Electric machining clamp for aircraft engine blade

Abstract

The utility model relates to an aircraft engine blade electromachining clamp which comprises a main positioning block and two sets of side pressing block assemblies, the side pressing block assemblies are assembled on the front side and the rear side of the main positioning block respectively, the upper ends of the side pressing block assemblies are provided with pressing parts, and the pressing parts are used for clamping and pressing an aircraft engine blade on the main positioning block. Guide matching parts are arranged at the lower ends of the side pressing block assemblies, and matching grooves matched with the guide matching parts are formed in the front side and the rear side of the main positioning block. When the aircraft engine blade with the air film hole needs to be clamped, the position of the side pressing block assembly on the main positioning block is adjusted through the adjusting assembly, so that the side pressing block assembly clamps and presses the pressing grooves in the two sides of the aircraft engine blade, and due to the fact that the pressing grooves are formed in the side portions of the aircraft engine blade, the air film hole is formed in the side portion of the aircraft engine blade. Therefore, interference between the clamp and the aircraft engine blade during electromachining of the aircraft engine blade is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engine blade fixtures, in particular to an electro-machining fixture for aero-engine blades. Background Art

[0002] Aero-engine turbine blades need to withstand high-temperature and high-pressure environments. Advanced turbine blades have a hollow blade body with film holes. High-speed and high-pressure gas flows out from the film holes in the blade body to cool and protect the blade, and improve the temperature tolerance of the blade.

[0003] The film holes on the blade body of the aero-engine blade cover the entire blade body. When using the electro-machining process, the fixture is likely to interfere with the electrode cutting tool.

[0004] The existing conventional solution is to use multiple sets of fixtures to avoid the interference parts respectively and perform positioning and clamping multiple times, which increases the processing time and cost.

[0005] There is also a method of first using wire cutting to machine a pressing groove structure at the edge of the blade blank position to provide a pressable part, then clamping the pressing groove structure with a fixture to avoid interference in the spatial orientation during clamping. After electro-machining is completed, the pressing groove structure is removed by mechanical machining.

[0006] This patent designs an electro-machining fixture for aero-engine blades. By improving the clamping and positioning structures of the fixture, the interference between the electrode and the fixture is avoided, so that the film holes on the blade body of the aero-engine blade can be processed by one-time positioning and clamping, improving the processing efficiency and reducing the processing cost. Summary of the Utility Model

[0007] In order to solve the above technical problems, the purpose of the utility model is to provide a fixture that can avoid interference during electro-machining for aero-engine blades with film holes.

[0008] In order to achieve the above purpose, the technical solution of the utility model is as follows: an electro-machining fixture for aero-engine blades, including a main positioning block and side pressing block assemblies. There are two sets of side pressing block assemblies, which are respectively assembled on the front and rear sides of the main positioning block. The upper end of the side pressing block assembly is provided with a pressing part for clamping and pressing the aero-engine blade on the main positioning block. The lower end of the side pressing block assembly is provided with a guiding and mating part, and mating grooves adapted to the guiding and mating parts are provided on both the front and rear sides of the main positioning block.

[0009] The beneficial effect of the utility model is that when it is necessary to clamp an aero-engine blade with film holes, the position of the side pressing block assembly on the main positioning block is adjusted through an adjusting component, so that the side pressing block assembly clamps and presses the two side pressing grooves of the aero-engine blade. Since the pressing grooves are arranged on the sides of the aero-engine blade, interference between the fixture and the aero-engine blade is avoided during electro-machining of the aero-engine blade.

[0010] On the basis of the above technical solution, the present utility model can be further improved as follows.

[0011] Further, the side pressing block assembly includes a side pressing block, and the pressing part and the guiding and fitting part are respectively assembled on the same side of the upper and lower ends of the side pressing block.

[0012] Through the above technical solution, by providing two side pressing blocks and respectively pressing the two side pressing blocks into the front pressing groove and the rear pressing groove of the aero-engine blade, there is no spatial interference between the entire blade surface of the aero-engine blade and the fixture.

[0013] Further, reinforcing ribs are assembled on the sides of the two side pressing blocks that are away from each other.

[0014] Through the above technical solution, by providing reinforcing ribs on the sides of the two side pressing blocks, the structural strength of the two pressing blocks during pressing is improved.

[0015] Further, the pressing part is a horizontal clamping block, the guiding and fitting part is a plate body extending obliquely downward, the fitting groove is an inclined groove body, and a pressing screw threadedly connected to the main positioning block is provided through the side pressing block in the front and rear directions.

