Aviation turbine disc blade centering device

Abstract

The utility model relates to an aeronautical turbine disc blade centering device, which belongs to the technical field of aeronautical parts, and comprises a chassis, a centering assembly and a positioning assembly, the positioning assembly comprises a positioning block and a plurality of pressing assemblies, the pressing assemblies are arranged along the radial direction of the positioning block and are in sliding fit with the positioning block, and the pressing assemblies are arranged along the circumferential direction of the positioning block at intervals and are in sliding fit with the positioning block. One end of the centering assembly is connected with the base plate, and the other end of the centering assembly penetrates through the positioning block and is in sliding fit with the positioning block. The turbine disc blade centering device has the beneficial effects that the turbine disc blade is placed on the base plate, the centering assembly is driven to move up and down in the vertical direction, then the positioning assembly is driven to move up and down in the vertical direction till the end, in the circumferential direction, of the positioning assembly moves to abut against the inner wall of the turbine disc blade and is pressed tightly, and a positioning point is formed at the abutting position; the center of a circle formed by the multiple positioning points is the circle center of the turbine disc blade, and the circle center of the turbine disc blade is accurately positioned.

Description

Technical Field

[0001] This utility model relates to the field of aviation parts technology, specifically to an aviation turbine disk blade centering device. Background Technology

[0002] The machining of aerospace turbine blades is quite complex, differing from the machining of general ring components such as casings. The complexity lies in the numerous blade sections and curved surfaces inherent in turbine blade rings, and positioning methods are often limited by the complexity of their structure and the difficulty of machining. Many ring-shaped positioning methods choose fixed positions on the inner arc of the turbine blade's curved surface. However, the inner arc of this surface often has protrusions or depressions, making accurate positioning impossible and consequently preventing the precise location of the turbine blade's actual center, thus affecting subsequent machining steps.

[0003] Therefore, an aircraft turbine disk blade centering device is provided to solve the above problems. Utility Model Content

[0004] The technical problem solved by this invention is how to accurately locate the center of the turbine disk blades.

[0005] The technical solution of this utility model to solve the above-mentioned technical problems is as follows: A centering device for aircraft turbine disk blades includes a chassis, a centering component and a positioning component. The positioning component includes a positioning block and a plurality of clamping components. The clamping components are arranged radially along the positioning block and slide in cooperation with the positioning block. The plurality of clamping components are arranged circumferentially and spaced apart along the positioning block. One end of the centering component is connected to the chassis, and the other end of the centering component passes through the positioning block and slides in cooperation with the positioning block.

[0006] The centering component moves the positioning component closer to the chassis, and one end of one of the plurality of clamping components extends out of the positioning block, or moves the positioning component away from the chassis, and one end of one of the plurality of clamping components retracts into the positioning block.

[0007] The beneficial effects of this utility model are: placing the turbine disk blade on the chassis, driving the centering component to move up and down in the vertical direction, thereby driving the positioning component to move up and down in the vertical direction until one end of multiple pressing components extends out of the positioning block and abuts and presses against the inner wall of the turbine disk blade, and a positioning point is formed at the abutment point. The center of the circle formed by multiple positioning points is the center of the turbine disk blade, thus achieving accurate positioning of the center of the turbine disk blade.

[0008] Based on the above technical solution, the present invention can be further improved as follows.

[0009] Furthermore, the positioning block is provided with multiple fixing parts at intervals along its circumference, and multiple clamping components are slidably disposed in one end of each of the multiple fixing parts. The other end of the clamping component passes through the other end of the fixing part and slides in cooperation with the centering component.

[0010] The beneficial effect of adopting the above-described further solution is that when the centering assembly moves downward in the vertical direction, it simultaneously applies a downward vertical force to the positioning block and an axial force to the clamping assembly. The downward vertical force drives the positioning block and the clamping assembly to move downward in the vertical direction simultaneously. During the downward vertical movement of the clamping assembly, the axial force pushes the clamping assembly to abut and press against the inner wall of the turbine disk blade, forming a positioning point at the contact point.

[0011] Furthermore, the number of fixing parts is at least three, and the at least three fixing parts are evenly distributed along the circumference of the positioning block.

