Tool structure for abrasive particle flow of turbine blade
By designing the abrasive workpiece structure of the turbine blades, the deformation problem of the turbine blades during the grinding process is solved, precise fixation and efficient processing are achieved, and operation is simplified and costs are reduced.
Patent Information
- Application Number
- CN202422284411.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-19
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2034-09-19
AI Technical Summary
The existing tooling has complex structure, high cost and inconvenient operation, making it difficult to effectively control the deformation of turbine blades during grinding, affecting the processing accuracy and quality.
A turbine blade abrasive flow tooling structure is designed, through the close fit between the cover plate and the inner ring and the stable connection between the base and the outer ring, combined with the screw connection method, the turbine blade is precisely fixed and provides smooth abrasive flow channels, reducing operation difficulty and cost.
The precise fixation of turbine blades during the abrasive flow treatment process is achieved, which avoids movement or deformation during the processing process, improves processing accuracy and surface polishing efficiency, simplifies the loading and unloading and maintenance process of the tooling, and reduces costs.
Smart Images
Figure CN223146794U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of machining equipment, and particularly relates to a tooling structure for abrasive flow machining of turbine blades. Background Art
[0002] In the fields of modern aerospace and energy power, as a core component, the performance of turbine blades is directly related to the operating efficiency and noise level of the whole machine. With the rapid development of 3D printing technology, the manufacturing of turbine blades has broken through the limitations of traditional processes and realized more complex and efficient fluid structure profile designs. However, while such complex profiles improve performance, they also pose higher requirements for subsequent surface treatment. In particular, the control of surface roughness has become a key factor affecting fluid dynamics performance.
[0003] Traditional grinding techniques are difficult to accurately process the complex curved surfaces of turbine blades, easily resulting in uneven surface quality and machining deformation, thereby affecting their overall performance. Therefore, the fluid grinding abrasive flow technology has emerged. With its unique flexible grinding ability, it shows great potential in reducing surface roughness and improving surface quality. However, in the implementation process, how to effectively control the deformation of turbine blades during grinding has become a technical problem to be solved urgently.
[0004] Most of the existing toolings have problems such as complex structure, high cost, and inconvenient operation, and it is difficult to effectively guarantee the machining accuracy and stability of turbine blades. Therefore, designing a tooling structure with a simple structure, low cost, convenient operation and capable of effectively reducing part machining deformation is of great significance for improving the manufacturing quality and efficiency of turbine blades. Based on this background, a tooling structure for abrasive flow machining of turbine blades is proposed. Summary of the Utility Model
[0005] In order to solve the above problems, the utility model provides a tooling structure for abrasive flow machining of turbine blades, which realizes the precise fixation of turbine blades during the abrasive flow machining process, effectively avoids the movement or deformation of turbine blades during the machining process, and ensures the machining accuracy and the safety of the blades.
[0006] The technical solution adopted by the utility model is as follows:
[0007] A tooling structure for abrasive flow machining of a turbine blade, comprising a cover plate A, a cover plate B, a base A, a base B and a turbine blade; the turbine blade consists of a blade, an inner ring and an outer ring, the blade is arranged between the inner ring and the outer ring, and a flange is arranged in the middle of the outer circle of the outer ring; the cover plate A is arranged above the inner ring, the cover plate B is arranged below the inner ring, and the cover plate A and the cover plate B are fixedly connected by a screw A; the base A is arranged above the outer ring, the base B is arranged below the outer ring, the base A and the base B are fixedly connected by a screw B, and a plurality of abrasive flow channels A are arranged on the base A, and a plurality of abrasive flow channels B are arranged on the base B.
[0008] A through hole A is arranged at the center of the cover plate A, and a threaded hole A is arranged at the center of the cover plate B. The screw A passes through the through hole A and is threadedly connected with the threaded hole A to fixedly connect the cover plate A and the cover plate B together.
[0009] An inner ring mating groove A for mating with the inner ring is arranged on the lower side of the outer circle of the cover plate A, and an inner ring mating groove B for mating with the inner ring is arranged on the upper side of the outer circle of the cover plate B.
[0010] A plurality of through holes B are arranged around the base A, and threaded holes B corresponding to the through holes B are arranged around the base B. The screw B passes through the through hole B and is threadedly connected with the threaded hole B to fixedly connect the base A and the base B together.
[0011] The base A is sequentially provided with an abrasive flow cavity A, an outer ring mating groove A and a flange mating groove from top to bottom. A pressing platform A is arranged at the center of the abrasive flow cavity A, and a plurality of abrasive flow channels A are arranged above the abrasive flow cavity A; the base B is sequentially provided with an abrasive flow cavity B and an outer ring mating groove B from bottom to top, and a pressing platform B is arranged at the center of the abrasive flow cavity B.
[0012] The through hole B is a stepped hole.
