Airline turbine blade tenon tooth positioning clamp

Abstract

The utility model relates to an aircraft turbine blade tenon tooth positioning clamp which comprises a positioning seat and a pressing seat which are distributed in a left-right spaced mode, a positioning block is arranged at the upper end of the positioning seat, a pressing block is arranged at the upper end of the pressing seat, the positioning seat and the pressing seat are connected through a fastener, a movable gap is formed between the positioning block and the pressing block, and the movable gap is arranged between the positioning block and the pressing block. The pressing block and the positioning block are connected through a pressing adjusting piece, the pressing adjusting piece is used for adjusting the pressing block to move to be close to or away from the positioning block, and a positioning piece is arranged at the front end of the positioning seat and used for positioning the front side of a blade. According to the clamping device for the tenon tooth of the aircraft turbine blade, the bendable pressing base is arranged, after the pressing piece is adjusted and the pressing base is bent at the movable gap, the pressing base and the positioning base can position and clamp the tenon tooth of the aircraft turbine blade, the purposes of one-time positioning and clamping are achieved, and the convenience of clamping the tenon tooth of the aircraft turbine blade through the clamping device is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of blade positioning jigs, in particular to a positioning jig for the dovetail teeth of an aero-engine turbine blade. Background Art

[0002] The turbine rotor blade of an aero-engine has a dovetail tooth structure, which is assembled and fixed with the dovetail groove on the disk shaft of the engine and is a very important dimensional reference.

[0003] Most of the machining surfaces on the turbine blade are based on the dovetail teeth as the positioning reference. The quality of the dovetail tooth positioning affects the dimensional accuracy of the blade, and thus affects the engine performance.

[0004] The positioning part of the existing dovetail tooth positioning jig fits with the dovetail teeth of the blade. Due to the fluctuation of the dovetail tooth sizes of different blades, over-positioning will occur, resulting in the problem of repeated positioning deviation.

[0005] This patent designs a positioning jig for the dovetail teeth of an aero-engine turbine blade. By reasonably setting the positioning part and adopting the positioning method of "clamping the first tooth and clamping the last tooth", the jig structure is simplified, and the problem of repeated positioning deviation caused by over-positioning is solved. Content of the Utility Model

[0006] In order to solve the above technical problems, the purpose of the utility model is to provide a positioning jig for the dovetail teeth of an aero-engine turbine blade that can avoid the problem of positioning deviation.

[0007] In order to achieve the above purpose, the technical solution of the utility model is as follows: A positioning jig for the dovetail teeth of an aero-engine turbine blade includes a positioning seat and a pressing seat that are distributed at intervals left and right. A positioning block is provided at the upper end of the positioning seat, and a pressing block is provided at the upper end of the pressing seat. The positioning seat and the pressing seat are connected by fasteners. An activity gap is provided between the positioning block and the pressing block, and the two are connected by a pressing adjustment member. The pressing adjustment member is used to adjust the pressing block to move closer to or away from the positioning block. A positioning member is provided at the front end of the positioning seat, and this positioning member is used to position the front side of the blade.

[0008] The beneficial effect of the utility model is that by providing a bendable pressing seat, by adjusting the pressing member, the pressing seat bends at the activity gap. After bending, the pressing seat can position and clamp the dovetail teeth of the aero-engine turbine blade with the positioning seat, achieving the purpose of one-time positioning and clamping, and improving the convenience of the device for clamping the dovetail teeth of the aero-engine turbine blade.

[0009] Based on the above technical solution, the utility model can also be improved as follows.

[0010] Further, the positioning block is fixedly assembled at the upper end of the positioning seat. The positioning block includes a positioning portion and a first connecting portion. The positioning portion is assembled at the upper end of the first connecting portion. A first mating surface that mates with the dovetail teeth of the blade is provided on one side of the positioning portion close to the pressing block.

[0011] In the above technical solution, by providing the positioning portion and the first connecting portion, when clamping the aero-engine turbine blade, first insert the dovetail teeth of the aero-engine turbine blade between the positioning block and the pressing block. The positioning portion of the positioning block can position the dovetail tooth structure of the aero-engine turbine blade. At the same time, use the pressing member to connect and fasten the positioning block and the pressing block, so that the two can clamp the dovetail teeth of the aero-engine turbine blade.