[0012] The beneficial effect of adopting the above-mentioned further solution is that multiple fixing parts can increase the stability of contact with the inner wall of the turbine disk blades.

[0013] Furthermore, it also includes a guide block, the chassis is fixedly connected to the guide block, and one end of the centering component is sleeved inside the guide block and detachably connected to the guide block.

[0014] Furthermore, the centering assembly includes a centering block, a centering screw, and a centering spring. The positioning block has a tapered hole, and the guide block has a first groove. One end of the centering block is located in the first groove, and the other end of the centering block has a tapered portion located in the tapered hole and slidingly engaged with the tapered hole. The centering screw passes through the centering block and the first groove in sequence and is threadedly connected to the guide block. The centering screw is fitted with the centering spring. One end of the centering block has a second groove, and one end of the centering spring abuts against the bottom of the second groove. The other end of the centering spring abuts against the bottom of the first groove and applies an elastic force to the centering block to move it away from the guide block.

[0015] The beneficial effect of adopting the above-mentioned further solution is that during the process of driving the centering screw to tighten with the guide block thread, the centering screw applies a downward force in the vertical direction to the centering block and the centering spring, and at the same time applies a downward force in the vertical direction to the positioning block, so that the centering block moves downward in the vertical direction in the tapered hole, and at the same time drives the positioning block and the clamping assembly in each fixing part to move downward in the vertical direction.

[0016] Furthermore, the diameter of the tapered hole gradually decreases from the end furthest from the guide block to the end closest to the guide block.

[0017] Furthermore, one end of the centering block has a cylindrical portion, which is located within the first groove and has a second groove.

[0018] The advantages of adopting the above-mentioned further solution are: one end of the centering block has a cylindrical portion, which facilitates better fitting into the guide block. The other end of the centering block has a tapered portion, which facilitates better sliding with the tapered hole, thereby improving the efficiency of accurately positioning the center of the turbine disk blades.

[0019] Furthermore, the outer wall of the conical portion is provided with a plurality of third grooves at intervals along its circumference. The third grooves are opened along the generatrix direction of the conical portion, and the plurality of third grooves are slidably engaged with the plurality of pressing components one by one.

[0020] The beneficial effects of adopting the above-mentioned further solution are: during the process of driving the centering screw and the guide block to tighten together, the centering screw applies a downward force in the vertical direction to the centering block and the centering spring, and at the same time applies a partial force in the axial direction of the fixed part to the clamping assembly, so that one end of the clamping assembly slides into contact with the inner wall of the turbine disk blade until it abuts and presses against it, and the other end of the clamping assembly slides into contact with the third groove.

[0021] Furthermore, the clamping assembly includes a clamping pin and a clamping spring. A clamping plug is fixed inside the positioning block. One end of the clamping pin slides through the clamping plug and is slidably connected to the positioning block. The other end of the clamping pin passes through the positioning block and is slidably engaged with the third groove. The outer wall of the clamping pin has a radially outwardly extending boss. The clamping spring is sleeved on the clamping pin. One end of the clamping spring abuts against the end face of the boss, and the other end of the clamping spring abuts against the clamping plug, applying an elastic force to the clamping pin to move it away from the clamping plug.

[0022] The beneficial effects of adopting the above-mentioned further solution are as follows: during the process of driving the centering screw to tighten with the guide block thread, the centering screw applies a downward force in the vertical direction to the centering block and the centering spring, and at the same time applies a partial force in the axial direction of the fixed part to the clamping pin and the clamping spring, so that the clamping spring is in a compressed state, and one end of the clamping pin moves in the axial direction of the fixed part and away from the centering block until one end of the clamping pin moves to abut against and press against the inner wall of the turbine disk blade, and a positioning point is formed at the abutment.

[0023] Furthermore, the chassis, the guide block, and the centering block are coaxially arranged.