[0013] The beneficial effects of the present utility model are as follows:
[0014] 1. A tooling structure for abrasive flow machining of a turbine blade disclosed by the present utility model realizes precise fixation of the turbine blade during the abrasive flow machining process through the tight fit of the cover plate A and the cover plate B with the inner ring of the turbine blade, and the stable connection of the base A and the base B with the outer ring and the flange, effectively avoiding the movement or deformation of the turbine blade during the machining process, and ensuring the machining accuracy and the safety of the blade.
[0015] 2. A tooling structure for abrasive flow machining of a turbine blade disclosed by the present utility model provides a smooth flow path for the abrasive flow through the uniformly distributed abrasive flow channels A and abrasive flow channels B at the bottoms of the base A and the base B, ensuring that the abrasive can act on the surface of the turbine blade evenly and efficiently, thereby improving the efficiency and quality of surface polishing or deburring.
[0016] 3. A tooling structure for abrasive flow machining of turbine blades disclosed by the present utility model. Through the threaded connection of screw A and screw B, the assembly and disassembly of the cover plate and the base become simple and fast, which not only facilitates the loading and unloading of turbine blades, but also is convenient for the maintenance and repair of the tooling structure, reducing the operation difficulty and cost.
[0017] 4. A tooling structure for abrasive flow machining of turbine blades disclosed by the present utility model. The tooling structure for abrasive flow machining of turbine blades supports the weak parts of the parts through two cover plates respectively to reduce the deformation of the parts during the abrasive grinding process; and the two cover plates respectively transfer the forces received to the two tooling bases; effectively reducing the machining deformation during the part processing; enabling the parts to meet the dimensional tolerances and geometric tolerances of the drawings, and ultimately meeting the usage requirements of the parts.
[0018] 5. A tooling structure for abrasive flow machining of turbine blades disclosed by the present utility model. The tooling structure for abrasive flow machining of turbine blades is a simple, practical, effective and low-cost fixture design structure, and the operation is simple and stable, with strong practical applicability. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 is a three-dimensional exploded view of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0020] Figure 2 is a three-dimensional structure diagram of the assembled tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0021] Figure 3 is Figure 2 the sectional view of
[0022] Figure 4 is the sectional view of cover plate A of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0023] Figure 5 is the sectional view of cover plate B of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0024] Figure 6 is the sectional view of base A of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0025] Figure 7 is the sectional view of base B of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0026] Figure 8 is the working state diagram of the tooling structure for abrasive flow machining of turbine blades of the present utility model;
[0027] The components represented by the reference numerals in the drawings are:
[0028] The utility model: 1. Cover plate A, 1a. Through hole A, 1b. Inner ring mating groove A, 2. Cover plate B, 2a. Screw hole A, 2b. Inner ring mating groove B, 3. Base A, 3a. Outer ring mating groove A, 3b. Flange mating groove, 3c. Abrasive flow chamber A, 3d. Abrasive flow channel A, 3e. Through hole B, 3f. Pressing platform A, 4. Base B, 4a. Outer ring mating groove B, 4b. Abrasive flow chamber B, 4c. Abrasive flow channel B, 4d. Pressing platform B, 4e. Screw hole B, 5. Turbine blade, 5a. Blade, 5b. Inner ring, 5c. Outer ring, 5d. Flange, 6. Screw A, 7. Screw B. Detailed implementation mode
[0029] As Figures 1 to 3 shown, a tooling structure for abrasive flow of a turbine blade includes a cover plate A1, a cover plate B2, a base A3, a base B4 and a turbine blade 5; the turbine blade 5 is composed of a blade 5a, an inner ring 5b and an outer ring 5c, the blade 5a is arranged between the inner ring 5b and the outer ring 5c, and a ring of flange 5d is arranged in the middle of the outer circle of the outer ring 5c.
[0030] The cover plate A1 is arranged above the inner ring 5b, the cover plate B2 is arranged below the inner ring 5b, and the cover plate A1 and the cover plate B2 are fixedly connected by a screw A6; the base A3 is arranged above the outer ring 5c, the base B4 is arranged below the outer ring 5c, the base A3 and the base B4 are fixedly connected by a screw B7, and a plurality of abrasive flow channels A3d are arranged on the base A3, and a plurality of abrasive flow channels B4c are arranged on the base B4.
[0031] As Figure 4 and Figure 5 shown, a through hole A1a is arranged in the center of the cover plate A1, a screw hole A2a is arranged in the center of the cover plate B2, and the screw A6 passes through the through hole A1a and is threadedly connected with the screw hole A2a to fixedly connect the cover plate A1 and the cover plate B2 together.
[0032] An inner ring mating groove A1b for mating with the inner ring 5b is arranged on the lower side of the outer circle of the cover plate A1, and an inner ring mating groove B2b for mating with the inner ring 5b is arranged on the upper side of the outer circle of the cover plate B2.