[0012] Further, a positioning recess extending forward and backward is concavely provided in the upper part of the first mating surface, and positioning teeth extending forward and backward are convexly provided in the lower part of the first mating surface.

[0013] In the above technical solution, when the positioning portion clamps the dovetail teeth of the aero-engine turbine blade, the positioning recess can clamp and position the uppermost tooth of the dovetail teeth of the aero-engine turbine blade, forming a head-end reserved gap while clamping and limiting. At the same time, the positioning teeth can clamp and position the tooth groove at the lowermost end of the dovetail teeth of the aero-engine turbine blade, forming a tail-end reserved gap while clamping and limiting, avoiding the situation of inaccurate positioning caused by interference fit.

[0014] Further, the pressing block is fixedly assembled at the upper end of the pressing seat. The pressing block includes a pressing portion and a second connecting portion. The pressing portion is assembled at the upper end of the second connecting portion. A second mating surface that mates with the dovetail teeth of the blade is provided on one side of the pressing portion close to the positioning block.

[0015] In the above technical solution, by providing the pressing block and the second connecting portion, after the dovetail teeth of the aero-engine turbine blade are clamped and positioned, by adjusting the pressing member, use the pressing member to press against the pressing block and make it bend, so that the pressing portion of the pressing block approaches the positioning portion, and then clamp the positioned dovetail teeth of the aero-engine turbine blade.

[0016] Further, a pressing recess extending forward and backward is concavely provided in the upper part of the second mating surface, and pressing teeth extending forward and backward are convexly provided in the lower part of the second mating surface.

[0017] In the above technical solution, when the pressing portion of the device cooperates with the positioning portion to clamp the dovetail teeth of the aero-engine turbine blade, the pressing recess cooperates with the positioning recess to clamp the uppermost dovetail teeth of the aero-engine turbine blade. At the same time, the pressing teeth and the positioning teeth cooperate with each other, embed into the tooth groove at the lowermost end of the aero-engine turbine blade and clamp it.

[0018] Further, the pressing and adjusting member includes a double-headed screw, a gasket, and a handle. One end of the double-headed screw penetrates through the second connecting portion and is fitted on the first connecting portion. The handle is threadedly assembled on the other end of the double-headed screw. The gasket is sleeved on the other end of the double-headed screw and is located between the handle and the pressing block.

[0019] Through the above technical solution, by setting the double-headed screw, one end of the double-headed screw is fitted on the first connecting portion, and at the same time, the handle is rotated, so that the handle moves along the length direction of the double-headed screw, and the pressing block is abutted and bent, so that the movable gap between the pressing block and the positioning block is shortened, thereby clamping the dovetail teeth of the aero-engine turbine blade.

[0020] Further, the lower end of the second connecting portion is connected to the upper end of the pressing seat through a bendable connecting piece.

[0021] Through the above technical solution, by setting the connecting piece and using the connecting piece to connect and assemble the second connecting portion and the pressing seat, the second connecting portion is bent under the abutting action of the pressing and adjusting member.

[0022] Further, the fastening member includes a positioning pin and a fastening bolt. One end of the positioning pin is fixedly assembled on the positioning seat, and the other end penetrates through the pressing seat. One end of the fastening bolt penetrates through the pressing seat and is threadedly connected to the positioning seat.

[0023] Through the above technical solution, by setting the fastening bolt, the purpose of detachable connection of the pressing seat on the positioning seat is realized, and at the same time, setting the positioning pin improves the accuracy during disassembly and assembly of the pressing seat.

[0024] Further, the positioning member includes a positioning block and a connecting base. The positioning block is fixedly assembled on the upper end of the connecting base. The connecting base is assembled on the front end of the positioning seat through a positioning connecting member.

[0025] Through the above technical solution, by the detachable positioning member, when the device clamps the dovetail teeth of the aero-engine turbine blade, the positioning member can be used to position it, improving the clamping accuracy.

[0026] Further, the positioning connecting member includes a pin and a screw. One end of the pin passes through the connecting base and is fixedly connected to the positioning seat. One end of the screw penetrates through the connecting base and is threadedly connected to the positioning seat.