[0016] Through the above technical solution, by providing a sliding strip and a pressing screw, the rotation of the pressing screw drives the pressing block to move towards the main positioning block, so that the pressing part of the pressing block clamps the aero-engine blade in the horizontal direction. At the same time, the sliding strip at the lower end of the main positioning block is inserted into the fitting groove, and the fitting groove applies a downward pressure to the sliding strip, thereby driving the pressing part at the upper end of the pressing block to press the aero-engine blade in the vertical direction while clamping, so as to achieve the purpose of clamping the aero-engine blade in one step.

[0017] Further, an auxiliary positioning block is also included, and the auxiliary positioning block is assembled at any one of the left and right ends of the main positioning block.

[0018] Through the above technical solution, by providing an auxiliary positioning block and using the auxiliary positioning block to position the aero-engine blade before clamping, the accuracy during clamping is improved.

[0019] Further, the auxiliary positioning block is a strip-shaped member, and a positioning surface adapted to the side end of the aero-engine blade is provided on the side of the auxiliary positioning block close to the main positioning block at the upper end.

[0020] Through the above technical solution, by providing a positioning surface on the side of the auxiliary positioning block 1, the positioning surface can be positioned according to the shapes of the left and right ends of the aero-engine blade, so that the aero-engine blade is more stable and accurate during clamping.

[0021] Further, a notch is provided at one end of the main positioning block, and the auxiliary positioning block is embedded in the notch.

[0022] The above technical solution improves the accuracy during the installation of the auxiliary positioning block by providing an auxiliary positioning block and embedding the auxiliary positioning block in the main positioning block.

[0023] Furthermore, a second positioning surface is provided at the upper end of the end of the main positioning block away from the auxiliary positioning block, and the shape of the second positioning surface matches the shape of the lower end of the aero-engine blade.

[0024] The above technical solution provides a second positioning surface on the main positioning block. When the device clamps the aero-engine blade, the second positioning surface performs secondary positioning on the lower end of the aero-engine blade, thereby making the aero-engine blade more stable and accurate during clamping.

[0025] Furthermore, an assembly part penetrating the auxiliary positioning block in the left-right direction is provided inside the auxiliary positioning block, and the assembly part is connected to the main positioning block.

[0026] The above technical solution enables the auxiliary positioning block to be disassembled and assembled from the device through the assembly part, improving the convenience of the device when clamping the aero-engine blade.

[0027] Furthermore, the assembly part is a wing nut bolt, and one end of the wing nut bolt penetrates the auxiliary positioning block and is threadedly connected to the corresponding end of the main positioning block.

[0028] The above technical solution sets the assembly part as a wing nut bolt, so that when moving the auxiliary positioning block, there is no need to use tools, and manually turning the wing nut bolt can achieve the disassembly and assembly of the auxiliary positioning block. Description of the Drawings

[0029] Figure 1 is a three-dimensional structural schematic diagram in an embodiment of the present invention;

[0030] Figure 2 is a side view cross-sectional structural schematic diagram of the pressing part in an embodiment of the present invention;

[0031] Figure 3 is a three-dimensional exploded structural schematic diagram in an embodiment of the present invention;

[0032] Figure 4 is a three-dimensional structural schematic diagram of the reinforcing rib in an embodiment of the present invention.

[0033] In the drawings, the list of components represented by each reference numeral is as follows:

[0034] 1. Main positioning block; 2. Rear side pressing block; 21. Reinforcing rib; 3. Pressing screw; 4. Front side pressing block; 5. Auxiliary positioning block; 6. Assembly part. Detailed Embodiments

[0035] The principles and features of the present utility model will be described below in conjunction with the accompanying drawings. The examples given are only used to explain the present utility model and are not intended to limit the scope of the present utility model.

[0036] Embodiment

[0037] As Figures 1-4 shown, an electro - machining fixture for aero - engine blades includes a main positioning block 1 and side pressing block assemblies. There are two sets of side pressing block assemblies, which are respectively assembled on the front and rear sides of the main positioning block 1. The upper end of the side pressing block assembly is provided with a pressing part for clamping and pressing the aero - engine blade on the main positioning block 1. The lower end of the side pressing block assembly is provided with a guiding and mating part, and mating grooves adapted to the guiding and mating part are provided on both the front and rear sides of the main positioning block 1.

[0038] The working principle is as follows: When the device clamps the aero - engine blade, the side pressing block assembly can use the pressing part to clamp the aero - engine blade, and the guiding and mating part and the mating groove cooperate with each other, so that the pressing part can apply a downward pressure to the aero - engine blade while clamping it, enabling the device to perform a one - time clamping operation while clamping the aero - engine blade.

[0039] The above - mentioned technical solution can, when it is necessary to clamp an aero - engine blade with air film holes, adjust the position of the side pressing block assembly on the main positioning block through the adjusting assembly, so that the side pressing block assembly clamps and presses the two side pressing grooves of the aero - engine blade. Since the pressing grooves are arranged on the side of the aero - engine blade, interference between the fixture and the aero - engine blade during electro - machining of the aero - engine blade is avoided.