[0024] The beneficial effects of adopting the above-mentioned further solution are: the coaxially arranged chassis, guide block and centering block can ensure that the centering device will not shift during the centering process of the turbine disk blade, thereby improving the accuracy of positioning the center of the turbine disk blade. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the structure of the aircraft turbine disk blade centering device of this utility model;

[0026] Figure 2 This is a top view of the aircraft turbine disk blade centering device of this utility model;

[0027] Figure 3 for Figure 2 AA section view;

[0028] Figure 4 A partial schematic diagram of a novel aircraft turbine disk blade centering device;

[0029] Figure 5 A schematic diagram of a new type of aircraft turbine disk blade centering device and turbine disk blade assembly;

[0030] Figure 6 for Figure 5 BB cross-sectional view.

[0031] The attached diagram lists the components represented by each number as follows:

[0032] 1. Chassis; 2. Guide block; 3. Positioning block; 301. Tapered hole; 4. Centering assembly; 401. Centering block; 4011. Tapered part; 4012. Cylindrical part; 402. Centering screw; 403. Centering spring; 404. Third groove; 5. Positioning assembly; 6. Fixing part; 601. Pressure plug; 7. Turbine disk blade; 8. Pressure assembly; 801. Pressure pin; 802. Pressure spring. Detailed Implementation

[0033] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0034] like Figures 1-6 As shown, this embodiment provides an aircraft turbine disk blade centering device, including a chassis 1, a centering component 4, and a positioning component 5. The positioning component 5 includes a positioning block 3 and a plurality of clamping components 8. The clamping components 8 are arranged radially along the positioning block 3 and slide in cooperation with the positioning block 3. The plurality of clamping components 8 are arranged circumferentially spaced along the positioning block 3. One end of the centering component 4 is connected to the chassis 1, and the other end of the centering component 4 passes through the positioning block 3 and slides in cooperation with the positioning block 3.

[0035] The centering component 4 moves the positioning component 5 closer to the chassis 1, and one end of the plurality of clamping components 8 extends out of the positioning block 3, or moves the positioning component 5 away from the chassis 1, and one end of the plurality of clamping components 8 retracts into the positioning block 3.

[0036] The turbine blade 7 is placed on the chassis 1, and the centering component 4 is driven to move up and down in the vertical direction, which in turn drives the positioning component 5 to move up and down in the vertical direction until one end of the multiple pressing components 8 extends out of the positioning block and abuts and presses against the inner wall of the turbine blade 7, forming a positioning point at the abutment. The center of the circle formed by the multiple positioning points is the center of the turbine blade 7, thus achieving accurate positioning of the center of the turbine blade 7.

[0037] Specifically, the top of the chassis 1 has a frustum, the end face of which is the mounting surface for the turbine disk blades 7. The chassis 1 is made of stainless steel, which increases the service life of the device.

[0038] In this embodiment, the guide block 2 is a cylinder, located in the middle of the chassis 1, and is threadedly fixed to the chassis 1.

[0039] Based on the above scheme, the positioning block 3 is provided with multiple fixing parts 6 at intervals along its circumference, and multiple pressing components 8 are slidably disposed in one end of the multiple fixing parts 6 respectively. The other end of the pressing component 8 passes through the other end of the fixing part 6 and slides in cooperation with the centering component 4.

[0040] When the centering assembly 4 moves downwards vertically, it simultaneously applies a downward vertical force to the positioning block 3 and an axial force to the clamping assembly 8 along the fixing part 6. The downward vertical force drives both the positioning block 3 and the clamping assembly 8 to move downwards vertically. As the clamping assembly 8 moves downwards vertically, the axial force along the fixing part 6 pushes the clamping assembly 8 to abut and press against the inner wall of the turbine disk blade 7, forming a positioning point at the contact point.

[0041] Specifically, the end of the positioning component 5 along its circumference is the end of one end of the clamping component 8 inside the fixing part 6.

[0042] In this embodiment, the positioning block 3 is evenly spaced with three fixing parts 6 along its circumference, and the three pressing components 8 are slidably sleeved in the three fixing parts 6 in a one-to-one correspondence.

[0043] In addition, the top end face of the positioning block 3 and the top end face of the fixing part 6 are located on the same plane.

[0044] Based on the above scheme, the number of fixing parts 6 is at least three, and the at least three fixing parts 6 are evenly distributed around the positioning block 3.

[0045] Multiple fixing parts 6 can increase the stability of the contact with the inner wall of the turbine disk blades 7.

