Zero-point positioning clamp special for aero-engine moving blade

Abstract

The utility model provides a special zero-point positioning clamp for an aero-engine moving blade, which is used for positioning and clamping the aero-engine moving blade and comprises a clamp body, a positioning piece, a deformation acting piece and a zero-point positioning assembly, a mortise with at least the top, the front and the back opened is arranged on the clamp body, a deformation groove is arranged on one side of the mortise, and the zero-point positioning assembly is arranged in the deformation groove. The deformation acting piece is connected with the deformation part and the clamp body in a matched mode, and the deformation acting piece drives the deformation part to deform so as to clamp and loosen the blade tenon. The zero point positioning assembly comprises a positioning piece and a blind rivet, and the positioning piece and the blind rivet are installed at the bottom of the clamp body in a positioning mode. According to the scheme, assembling is easy, using is convenient, stable clamping of the aero-engine moving blade and the quick-changing function and the zero-point positioning function applied to an automatic production line can be achieved, it is not needed to determine whether the position of the blade is correct or not every time of metering, manpower consumption is reduced, labor efficiency is improved, and the requirement of the automatic production line is met.

Description

Technical Field

[0001] The utility model relates to the technical field of tooling fixtures, and in particular to a special zero-point positioning fixture for aircraft engine moving blades in the field of air film hole processing on the surface of aircraft engine moving blades in an automated production line. Background Art

[0002] At present, the country is vigorously developing industrial intelligence, and the processing of air film holes in aircraft engine blades is becoming more and more intelligent. Through the automated production line, workers only need to put the parts to be processed in the parts loading and unloading station. After the parts enter the line, the bus robot is responsible for the turnover, and finally completes the inspection and processing of the parts. Therefore, accurate positioning of the workpiece is the premise and guarantee of accurate processing.

[0003] Since aircraft engine blades are curved surfaces, the positions of the air film holes to be processed are relatively complex. Before processing, it is necessary to determine whether the aircraft engine blades have been installed in the correct installation positions of the pinhole machine and the measuring machine. Otherwise, it is difficult to ensure accuracy, and the processing will also result in the output of waste due to deviations in the installation position.

[0004] In the process of implementing the present utility model, the applicant found that the conventional fixtures have at least the following problems:

[0005] 1. Existing conventional fixtures cannot guarantee the precise positioning of aircraft engine blades, which will lead to precision problems in the processing of air film holes on the blades.

[0006] 2. The use of existing conventional fixtures and fixtures cannot achieve zero-point quick change in the automated production line, resulting in low processing efficiency.

[0007] In view of this, how to solve the problems of the inability to guarantee positioning accuracy and the inability to achieve zero-point quick change during the processing of the above-mentioned aero-engine blade workpieces in the automated production line has become the research content of this topic. Utility Model Content

[0008] The utility model provides a special zero-point positioning fixture for moving blades of an aero-engine.

[0009] In order to achieve the above-mentioned purpose, the technical solution adopted by the utility model is: a special zero-point positioning fixture for aircraft engine moving blades, which is used for positioning and clamping aircraft engine moving blades. The aircraft engine moving blades have blade tenons, and the innovation lies in:

[0010] The zero-point positioning fixture comprises a clamp body, a positioning member, a deformation acting member, and a zero-point positioning assembly;

[0011] The clamp body is provided with a tenon groove which is open at least at the top and front and back, the contour shape of the tenon groove matches the blade tenon so that the blade tenon can slide forward and backward along the axis, the positioning member is arranged on the sliding path of the blade tenon on the tenon groove, and the positioning member abuts against the blade tenon so that the clamping of the aircraft engine moving blade is positioned;

[0012] The clamp body is provided with a deformation groove on one side of the tenon groove, and the area between the deformation groove and the tenon groove constitutes a deformation part;

[0013] The deformation acting member is cooperatively connected with the deformation part and the clamp body, and the deformation acting member drives the deformation part to deform so as to clamp and loosen the blade tenon;

[0014] The zero point positioning assembly comprises a positioning piece and a rivet, and the positioning piece and the rivet are positioned and installed at the bottom of the clamp body.