[0027] Through the above technical solution, when the positioning member needs to be disassembled and assembled, the pin can be used to position the connecting base, and at the same time, the screw can fasten the positioning member on the positioning base, thereby realizing the convenient positioning and disassembly of the device. Description of the Drawings

[0028] Figure 1Schematic three-dimensional structure diagram in the loosened state in the embodiment of the present utility model;

[0029] Figure 2 Schematic three-dimensional structure diagram in the clamped state in the embodiment of the present utility model;

[0030] Figure 3 is Figure 2 Enlarged schematic diagram of part A in;

[0031] Figure 4 Schematic explosion structure diagram in the embodiment of the present utility model.

[0032] In the attached drawings, the list of components represented by each reference numeral is as follows:

[0033] 1. positioning seat; 2. pressing seat; 3. positioning member; 4. fastening bolt; 5. positioning pin; 6. handle; 7. double-headed screw; 8. gasket; 9. set screw; 10. pin; 11. screw; 12. positioning recess; 13. positioning cogs; 14. pressing part recess; 15. pressing cogs. Detailed implementation manners

[0034] The principles and features of the present utility model will be described below in conjunction with the attached 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.

[0035] Embodiment

[0036] As Figures 1-4 shown, an aero-engine turbine blade tenon tooth positioning fixture includes a positioning seat 1 and a pressing seat 2 which are distributed at intervals left and right. A positioning block is provided at the upper end of the positioning seat 1, and a pressing block is provided at the upper end of the pressing seat 2. The positioning seat 1 and the pressing seat 2 are connected by fasteners. There is an active gap between the positioning block and the pressing block, and the two are connected by a pressing adjustment member. The pressing adjustment member is used to adjust the pressing block to move closer to or away from the positioning block. A positioning member 3 is provided at the front end of the positioning seat 1, and the positioning member 3 is used to position the front side of the blade.

[0037] Among them, the pressing seat 2 is a CrWMn component, and the surface hardness after heat treatment is HRC58 - 62.

[0038] The working principle is as follows: When it is necessary to use the device to clamp the tenon tooth structure of the aero-engine turbine blade, by manipulating the pressing member, the pressing member can drive the pressing block 2 to bend, so that it can approach the positioning block, thereby using the positioning block and the pressing block to position and clamp the tenon tooth of the aero-engine turbine blade, improving the convenience of clamping.

[0039] The above technical solution can be achieved by setting a bendable pressing seat 2. By adjusting the pressing member, the pressing seat 2 bends at the movable gap. After bending, the pressing seat 2 can position and clamp the dovetail teeth of the aero-engine turbine blade with the positioning seat 1, achieving the purpose of one-time positioning and clamping, and improving the convenience of the device for clamping the dovetail teeth of the aero-engine turbine blade.

[0040] Preferably, the positioning block is fixedly assembled at the upper end of the positioning seat 1. The positioning block includes a positioning portion and a first connecting portion. The positioning portion is assembled at the upper end of the first connecting portion. A first matching surface that matches the dovetail teeth of the blade is provided on one side of the positioning portion close to the pressing block.

[0041] The working principle is as follows: When clamping the dovetail teeth of the aero-engine turbine blade is required, the positioning portion above the positioning block of the pressing seat is used to preliminarily position the dovetail teeth of the aero-engine turbine blade. After positioning, by adjusting the pressing member, the pressing block and the positioning block jointly clamp the dovetail teeth of the aero-engine turbine blade, thus achieving the purpose of one-step positioning and clamping.

[0042] The above technical solution, by setting the positioning portion and the first connecting portion, when clamping the aero-engine turbine blade, first insert the dovetail teeth of the aero-engine turbine blade between the positioning block and the pressing block. The positioning portion of the positioning block can position the dovetail tooth structure of the aero-engine turbine blade, and at the same time, use the pressing member to connect and fasten the positioning block and the pressing block, so that the two can clamp the dovetail teeth of the aero-engine turbine blade.

[0043] Preferably, a positioning recess 12 extending forward and backward is concavely provided in the upper part of the first matching surface, and a positioning tooth 13 extending forward and backward is convexly provided in the lower part of the first matching surface.