[0046] Specifically, such as Figure 1As shown, there are three fixing parts 6. However, the number of fixing parts 6 can also be set to four, depending on the actual situation.

[0047] Among them, multiple fixing parts 6 are evenly distributed along the circumferential intervals of the positioning block 3.

[0048] Specifically, such as Figure 2 As shown, there are three fixing parts 6, and the three fixing parts 6 are spaced 120° apart around the positioning block 3.

[0049] The clamping components 8 within the three fixing parts 6 respectively abut and press against the inner wall of the turbine disk blade 7, forming three abutment points on the inner wall of the turbine disk blade 7, thus forming three positioning points. The center of the circle formed by the three positioning points is the center of the turbine disk blade 7, thereby accurately positioning the center of the turbine disk blade.

[0050] Specifically, at least three positioning points are needed to form a circle, and the center of the turbine disk blade 7 can be found through the center of the circle. Therefore, the number of fixing parts 6 is at least three.

[0051] Based on the above scheme, a guide block 2 is also included. The chassis 1 is fixedly connected to the guide block 2, and one end of the centering component 4 is sleeved in the guide block 2 and detachably connected to the guide block 2.

[0052] Based on the above scheme, the centering component 4 includes a centering block 401, a centering screw 402, and a centering spring 403. The positioning block 3 has a tapered hole 301, and the guide block 2 has a first groove. One end of the centering block 401 is located in the first groove, and the other end of the centering block 401 has a tapered portion 4011. The tapered portion 4011 is located in the tapered hole 301 and slides in cooperation with the tapered hole 301. The centering screw 402 passes through the centering block 401 and the first groove in sequence and is threadedly connected to the guide block 2. The centering screw 402 is sleeved with the centering spring 403. One end of the centering block 401 has a second groove. One end of the centering spring 403 abuts against the bottom of the second groove, and the other end of the centering spring 403 abuts against the bottom of the first groove, applying an elastic force to the centering block 401 to move it away from the guide block 2.

[0053] During the process of tightening the centering screw 402 with the guide block 2, the centering screw 402 applies a downward force in the vertical direction to the centering block 401 and the centering spring 403, and at the same time applies a downward force in the vertical direction to the positioning block 3, causing the centering block 401 to move downward in the vertical direction within the tapered hole 301, while simultaneously driving the positioning block 3 and the clamping assembly 8 in each fixing part 6 to move downward in the vertical direction.

[0054] Specifically, the bottom of the guide block 2 has an internal thread, the bottom of the centering screw 402 has an external thread, and the guide block 2 is threadedly connected to the centering screw 402.

[0055] The other end of the centering block 401 is located inside the tapered hole 301 and is clearance-fitted with the tapered hole 301. The positioning block 3 abuts against the centering block 401 through multiple clamping components 8.

[0056] Based on the above scheme, the diameter of the tapered hole 301 gradually decreases from the end away from the guide block 2 to the end closer to the guide block 2.

[0057] Based on the above scheme, one end of the centering block 401 has a cylindrical portion 4012, which is located in the first groove and has the second groove.

[0058] One end of the centering block 401 has a cylindrical portion 4012, which facilitates better fitting into the guide block 2. The other end of the centering block 401 has a tapered portion 4011, which facilitates better sliding with the tapered hole 301 and improves the efficiency of accurately positioning the center of the turbine disk blade 7.

[0059] The tapered portion 4011 and the cylindrical portion 4012 can be fixedly connected or can be two separate parts, with the bottom of the cylindrical portion 4012 fitted inside the guide block 2.

[0060] In addition, the centering screw 402 passes through the tapered portion 4011, the cylindrical portion 4012 and the first groove in sequence, and is threadedly connected to the guide block 2.

[0061] Specifically, the guide block 2, positioning block 3, and centering block 401 are made of stainless steel, which can improve the service life of the device.

[0062] Based on the above scheme, the outer wall of the centering block 401 is provided with a plurality of third grooves 404 at intervals along its circumference, and the plurality of third grooves 404 are slidably engaged with the plurality of pressing components 8 in a one-to-one correspondence.