[0015] The relevant contents in the above technical solution are explained as follows:

[0016] 1. In the present utility model, in view of the fact that conventional tooling fixtures cannot guarantee the precise positioning of the aero-engine blades during the surface air film hole processing of such aero-engine moving blades, and cannot realize zero-point quick change in the automated production line, resulting in poor processing accuracy and low efficiency of the air film holes on the blades, a special zero-point positioning fixture for aero-engine moving blades is designed. The zero-point positioning fixture can be used to quickly and accurately position and zero-point position the aero-engine blades. The zero-point positioning fixture consists of a clamp body, a positioning member, a deformation acting member, and a zero-point positioning assembly. The clamp body is provided with a tenon groove for slidingly assembling the blade tenon and a deformation groove and a deformation part for deformation clamping. The blade tenon slides back and forth along the tenon groove and is accurately positioned by the positioning member. After positioning, the deformation acting member drives the deformation part to deform to clamp the blade tenon, thereby quickly and accurately positioning the aero-engine blade. The zero-point positioning assembly on the zero-point positioning fixture can be quickly connected with an external standard chuck through a rivet action to realize zero-point quick change. Therefore, the zero-point positioning fixture of the utility model is simple to assemble and easy to use. It can realize stable clamping of aircraft engine moving blades and the quick change function and zero-point positioning function applied in automated production lines. There is no need to use a meter to determine whether the blade position is correct each time, which reduces manpower consumption, improves labor efficiency, and adapts to the needs of automated production lines.

[0017] 2. In the above scheme, the deformation groove is an L-shaped groove, so that the deformation part can produce stable, reliable and accurate deformation under the action of the deformation action member, but the utility model is not limited to this, and the deformation groove can also be C-shaped or a combination of a straight line and an arc, a combination of arcs and arcs, etc.

[0018] 3. In the above scheme, the deformation acting member passes through the deformation groove from the outside of the clamp body in a direction perpendicular to the sliding path of the blade tenon and is connected to the deformation part, so that the deformation generated by the deformation part can be roughly perpendicular to the axis of the blade tenon, so that the blade tenon can ensure accurate position when clamped by the deformation part.

[0019] 4. In the above technical solution, the deformation acting member is a butterfly-shaped fastening screw, which is easy and quick to operate and can reliably and stably deform the deformation part to clamp and loosen the blade tenon.

[0020] 5. In the above technical solution, the positioning member is a positioning ball rod, and the positioning ball rod includes a ball portion and a rod portion. The use of this structure is stable and reliable.

[0021] 6. In the above technical solution, the ball part is configured such that when the front end of the blade tenon slides along the axis and is flush with the front end of the clamp body, the ball part abuts against the front end of the blade tenon to perform positioning. That is, the rearward side of the ball part is flush with the front end of the tenon groove.

[0022] 7. In the above technical solution, a toothed profile is provided at the profile of the tenon groove so that the blade tenon of the aircraft engine moving blade can be reliably clamped.

[0023] 8. In the above technical solution, the tooth profile of the tooth profile is 0.05, so as to further allow the blade to be stably clamped.

[0024] 9. In this utility model, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0025] 10. In the present utility model, the orientation or position relationship indicated by the terms "center", "upper", "lower", "axial", "bottom", "inner", "outer", etc. is based on the orientation or position assembly relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application.

[0026] 11. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0027] Due to the application of the above scheme, the utility model has the following advantages and effects compared with the prior art:

[0028] 1. In the above scheme of the utility model, the zero-point positioning fixture can be used to quickly and accurately position and zero-point position the aircraft engine blade. The zero-point positioning fixture consists of a clamp body, a positioning member, a deformation-acting member, and a zero-point positioning assembly. The clamp body is provided with a tenon for slidingly assembling the blade tenon and a deformation groove and a deformation part for deformation clamping. The blade tenon slides back and forth along the tenon groove and is accurately positioned by the positioning member. After positioning, the deformation-acting member drives the deformation part to deform to clamp the blade tenon, thereby quickly and accurately positioning the aircraft engine blade. The zero-point positioning assembly on the zero-point positioning fixture can be quickly connected to an external standard chuck through a rivet action to achieve zero-point quick change.