[0044] The working principle is as follows: When the positioning block positions the dovetail teeth of the aero-engine turbine blade, the uppermost tooth of the dovetail teeth of the aero-engine turbine blade is inserted into the positioning recess 12 to achieve clamping of the uppermost tooth of the dovetail teeth of the aero-engine turbine blade. At the same time, the positioning tooth 13 is inserted into the lowermost tooth groove of the dovetail teeth of the aero-engine turbine blade to achieve engagement with the lowermost tooth groove of the dovetail teeth of the aero-engine turbine blade, thereby improving the accuracy of the device when clamping the dovetail teeth of the aero-engine turbine blade.

[0045] When the above technical solution clamps the dovetail teeth of the aero-engine turbine blade by the positioning block, the positioning recess 12 can clamp and position the uppermost tooth of the dovetail teeth of the aero-engine turbine blade, forming a head-end reserved gap while clamping and limiting. At the same time, the positioning tooth 13 can clamp and position the lowermost tooth groove of the dovetail teeth of the aero-engine turbine blade, forming a tail-end reserved gap while clamping and limiting, avoiding the situation of inaccurate positioning caused by interference fit.

[0046] Preferably, the clamping block is fixedly assembled on the upper end of the clamping seat 2, and the clamping block includes a clamping part and a second connecting part, the clamping part is assembled on the upper end of the second connecting part, and a second matching surface matching with the tenon of the blade is provided on one side of the clamping part close to the positioning block.

[0047] The pressing block includes a plate-shaped connecting portion and a block-shaped pressing portion, wherein the thickness of the plate-shaped connecting portion is smaller than the thickness of the block-shaped pressing portion, so that when the pressing member squeezes the block-shaped pressing portion, the plate-shaped connecting portion can be deformed, thereby causing the entire pressing block to bend.

[0048] The working principle is: by setting a clamping part, when the clamping block and the positioning block clamp the tenon of the aero-engine turbine blade, the clamping part cooperates with the positioning part to clamp the positioned aero-engine turbine blade tenon, and by adjusting the clamping piece, the clamping part continuously applies pressure, thereby making the tenon of the aero-engine turbine blade more stable during the clamping process.

[0049] The above technical solution is to set a clamping block and a second connecting part. After the tenon of the aero-engine turbine blade is clamped and positioned, the clamping piece is adjusted and used to press the clamping block and bend it, so that the clamping part of the clamping block is close to the positioning part, thereby clamping the tenon of the positioned aero-engine turbine blade.

[0050] Preferably, a pressing portion recess 14 extending forward and backward is concavely provided on the upper portion of the second mating surface, and a pressing clamping tooth 15 extending forward and backward is convexly provided on the lower portion of the second mating surface.

[0051] The working principle is: when the clamping part is clamping the tenon of the aero-engine turbine blade, the uppermost clamping tooth of the aero-engine turbine blade tenon is close to one side of the clamping part and inserted into the recess 14 of the clamping part, and the clamping clamping tooth 15 is clamped into the lowermost tooth groove of the aero-engine turbine blade tenon, so that the clamping block cooperates with the positioning block to clamp the tenon of the aero-engine turbine blade, which is more stable.

[0052] In the above technical solution, when the clamping part cooperates with the positioning part to clamp the tenon of the aero-engine turbine blade, the clamping part recess 14 cooperates with the positioning part recess 12 to clamp the uppermost tenon of the aero-engine turbine blade, and at the same time, the clamping tooth 15 cooperates with the positioning tooth 13 to embed into the lowermost tooth groove of the aero-engine turbine blade and clamp it.

[0053] Preferably, the clamping adjustment member includes a double-headed screw 7, a gasket 8 and a handle 6, one end of the double-headed screw 7 passes through the second connecting part and is embedded in the first connecting part, the handle 6 is threadedly assembled on the other end of the double-headed screw 7, and the gasket 8 is sleeved on the other end of the double-headed screw 7 and is located between the handle 6 and the clamping block.

[0054] The working principle is as follows: When adjusting the pressing member and applying a lateral pressure to the pressing block, by rotating the handle 6, the handle 6 maintains feeding along the length direction of the double-headed screw during rotation. While moving, it drives the gasket 8 to move towards the pressing block. At this time, the gasket 8 presses against the pressing block, causing the pressing block to bend towards the positioning block, thereby clamping the dovetail teeth of the aero-engine turbine blade.