[0033] As Figure 6 and Figure 7 shown, a plurality of through holes B3e are arranged around the base A3, and screw holes B4e corresponding to the through holes B3e are arranged around the base B4. The screw B7 passes through the through hole B3e and is threadedly connected with the screw hole B4e to fixedly connect the base A3 and the base B4 together. The through hole B3e is a stepped hole.
[0034] The base A3 is successively provided with an abrasive flow cavity A3c, an outer ring fitting groove A3a, and a flange fitting groove 3b from top to bottom. A pressing platform A3f is arranged at the center of the abrasive flow cavity A3c, and several abrasive flow channels A3d are arranged above the abrasive flow cavity A3c; the base B4 is successively provided with an abrasive flow cavity B4b and an outer ring fitting groove B4a from bottom to top, and a pressing platform B4d is arranged at the center of the abrasive flow cavity B4b.
[0035] The functions of the pressing platform A3f and the pressing platform B4d are that after the base A3 and the base B4 are fixedly connected into one body, the pressing platform A3f and the pressing platform B4d press and fix the cover plate A1 and the cover plate B2.
[0036] In a specific embodiment, the two cover plates are respectively installed on the two end faces of the inner hole of the part and fixed with M16 bolts; the above-mentioned assembly is installed in the two bases; the two bases are connected and fixed with eight M10 hexagon socket head cap screws; the tooling with the part to be ground is placed on the abrasive flow equipment for reciprocating grinding up and down.
[0037] As Figure 8 shown, the abrasive enters the tooling from the feed port at a certain pressure in the form of a viscous fluid mixed with abrasive grains. After being shunted by the base, it enters the part to be ground, and then flows out from the other side base.
[0038] The tooling structure of the abrasive flow of the turbine blade effectively reduces the machining deformation during the grinding process of the part; enables the part to meet the dimensional tolerance and geometric tolerance of the drawing, and finally meets the use requirements of the part.
Claims
1. An abrasive flow machining tooling structure for a turbine blade, characterized in that, It includes a cover plate A (1), a cover plate B (2), a base A (3), a base B (4) and a turbine blade (5); the turbine blade (5) is composed of a blade (5a), an inner ring (5b) and an outer ring (5c), the blade (5a) is arranged between the inner ring (5b) and the outer ring (5c), and a ring of flange (5d) is arranged in the middle of the outer circle of the outer ring (5c); the cover plate A (1) is arranged above the inner ring (5b), the cover plate B (2) is arranged below the inner ring (5b), and the cover plate A (1) and the cover plate B (2) are fixedly connected by a screw A (6); the base A (3) is arranged above the outer ring (5c), the base B (4) is arranged below the outer ring (5c), the base A (3) and the base B (4) are fixedly connected by a screw B (7), and a plurality of abrasive flow channels A (3d) are arranged on the base A (3), and a plurality of abrasive flow channels B (4c) are arranged on the base B (4).
2. The tooling structure of an abrasive flow for a turbine blade according to claim 1, wherein A through hole A (1a) is arranged at the center of the cover plate A (1), a screw hole A (2a) is arranged at the center of the cover plate B (2), and the screw A (6) passes through the through hole A (1a) and is threadedly connected with the screw hole A (2a) to fixedly connect the cover plate A (1) and the cover plate B (2) together.
3. The tooling structure of an abrasive flow for a turbine blade according to claim 2, characterized in that, An inner ring mating groove A (1b) for mating with the inner ring (5b) is arranged on the lower side of the outer circle of the cover plate A (1), and an inner ring mating groove B (2b) for mating with the inner ring (5b) is arranged on the upper side of the outer circle of the cover plate B (2).
4. The tooling structure of an abrasive flow for a turbine blade according to claim 1, wherein A plurality of through holes B (3e) are arranged around the base A (3), and screw holes B (4e) corresponding to the through holes B (3e) are arranged around the base B (4), and the screw B (7) passes through the through holes B (3e) and is threadedly connected with the screw holes B (4e) to fixedly connect the base A (3) and the base B (4) together.
5. The tooling structure of abrasive flow for a turbine blade according to claim 4, characterized in that, The base A (3) is sequentially provided with an abrasive flow cavity A (3c), an outer ring mating groove A (3a) and a flange mating groove (3b) from top to bottom, a pressing platform A (3f) is arranged at the center of the abrasive flow cavity A (3c), and a plurality of abrasive flow channels A (3d) are arranged above the abrasive flow cavity A (3c); the base B (4) is sequentially provided with an abrasive flow cavity B (4b) and an outer ring mating groove B (4a) from bottom to top, and a pressing platform B (4d) is arranged at the center of the abrasive flow cavity B (4b).
6. The tooling structure of abrasive flow for a turbine blade according to claim 4, characterized in that, The through hole B (3e) is a stepped hole.