[0040] Preferably, the side pressing block assembly includes a side pressing block 2, and the pressing part and the guiding and mating part are respectively assembled on the same side of the upper and lower ends of the side pressing block 2.

[0041] Among them, the side pressing block 2 is a steel member.

[0042] The working principle is as follows: By setting the side pressing block 2 and using the side pressing block 2 to clamp the aero - engine blade front and back, the stability of clamping the aero - engine blade is improved.

[0043] The above - mentioned technical solution makes the entire blade surface of the aero - engine blade have no space interference with the fixture by setting two side pressing blocks and pressing the side pressing blocks 2 into the front - side basin - side pressing groove and the rear - side back - side pressing groove of the aero - engine blade respectively.

[0044] Preferably, reinforcing ribs 21 are assembled on the mutually - far - away sides of the two side pressing blocks 2.

[0045] The working principle is: when the front side pressure block 4 and the rear side pressure block 2 move relative to each other and clamp the aero-engine blade, the structural strength of the front side pressure block 4 and the rear side pressure block 2 is improved by setting the reinforcing ribs 21, so that when the two pressure blocks are moved and clamped, the mutual extrusion between the guide matching part and the matching groove will not cause the device to bend or break.

[0046] The above technical solution provides reinforcing ribs on the sides of the front side pressing block 4 and the rear side pressing block 2 to improve the structural strength of the two pressing blocks when they are pressed.

[0047] Preferably, the clamping portion is a horizontal clamping block, the guiding matching portion is a plate body extending obliquely downward, the matching groove is an inclined groove body, and the side clamping block 2 is penetrated front and back by a clamping screw 3 threadedly connected to the main positioning block 1.

[0048] The diameter of the through hole of the side pressure block 2 at the clamping screw 3 is larger than the diameter of the clamping screw 3 itself.

[0049] The working principle is: when the two side pressure blocks 2 move with the clamping screw 3, the slide bar is inserted into the matching groove, and under the mutual interference with the matching groove, the clamping block can clamp in the horizontal direction while maintaining downward pressure on the aero-engine blade, thereby improving the stability of the device when clamping the aero-engine blade.

[0050] The above technical solution sets a sliding bar and a clamping screw 3, and utilizes the screwing of the clamping screw 3 to drive the pressure block to move toward the main positioning block 1, so that the clamping part of the pressure block clamps the aero-engine blade in the horizontal direction, and at the same time, the sliding bar at the lower end of the main positioning block 1 is inserted into the matching groove, and the matching groove is utilized to apply downward pressure to the sliding bar, thereby driving the clamping part at the upper end of the pressure block to clamp the aero-engine blade in the vertical direction at the same time, thereby achieving the purpose of clamping the aero-engine blade in one step.

[0051] Furthermore, it also includes an auxiliary positioning block 5 , which is assembled on either the left or right end of the main positioning block 1 .

[0052] The working principle is: when clamping the aero-engine blade, by setting the auxiliary positioning block 5, the left and right sides of the aero-engine blade can be positioned by the auxiliary positioning block 5 before clamping, so as to achieve fast and accurate clamping.

[0053] The above technical solution arranges the auxiliary positioning block 5, and uses the auxiliary positioning block 5 to position the aero-engine blade before clamping the aero-engine blade, so as to improve the accuracy of clamping.

[0054] Furthermore, a notch is provided at one end of the main positioning block 1, and the auxiliary positioning block 5 is embedded in the notch.

[0055] The working principle is as follows: By setting the auxiliary positioning block 5 and embedding the auxiliary positioning block 5 in the notch, the installation stability of the auxiliary positioning block 5 is improved.

[0056] The above technical solution improves the accuracy of the installation of the auxiliary positioning block 5 by setting the auxiliary positioning block 5 and embedding the auxiliary positioning block 5 in the main positioning block 1.

[0057] Furthermore, a second positioning surface is provided at the upper end of the end of the main positioning block 1 away from the auxiliary positioning block 5, and the shape of the second positioning surface matches the shape of the lower end of the aero-engine blade.

[0058] The working principle is as follows: When it is necessary to clamp the aero-engine blade, first, the aero-engine blade needs to be placed on the upper end of the main positioning block 1, and the second positioning surface is used to fit and position the upper and lower ends of the aero-engine blade, so that it can be more precise and stable when being clamped.

[0059] The above technical solution sets a second positioning surface on the main positioning block. When the device clamps the aero-engine blade, the second positioning surface performs secondary positioning on the lower end of the aero-engine blade, so that the aero-engine blade is more stable and precise when being clamped.