[0055] The above technical solution sets the double-headed screw 7. By fitting one end of the double-headed screw 7 on the first connecting portion and simultaneously rotating the handle 6, the handle 6 moves along the length direction of the double-headed screw 7, and presses against and bends the pressing block, shortening the movable gap between the pressing block and the positioning block, thereby clamping the dovetail teeth of the aero-engine turbine blade.

[0056] Preferably, the lower end of the second connecting portion is connected to the upper end of the pressing seat 2 through a bendable connecting piece.

[0057] The working principle is as follows: By setting a sheet-shaped connecting piece between the second connecting portion and the pressing seat 2, when the pressing adjustment member abuts against the second connecting portion, the connecting piece can be bent, facilitating pressing.

[0058] The above technical solution sets the connecting piece and uses the connecting piece to connect and assemble the second connecting portion and the pressing seat 2. The second connecting portion bends under the abutting action of the pressing adjustment member.

[0059] Preferably, the fastener includes a positioning pin 5 and a fastening bolt 4. One end of the positioning pin 5 is fixedly assembled on the positioning seat 1, and the other end penetrates through the pressing seat 2. One end of the fastening bolt 4 penetrates through the pressing seat 2 and is threadedly connected to the positioning seat 1.

[0060] The working principle is as follows: When the pressing seat 2 is assembled on the positioning base, the positioning pin 5 can position and limit the pressing seat 2. At the same time, one end of the fastening bolt 4 passes through the pressing base and fixedly assembles the pressing base on the positioning base, thereby achieving high-precision fixed installation of the positioning base.

[0061] The above technical solution sets the fastening bolt 4, thereby achieving the purpose of detachable connection of the pressing seat 2 on the positioning seat 1. At the same time, setting the positioning pin 5 improves the accuracy of the pressing seat 2 during disassembly and assembly.

[0062] Preferably, the positioning member 3 includes a positioning block and a connecting base. The positioning block is fixedly assembled on the upper end of the connecting base, and the connecting base is assembled on the front end of the positioning seat 1 through a positioning connecting piece.

[0063] The working principle is as follows: Before the pressing block and the positioning block clamp the dovetail structure of the aero-engine turbine blade, the aero-engine turbine blade needs to be set on the main positioning block 1, and the positioning member is used to position the end of the aero-engine turbine blade, and cooperate with the positioning block to position the side of the aero-engine turbine blade, thereby further improving the positioning accuracy.

[0064] The above technical solution can realize the positioning of the device when clamping the dovetail of the aero-engine turbine blade by using the detachable positioning member 3, thereby improving the clamping accuracy.

[0065] Preferably, the positioning connecting member includes a pin 10 and a screw 11. One end of the pin 10 passes through the connecting base and is fixedly connected to the positioning seat 1, and one end of the screw 11 penetrates through the connecting base and is threadedly connected to the positioning seat 1.

[0066] The working principle is as follows: When the positioning member 3 needs to be installed, first, the pin 10 passes through the positioning member 3 and positions and limits it. At the same time, the screw 11 is used to fixedly assemble the positioning member on the positioning base, realizing the quick and high-precision installation of the positioning member 3.

[0067] In the above technical solution, when the positioning member 3 needs to be disassembled and assembled, the pin 10 can play the role of positioning the connecting base, and at the same time, the screw 11 can fasten the positioning member 3 on the positioning base, thereby realizing the convenient positioning, disassembly and assembly of the device.

[0068] Wherein, it further includes a set screw 9, and the set screw 9 is embedded inside the first connecting portion and is threadedly connected to one end of the double-headed screw 7.

[0069] The working principle is as follows: After one end of the double-headed screw 7 is inserted into the positioning block, the set screw 9 is embedded into the fitting gap between the double-headed screw 7 and the positioning block, thereby further improving the anti-torsion ability of the double-headed screw 7 and improving the installation stability of the double-headed screw 7.

[0070] The above technical solution, by setting the set screw 9, after one end of the double-headed screw 7 is embedded into the positioning block, the set screw 9 can be inserted into the fitting gap between one end of the double-headed screw 7 and the positioning block, thereby further improving the stability when one end of the double-headed screw 7 is embedded inside the positioning block.