[0063] During the process of tightening the centering screw 402 and the guide block 2, the centering screw 402 applies a downward force in the vertical direction to the centering block 401 and the centering spring 403, and at the same time applies a partial force in the axial direction of the fixed part 6 to the clamping assembly 8, so that one end of the clamping assembly 8 slides against the inner wall of the turbine disk blade 7 until it abuts and presses against it, and the other end of the clamping assembly 8 slides against the third groove 404.

[0064] Specifically, such as Figure 4 As shown, in this embodiment, the outer wall of the centering block 401 is provided with three third grooves 404 at intervals along its circumference.

[0065] The length of the third groove 404 in the vertical direction is the same as the length of the tapered portion 4011 in the vertical direction.

[0066] In addition, the diameter of the groove 404 gradually decreases from one end to the other.

[0067] Based on the above scheme, the clamping assembly 8 includes a clamping pin 801 and a clamping spring 802. A clamping screw plug 601 is fixed inside the positioning block 3. One end of the clamping pin 801 slides through the clamping screw plug 601 and is slidably connected to the positioning block 3. The other end of the clamping pin 801 passes through the positioning block 3 and is slidably engaged with the third groove 404. The outer wall of the clamping pin 801 has a radially outwardly extending boss. The clamping spring 802 is sleeved on the clamping pin 801. One end of the clamping spring 802 abuts against the end face of the boss, and the other end of the clamping spring 802 abuts against the clamping screw plug 601, and applies an elastic force to the clamping pin 801 to move it away from the clamping screw plug 601.

[0068] During the process of tightening the centering screw 402 with the guide block 2, the centering screw 402 applies a downward force in the vertical direction to the centering block 401 and the centering spring 403, and at the same time applies a partial force in the axial direction of the fixing part 6 to the clamping pin 801 and the clamping spring 802, so that the clamping spring 802 is in a compressed state, and one end of the clamping pin 801 moves in the axial direction of the fixing part 6 away from the centering block 401 until one end of the clamping pin 801 moves to abut against and press against the inner wall of the turbine disk blade 7, and a positioning point is formed at the abutment.

[0069] Specifically, when the clamping pin 801 and the clamping spring 802 are subjected to a partial pressure along the axial direction of the fixing part 6, one end of the clamping pin 801 moves along the axial direction of the fixing part 6 and away from the centering block 401, while the other end of the clamping pin 801 slides downward along the length direction of the third groove 404.

[0070] The compression plug 601 is also located inside the outer end of the fixing part 6.

[0071] Based on the above scheme, the chassis 1, the guide block 2, and the centering block 401 are coaxially arranged.

[0072] The coaxially arranged chassis 1, guide block 2 and centering block 401 ensure that the centering device will not shift during the centering process of the turbine disk blade 7, thereby improving the accuracy of positioning the center of the turbine disk blade 7.

[0073] In this embodiment, when in use, the turbine disk blade 7 is placed on the chassis 1; the drive centering screw 402 is threadedly tightened with the guide block 2, the centering screw 402 applies a downward force in the vertical direction to the centering block 401 and the centering spring 403, and at the same time applies a downward force in the vertical direction to the positioning block 3 and applies a force in the axial direction of the fixing part 6 to the clamping pin 801 and the clamping spring 802 in each fixing part 6;

[0074] The positioning block 3 is subjected to a downward vertical force, which can drive the positioning block 3 to move downward in the vertical direction, thereby simultaneously driving the clamping pin 801 and clamping spring 802 in each fixed part 6 to move downward in the vertical direction as a whole.

[0075] As the clamping pin 801 and clamping spring 802 in each fixing part 6 move downward in the vertical direction, the pressure distribution along the axial direction of the fixing part 6 pushes one end of the clamping pin 801 to move to abut against and press against the inner wall of the turbine disk blade 7, and a positioning point is formed at the abutment.

[0076] The center of the circle formed by multiple positioning points is the center of the turbine disk blade 7. After accurately positioning the center of the turbine disk blade 7, the turbine disk blade 7 is then processed in the next step.