[0060] Preferably, an assembly part 6 penetrating through the auxiliary positioning block 5 in the left-right direction is provided inside the auxiliary positioning block 5, and the assembly part 6 is connected to the main positioning block 1.

[0061] The working principle is as follows: When it is necessary to move or disassemble and assemble the auxiliary positioning block 5, by adjusting the assembly part 6, the auxiliary positioning block 5 can be disassembled and assembled on the main positioning block 1.

[0062] The above technical solution enables the auxiliary positioning block 5 to be disassembled and assembled from the device through the assembly part 6, improving the convenience of the device when clamping the aero-engine blade.

[0063] Preferably, the assembly part 6 is a wing nut. One end of the wing nut penetrates through the auxiliary positioning block 5 and is threadedly connected to the corresponding end of the main positioning block 1.

[0064] The working principle is as follows: By setting the assembly part as a wing nut, manually turning the wing nut by hand, and using the wing nut to fasten and assemble the auxiliary positioning block 5 on the main positioning block 1, the convenience of disassembling and assembling the auxiliary positioning block 5 is improved.

[0065] The above technical solution enables the disassembly and assembly of the auxiliary positioning block by setting the assembly part as a wing nut. When moving the auxiliary positioning block 5, no tools are required, and the wing nut can be manually turned by hand to achieve the disassembly and assembly of the auxiliary positioning block.

[0066] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model.

[0067] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present utility model, the meaning of "a plurality of" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0068] In the present utility model, unless otherwise clearly specified and defined, the terms "installed", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the connection inside two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0069] In the present utility model, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on the top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature is at a higher level than the second feature in terms of horizontal height. The first feature being "under", "beneath" and "under the bottom of" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature is at a lower level than the second feature in terms of horizontal height.

[0070] In the description of this specification, the description referring to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0071] Although the embodiments of the present utility model have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present utility model. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present utility model.

Claims

1. An electro-machining fixture for aero-engine blades, characterized in that, It includes a main positioning block (1) and side pressing block assemblies. There are two groups of the side pressing block assemblies, which are respectively assembled on the front and back sides of the main positioning block (1). The upper end of the side pressing block assembly is provided with a pressing part for clamping and pressing the aero-engine blade on the main positioning block (1). The lower end of the side pressing block assembly is provided with a guiding and mating part, and mating grooves adapted to the guiding and mating parts are provided on both the front and back sides of the main positioning block (1).

2. The electro-machining fixture for an aero-engine blade according to claim 1, characterized in that, The side pressing block assembly includes a side pressing block (2), and the pressing part and the guiding and mating part are respectively assembled on the same side of the upper and lower ends of the side pressing block (2).

3. The electro-machining fixture for an aero-engine blade according to claim 2, characterized in that, Reinforcing ribs (21) are assembled on the sides of the two side pressing blocks (2) away from each other.

4. The electro - machining fixture for aero - engine blades according to claim 2, wherein, The pressing part is a horizontal clamping block, the guiding and mating part is a plate body extending obliquely downward, the mating groove is an inclined groove body, and a pressing screw (3) threadedly connected to the main positioning block (1) penetrates through the side pressing block in the front and back directions.

5. The electro - machining fixture for aero - engine blades according to claim 1, wherein, It further includes an auxiliary positioning block (5), and the auxiliary positioning block (5) is assembled at any one of the left and right ends of the main positioning block (1).

6. The electro - machining fixture for aero - engine blades according to claim 5, wherein, The auxiliary positioning block (5) is a strip-shaped member, and a positioning surface adapted to the side end of the aero-engine blade is provided on one side of the upper end of the auxiliary positioning block (5) close to the main positioning block (1).

7. The electro - machining fixture for an aero - engine blade according to claim 6, wherein, A notch is provided at one end of the main positioning block (1), and the auxiliary positioning block (5) is embedded in the notch.

8. The electro - machining fixture for aero - engine blades according to claim 7, wherein, A second positioning surface is provided at the upper end of the end of the main positioning block (1) away from the auxiliary positioning block (5), and the second positioning surface matches the shape of the lower end of the aero-engine blade.

9. A kind of electric machining fixture for aeroengine blades according to any one of claims 5 to 8, characterized in that An assembly part (6) penetrating through the auxiliary positioning block (5) in the left and right directions is provided inside the auxiliary positioning block (5), and the assembly part (6) is connected to the main positioning block (1).

10. The electro - machining fixture for an aero - engine blade according to claim 9, wherein, The assembly part (6) is a wing bolt, and one end of the wing bolt penetrates through the auxiliary positioning block (5) and is threadedly connected to the corresponding end of the main positioning block (1).

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