[0029] 2. In the above scheme of the utility model, the zero-point positioning fixture is simple to assemble and easy to use. It can realize the stable clamping of aircraft engine moving blades and the quick change function and zero-point positioning function applied in the automated production line. There is no need to use a meter every time to determine whether the blade position is correct or not, which reduces manpower consumption, improves labor efficiency, and adapts to the needs of automated production lines. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a three-dimensional structural schematic diagram of a zero-point positioning fixture dedicated to a rotor blade of an aero-engine according to an embodiment of the utility model;

[0031] Figure 2 This is an exploded schematic diagram of a zero-point positioning fixture dedicated to a rotor blade of an aero-engine according to an embodiment of the utility model;

[0032] Figure 3 It is a three-dimensional schematic diagram of a clamping structure in an embodiment of the utility model;

[0033] Figure 4 It is a top view of a specific embodiment of the utility model;

[0034] Figure 5 It is a specific cross-sectional view of an embodiment of the present invention.

[0035] In the above attached figure:

[0036] 1 Clamp body

[0037] 11. Mortise and tenon

[0038] 111 Tooth profile

[0039] 12 Deformation groove

[0040] 13 Deformation

[0041] 2 Positioning parts

[0042] 21 Ball

[0043] 22 Rod

[0044] 3 Deformation effect parts

[0045] 4 Zero point positioning components

[0046] 41 Positioning piece

[0047] 42 Pull nail

[0048] 9 Aircraft engine rotor blades

[0049] 91 Blade tenon. DETAILED DESCRIPTION

[0050] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present application. However, the present application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present application, so the present application is not limited by the specific embodiments disclosed below.

[0051] The utility model aims to design a special zero-point positioning fixture for aircraft engine moving blades in order to solve the problems that conventional tooling fixtures cannot guarantee the precise positioning of the aircraft engine blades and cannot realize zero-point quick change in the automated production line during the processing of the air film holes on the blades, resulting in poor processing accuracy and low efficiency of the air film holes on the blades. The zero-point positioning fixture can be used to quickly and accurately position and zero-point the aircraft engine blades.

[0052] The following describes it in detail with reference to specific embodiments.

[0053] refer to Figure 1 , Figure 2 As shown, an embodiment of the utility model proposes a zero-point positioning fixture dedicated to aircraft engine moving blades, which is used for positioning and clamping aircraft engine moving blades 9. The aircraft engine moving blades 9 have blade tenons 91. The zero-point positioning fixture includes a clamp body 1, a positioning member 2, a deformation acting member 3, and a zero-point positioning component 4.

[0054] In the embodiment of the utility model, Figures 3 to 5 As shown, the clamp body 1 is provided with a tenon groove 11 which is open at least at the top and front and back. The contour shape of the tenon groove 11 matches the blade tenon 91 so that the blade tenon 91 can slide forward and backward along the axis. The positioning member 2 is arranged on the sliding path of the blade tenon 91 on the tenon groove 11. The positioning member 2 abuts against the blade tenon 91 to position the aircraft engine moving blade 9 during clamping. The clamp body 1 is provided with a deformation groove 12 on one side of the tenon groove 11. The portion between the deformation groove 12 and the tenon groove 11 constitutes a deformation portion 13. Figure 1 , Figure 2 As shown, the deformation acting member 3 is cooperatively connected with the deformation part 13 and the clamp body 1, and the deformation acting member 3 drives the deformation part 13 to deform so as to clamp and loosen the blade tenon 91; the zero point positioning component 4 includes a positioning piece 41 and a rivet 42, and the positioning piece 41 and the rivet 42 are positioned and installed at the bottom of the clamp body 1.

[0055] Through the implementation of the embodiment of the utility model, a special zero-point positioning fixture for aircraft engine moving blades is designed. The zero-point positioning fixture can be used to quickly and accurately position and zero-point position the aircraft engine blades. The zero-point positioning fixture consists of a clamp body 1, a positioning member 2, a deformation action member 3, and a zero-point positioning component 4. The clamp body 1 is provided with a tenon 11 for slidingly assembling the blade tenon 91 and a deformation groove 12 and a deformation part 13 for deformation clamping. The blade tenon 91 slides back and forth along the tenon 11 and is accurately positioned by the positioning member 2. After positioning, the deformation action member 3 drives the deformation part 13 to deform to clamp the blade tenon 91, thereby quickly and accurately positioning the aircraft engine blades, and the zero-point positioning component 4 on the zero-point positioning fixture can be quickly connected to an external standard chuck through the action of a rivet 42 to achieve zero-point quick change. Therefore, the zero-point positioning fixture of the utility model is simple to assemble and easy to use. It can achieve stable clamping of the aircraft engine moving blades 9 and the quick change function and zero-point positioning function used in the automated production line. There is no need to use a meter every time to determine whether the blade position is correct or not, which reduces manpower consumption, improves labor efficiency, and adapts to the needs of the automated production line.

