clamp for hot spraying gas turbine blade, a serial communication port, set up the constant head tank that corresponds and mate with gas turbine blade tongue-and-groove above the blade base constant head tank, 2 screw holes have been processed respectively to 4 sides of blade base constant head tank, the left side baffle, the backplate, the right side baffle, the preceding baffle is corresponding with 4 sides of blade base constant head tank respectively, and process 2 holes that correspond respectively with blade base constant head tank side separately, and be connected through 4 sides of fixing bolt and blade base constant head tank, the edge of four baffles realizes laminating completely through this fixed mode.
2. The tooling fixture for thermally spraying a gas turbine blade according to claim 1, wherein the blade base positioning groove and the four baffles define an inner cavity of a hollow structure, the tenon of the gas turbine blade is arranged in the inner cavity, the blade positioning pin is welded on the upper end surface of the blade base positioning groove and is positioned by the blade positioning pin and the positioning groove on the blade base positioning groove, the lower part of the blade positioning pin is externally threaded, the upper part of the blade positioning pin is inserted into the positioning hole at the bottom of the tenon of the gas turbine blade, two third threaded holes are machined on the upper end surface of the blade base positioning groove, and the blade base positioning groove is connected with the lower part of the blade positioning pin through the third threaded holes; the locating groove is processed in the locating groove of the blade base according to the shape of the mortise of the turbine blade of the gas turbine, and the locating groove is connected with the mortise of the turbine blade of the gas turbine.
3. The tooling fixture for thermally spraying a gas turbine blade according to claim 2, wherein the blade rabbet is disposed in the inner cavity of the tooling fixture and is positioned by a blade locating pin and a blade base locating slot; the blade locating pin sets up at blade base constant head tank up end, and the blade base constant head tank is connected with the base through the screw hole.
4. The tool fixture for thermally spraying turbine blades of gas turbines as claimed in claim 1, wherein the base is mounted on a commercial rotary table, the bottom of the positioning groove of the blade base is arranged on the base through a chassis, the positioning groove of the blade base is fixed with the chassis in a welding manner, a circular threaded hole is machined in the bottom surface of the positioning groove of the blade base, the base is designed into upper and lower layers of parallel disks, hollow-out design is adopted between the two layers of disks, and welding is carried out through a vertical cylinder, the upper layer of disk is provided with a central first threaded hole completely corresponding to the chassis of the positioning groove of the blade base and through holes positioned on two sides of the first threaded hole, a bolt sequentially penetrates through the through holes of the upper layer of disk, the chassis is in threaded connection with the positioning groove of the blade base, second threaded holes are uniformly machined in 4 directions of the lower layer of disk, and the bolt penetrates through the second threaded holes to be in threaded connection with the rotary table surface on the top of the commercial rotary table.
5. The tooling clamp for thermally spraying the turbine blade of the gas turbine as claimed in claim 4, wherein the first threaded hole in the center of the upper disc, the central hole of the base plate and the central threaded hole of the positioning groove of the blade base correspond to each other from bottom to top in sequence, an external thread is processed at one end of the cooling air pipe, a cone is processed at the other end of the cooling air pipe, the external thread end of the cooling air pipe is connected with the central threaded hole in the bottom surface of the positioning groove of the blade base through the first threaded hole of the upper disc of the base plate and the central hole of the base plate, and the cone end of the cooling air pipe is connected with the soft air cooling pipe.
6. A tooling fixture for thermally sprayed gas turbine blades according to claim 5, wherein the cooling air duct is connected with the lower end face of the blade base positioning groove by external threads.
7. The tooling fixture for thermally spraying a gas turbine blade according to claim 5, wherein the interior of the blade base positioning slot is machined according to the size of the blade mortise to ensure that the blade mortise is stably connected with the blade base positioning slot; meanwhile, a first circular threaded hole is formed in the bottom surface of the positioning groove of the blade base and is connected with a cooling air pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211677107.0A CN115961233A (en) | 2022-12-26 | 2022-12-26 | A frock clamp for hot spraying gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211677107.0A CN115961233A (en) | 2022-12-26 | 2022-12-26 | A frock clamp for hot spraying gas turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115961233A true CN115961233A (en) | 2023-04-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211677107.0A Pending CN115961233A (en) | 2022-12-26 | 2022-12-26 | A frock clamp for hot spraying gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115961233A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117399223A (en) * | 2023-12-12 | 2024-01-16 | 沈阳德通热喷涂新技术有限公司 | Automatic rotary spraying device for corrosion-resistant coating of petrochemical valve |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010180460A (en) * | 2009-02-06 | 2010-08-19 | Mitsubishi Heavy Ind Ltd | Method for forming hvof thermal spray coating layer and apparatus for holding turbine member |
| CN102031476A (en) * | 2009-10-06 | 2011-04-27 | 西门子公司 | Method and arrangement for a spray coating process |
| CN203498465U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Clamp for local coating of turbine blade |
| JP2014163898A (en) * | 2013-02-27 | 2014-09-08 | Mitsubishi Heavy Ind Ltd | Pore position acquisition method of construction object, and heat insulation coating method using the same |
| US20150217316A1 (en) * | 2012-08-10 | 2015-08-06 | Siemens Aktiengesellschaft | Measurement and protective apparatus for coating processes |
| US20180209279A1 (en) * | 2017-01-23 | 2018-07-26 | United Technologies Corporation | Apparatus and method for masking under platform areas of airfoil components |
-
2022
- 2022-12-26 CN CN202211677107.0A patent/CN115961233A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010180460A (en) * | 2009-02-06 | 2010-08-19 | Mitsubishi Heavy Ind Ltd | Method for forming hvof thermal spray coating layer and apparatus for holding turbine member |
| CN102031476A (en) * | 2009-10-06 | 2011-04-27 | 西门子公司 | Method and arrangement for a spray coating process |
| US20150217316A1 (en) * | 2012-08-10 | 2015-08-06 | Siemens Aktiengesellschaft | Measurement and protective apparatus for coating processes |
| JP2014163898A (en) * | 2013-02-27 | 2014-09-08 | Mitsubishi Heavy Ind Ltd | Pore position acquisition method of construction object, and heat insulation coating method using the same |
| CN203498465U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Clamp for local coating of turbine blade |
| US20180209279A1 (en) * | 2017-01-23 | 2018-07-26 | United Technologies Corporation | Apparatus and method for masking under platform areas of airfoil components |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117399223A (en) * | 2023-12-12 | 2024-01-16 | 沈阳德通热喷涂新技术有限公司 | Automatic rotary spraying device for corrosion-resistant coating of petrochemical valve |
| CN117399223B (en) * | 2023-12-12 | 2024-02-06 | 沈阳德通热喷涂新技术有限公司 | Automatic rotary spraying device for corrosion-resistant coating of petrochemical valve |
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