[0071] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by terms such as "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.

[0072] 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 of such features. 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.

[0073] In the present utility model, unless otherwise clearly specified and defined, terms such as "mounted", "connected", "connected to", "fixed" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication 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.

[0074] 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 in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on 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 has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" 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 has a lower horizontal height than the second feature.

[0075] In the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples", etc., mean 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 may 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.

[0076] 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 limitations on 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 aero-engine turbine blade tenon tooth positioning fixture, characterized in that It includes a positioning seat (1) and a pressing seat (2) which are distributed at intervals left and right. A positioning block is provided at the upper end of the positioning seat (1), and a pressing block is provided at the upper end of the pressing seat (2). The positioning seat (1) and the pressing seat (2) are connected by fasteners. There is a movable gap between the positioning block and the pressing block, and the two are connected by a pressing adjustment member. The pressing adjustment member is used to adjust the pressing block to move closer to or away from the positioning block. A positioning member (3) is provided at the front end of the positioning seat (1), and this positioning member (3) is used to position the front side of the blade; the positioning block includes a positioning portion and a first connecting portion; the pressing block includes a pressing portion and a second connecting portion; the pressing adjustment member includes a double-headed screw (7), a gasket (8) and a handle (6). One end of the double-headed screw (7) penetrates through the second connecting portion and is fitted on the first connecting portion. The handle (6) is threadedly assembled on the other end of the double-headed screw (7). The gasket (8) is sleeved on the other end of the double-headed screw (7) and is located between the handle (6) and the pressing block; A set screw (9) is also included. The set screw (9) is fitted inside the first connecting portion and is threadedly connected to one end of the double-headed screw (7); the positioning member (3) includes a positioning block and a connecting base. The positioning block is fixedly assembled on the upper end of the connecting base, and the connecting base is assembled on the front end of the positioning seat (1) through a positioning connecting member.

2. The positioning fixture for the tenon teeth of an aero-engine turbine blade according to claim 1, wherein The positioning block is fixedly assembled on the upper end of the positioning seat (1). The positioning portion is assembled on the upper end of the first connecting portion. A first matching surface that matches the tenon teeth of the blade is provided on one side of the positioning portion close to the pressing block.

3. The positioning fixture for the dovetail of an aero-engine turbine blade according to claim 2, wherein, A positioning recess (12) extending forward and backward is concavely provided in the upper part of the first matching surface, and a positioning tooth (13) extending forward and backward is convexly provided in the lower part of the first matching surface.

4. A positioning fixture for aeroengine turbine blade tenons according to claim 3, characterized in that The pressing block is fixedly assembled on the upper end of the pressing seat (2). The pressing portion is assembled on the upper end of the second connecting portion. A second matching surface that matches the tenon teeth of the blade is provided on one side of the pressing portion close to the positioning block.

5. A positioning fixture for the tenon teeth of an aero-engine turbine blade according to claim 4, characterized in that, A pressing portion recess (14) extending forward and backward is concavely provided in the upper part of the second matching surface, and a pressing tooth (15) extending forward and backward is convexly provided in the lower part of the second matching surface.

6. The positioning fixture for the tenon teeth of an aero-engine turbine blade according to claim 5, wherein, The lower end of the second connecting portion is connected to the upper end of the pressing seat (2) through a bendable connecting piece.

7. A positioning fixture for aeroengine turbine blade tenons according to any one of claims 1 to 6, characterized in that The fasteners include a positioning pin (5) and a fastening bolt (4). One end of the positioning pin (5) is fixedly assembled on the positioning seat (1), and the other end penetrates through the pressing seat (2). One end of the fastening bolt (4) penetrates through the pressing seat (2) and is threadedly connected to the positioning seat (1).

8. The positioning fixture for the tenon teeth of an aeroengine turbine blade according to claim 1, wherein The positioning connecting member includes a pin (10) and a screw (11). One end of the pin (10) passes through the connecting base and is fixedly connected to the positioning seat (1). One end of the screw (11) penetrates through the connecting base and is threadedly connected to the positioning seat (1).

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