[0056] In the embodiment of the utility model, the deformation groove 12 is an L-shaped groove, so that the deformation part 13 can produce stable, reliable and precise deformation under the action of the deformation acting member 3, but the utility model is not limited to this. The deformation groove 12 can also be C-shaped or a combination of straight lines and arcs, a combination of arcs and arcs, etc.

[0057] In the embodiment of the utility model, the deformation member 3 passes through the deformation groove 12 from the outside of the clamp body 1 in a direction perpendicular to the sliding path of the blade tenon 91 and is connected to the deformation part 13, so that the deformation generated by the deformation part 13 can be roughly perpendicular to the axis of the blade tenon 91, so that the blade tenon 91 can ensure accurate position when clamped by the deformation part 13. Specifically, the deformation member 3 is a butterfly fastening screw, which is easy and fast to operate, and can reliably and stably deform the deformation part 13 to clamp and loosen the blade tenon 91.

[0058] In the embodiment of the utility model, the positioning member 2 is a positioning ball rod, which includes a ball portion 21 and a rod portion 22. The structure is stable and reliable. Specifically, the ball portion 21 is configured such that when the front end of the blade tenon 91 slides along the axis and is flush with the front end of the clamp body 1, the ball portion 21 abuts against the front end of the blade tenon 91 to perform positioning. That is, the rearward side of the ball portion 21 is flush with the front end of the tenon groove 11.

[0059] In an embodiment of the utility model, a toothed profile 111 is provided at the contour of the tenon groove 11 so that the blade tenon 91 of the aircraft engine moving blade 9 can be reliably clamped. Specifically, the toothed profile 111 has a toothed profile degree of 0.05 so as to further allow the blade to be stably clamped.

[0060] The solution of the utility model is described below with a specific detailed embodiment.

[0061] In a zero-point positioning fixture dedicated to aircraft engine moving blades proposed in this detailed embodiment, the zero-point positioning fixture includes a clamp body 1, a positioning member 2, a deformation acting member 3, and a zero-point positioning component 4.

[0062] In this detailed embodiment, the clamp body 1 is provided with a tenon groove 11 which is open at least at the top and front and back. The contour shape of the tenon groove 11 matches the blade tenon 91 so that the blade tenon 91 can slide forward and backward along the axis. The contour of the tenon groove 11 is provided with a toothed profile 111, and the toothed profile degree of the toothed profile 111 is 0.05, so as to further stably clamp the blade. The positioning member 2 is arranged on the sliding path of the blade tenon 91 on the tenon groove 11. The positioning member 2 is a positioning ball rod, and the positioning ball rod includes a ball portion 21 and a rod portion 22. When the front end of the blade tenon 91 slides along the axis and is flush with the front end of the clamp body 1, the ball portion 21 is abutted against the front end of the blade tenon 91 for positioning. That is, the rearward side of the ball portion 21 is flush with the front end of the tenon groove 11.

[0063] In this detailed embodiment, a deformation groove 12 is provided on one side of the tenon 11 on the clamp body 1, and the deformation groove 12 is an L-shaped groove, and the portion between the deformation groove 12 and the tenon 11 constitutes a deformation portion 13; the deformation acting member 3 is cooperatively connected with the deformation portion 13 and the clamp body 1, and the deformation acting member 3 is a butterfly fastening screw, and the deformation acting member 3 passes through the deformation groove 12 from the outside of the clamp body 1 in a direction perpendicular to the sliding path of the blade tenon 91 and is connected to the deformation portion 13, so that the deformation generated by the deformation portion 13 can be roughly perpendicular to the axis of the blade tenon 91, and the deformation acting member 3 drives the deformation portion 13 to deform so as to clamp and loosen the blade tenon 91.

[0064] In this detailed embodiment, the zero-point positioning assembly 4 includes a positioning piece 41 and a rivet 42 , and the positioning piece 41 and the rivet 42 are positioned and installed at the bottom of the clamp body 1 .