[0077] In the description of this utility model, it should be understood that the terms "center", "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0078] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0079] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0080] In this utility model, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0081] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0082] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A centering device for aircraft turbine disk blades, characterized in that, The system includes a chassis (1), a centering component (4), and a positioning component (5). The positioning component (5) includes a positioning block (3) and a plurality of clamping components (8). The clamping components (8) are arranged radially along the positioning block (3) and slide in cooperation with the positioning block (3). The plurality of clamping components (8) are arranged circumferentially spaced along the positioning block (3). One end of the centering component (4) is connected to the chassis (1), and the other end of the centering component (4) passes through the positioning block (3) and slides in cooperation with the positioning block (3). The centering component (4) moves the positioning component (5) closer to the chassis (1) and one end of the plurality of clamping components (8) extends out of the positioning block (3), or moves the positioning component (5) away from the chassis (1) and one end of the plurality of clamping components (8) retracts into the positioning block (3).

2. The aircraft turbine disk blade centering device according to claim 1, characterized in that, The positioning block (3) is provided with a plurality of fixing parts (6) at intervals along its circumference. A plurality of pressing components (8) are slidably disposed in one end of a plurality of fixing parts (6) respectively. The other end of the pressing component (8) passes through the other end of the fixing part (6) and slides in cooperation with the centering component (4).

3. The aircraft turbine disk blade centering device according to claim 2, characterized in that, The number of the fixing parts (6) is at least three, and the at least three fixing parts (6) are evenly distributed around the positioning block (3).

4. The aircraft turbine disk blade centering device according to claim 1, characterized in that, It also includes a guide block (2), the chassis (1) is fixedly connected to the guide block (2), and one end of the centering component (4) is sleeved in the guide block (2) and detachably connected to the guide block (2).

5. The aircraft turbine disk blade centering device according to claim 4, characterized in that, The centering assembly (4) includes a centering block (401), a centering screw (402), and a centering spring (403). The positioning block (3) has a conical hole (301), and the guide block (2) has a first groove. One end of the centering block (401) is located in the first groove, and the other end of the centering block (401) has a conical portion (4011). The conical portion (4011) is located in the conical hole (301) and slides in cooperation with the conical hole (301). The centering screw... (402) passes through the centering block (401) and the first groove in sequence, and is threadedly connected to the guide block (2). The centering screw (402) is fitted with the centering spring (403). One end of the centering block (401) has a second groove. One end of the centering spring (403) abuts against the bottom of the second groove, and the other end of the centering spring (403) abuts against the bottom of the first groove, and applies an elastic force to the centering block (401) to move it away from the guide block (2).

6. The aircraft turbine disk blade centering device according to claim 5, characterized in that, The diameter of the tapered hole (301) gradually decreases from the end furthest from the guide block (2) to the end closest to the guide block (2).

7. The aircraft turbine disk blade centering device according to claim 5, characterized in that, One end of the centering block (401) has a cylindrical portion (4012), which is located in the first groove and has a second groove.

8. The aircraft turbine disk blade centering device according to claim 5, characterized in that, The outer wall of the tapered portion (4011) is provided with a plurality of third grooves (404) spaced apart along its circumference. The third grooves (404) are opened along the generatrix direction of the tapered portion (4011), and the plurality of third grooves (404) are slidably engaged with the plurality of pressing components (8) one by one.

9. The aircraft turbine disk blade centering device according to claim 8, characterized in that, The clamping assembly (8) includes a clamping pin (801) and a clamping spring (802). A clamping plug (601) is fixed inside the positioning block (3). One end of the clamping pin (801) slides through the clamping plug (601) and is slidably connected to the positioning block (3). The other end of the clamping pin (801) passes through the positioning block (3) and is slidably engaged with the third groove (404). The outer wall of the clamping pin (801) has a radially outwardly extending boss. The clamping pin (801) is sleeved with the clamping spring (802). One end of the clamping spring (802) abuts against the end face of the boss. The other end of the clamping spring (802) abuts against the clamping plug (601) and applies an elastic force to the clamping pin (801) to move it away from the clamping plug (601).

10. The aircraft turbine disk blade centering device according to claim 9, characterized in that, The chassis (1), the guide block (2), and the centering block (401) are coaxially arranged.

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