[0065] The use and assembly process of a zero-point positioning fixture for aero-engine moving blades in this detailed embodiment is as follows: Figure 2 As shown, the assembly process is divided into 5 steps:

[0066] 1. Insert the blade tenon 91 into the tenon groove 11 of the clamp body 1 along the tooth surface symmetry axis of the tenon groove 11 profile of the clamp body 1.

[0067] 2. Adjust the axial spacing so that the side surface of the blade tenon 91 is in point contact with the ball portion 21 of the positioning member 2.

[0068] 3. Tighten the butterfly-shaped fastening screws to clamp the aircraft engine moving blades 9 through the elastic deformation of the material.

[0069] 4. Fix the zero point positioning assembly 4 to the mounting hole of the clamp body 1.

[0070] 5. The zero point positioning of the aircraft engine moving blade 9 is completed by connecting it with the standard chuck through the rivet 42.

[0071] It can be seen from the above implementation steps that the zero-point positioning fixture of the utility model is simple to assemble and easy to use. It can achieve stable clamping of blades and quick change function and zero-point positioning function in automated production lines. There is no need to use a meter every time to determine whether the blade position is correct or not, which reduces manpower consumption, improves labor efficiency, and adapts to the needs of automated production lines.

[0072] The above embodiments are only for illustrating the technical concept and features of the utility model, and their purpose is to enable people familiar with the technology to understand the content of the utility model and implement it accordingly, and they cannot be used to limit the protection scope of the utility model. Any equivalent changes or modifications made according to the spirit of the utility model should be included in the protection scope of the utility model.

Claims

1. A zero-point positioning fixture for an aircraft engine moving blade, used for positioning and clamping an aircraft engine moving blade (9), wherein the aircraft engine moving blade (9) has a blade tenon (91), characterized in that: The zero-point positioning fixture comprises a clamp body (1), a positioning member (2), a deformation acting member (3), and a zero-point positioning component (4); The clamp body (1) is provided with a tenon groove (11) which is open at least at the top and front and back, the contour shape of the tenon groove (11) matches the blade tenon (91) so that the blade tenon (91) can slide forward and backward along the axis, and the positioning member (2) is arranged on the sliding path of the blade tenon (91) on the tenon groove (11), and the positioning member (2) and the blade tenon (91) are abutted against each other so that the aircraft engine moving blade (9) is clamped and positioned; The clamp body (1) is provided with a deformation groove (12) on one side of the tenon groove (11), and the area between the deformation groove (12) and the tenon groove (11) constitutes a deformation portion (13); The deformation acting member (3) is cooperatively connected with the deformation part (13) and the clamp body (1), and the deformation acting member (3) drives the deformation part (13) to deform so as to clamp and release the blade tenon (91); The zero point positioning assembly (4) comprises a positioning piece (41) and a pull nail (42), and the positioning piece (41) and the pull nail (42) are positioned and installed at the bottom of the clamp body (1).

2. The zero-point positioning fixture for aircraft engine moving blades according to claim 1, characterized in that: The deformation groove (12) is an L-shaped groove.

3. The zero-point positioning fixture for aircraft engine moving blades according to claim 1, characterized in that: The deformation acting member (3) passes through the deformation groove (12) from the outside of the clamp body (1) in a direction perpendicular to the sliding path of the blade tenon (91) and is connected to the deformation part (13).

4. The zero-point positioning fixture for aircraft engine moving blades according to claim 3 is characterized by: The deformation acting member (3) is a butterfly-shaped fastening screw.

5. The zero-point positioning fixture for aircraft engine moving blades according to claim 1, characterized in that: The positioning member (2) is a positioning ball rod, and the positioning ball rod comprises a ball portion (21) and a rod portion (22).

6. A zero-point positioning fixture for aircraft engine moving blades according to claim 5, characterized in that: The ball portion (21) is configured such that when the front end of the blade tenon (91) slides along the axis and is flush with the front end of the clamp body (1), the ball portion (21) abuts against the front end of the blade tenon (91) for positioning.

7. The zero-point positioning fixture for aircraft engine moving blades according to claim 1, characterized in that: A toothed profile (111) is provided at the profile of the tenon groove (11).

8. The zero-point positioning fixture for aircraft engine moving blades according to claim 7, characterized in that: The tooth profile accuracy of the tooth profile (111) is 0.05.

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