Turbojet engine guider roundness rapid correction device

Abstract

A rapid roundness correction device for a guider of a turbojet engine relates to the technical field of correction devices and comprises a bottom platform, a shape correction seat matched with the guider is arranged on the upper surface of the bottom platform, a positioning block is vertically lifted above the shape correction seat, and a guider correction area is formed by an area between the shape correction seat and the positioning block. And a cooling structure is arranged in the bottom platform. According to the utility model, the problems that the efficiency of a guider roundness measurement mode in the prior art is low, and after the guider roundness is measured, the guider needs to be put into a correction tool for correction operation, so that the operation is tedious, time-consuming and labor-consuming are solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of correction device, concretely relates to turbojet engine guider roundness quick correction device. BACKGROUND

[0002] The turbine guider is an important component of the gas turbine engine, and its main role is to change the flow direction of the gas to drive the turbine blade to rotate and generate power.

[0003] The existing device gradually exposes the deficiencies of the technology with use, mainly showing in the following aspects:

[0004] First, the existing guider roundness measurement mainly has two ways, one is measured by vernier caliper, and the distance between points is measured, that is, the diameter of the guider, and then the difference of the diameter in different positions is the roundness, this method is low in efficiency and large in error, and the efficiency cannot meet the production needs in batch production, the second is to use three coordinate detection instrument, this method is accurate in measurement, but has problems of low efficiency and high cost, and is used for small materials.

[0005] Second, after the existing guider roundness measurement, the guider still needs to be put into the correction tool for correction operation, which is tedious and time-consuming.

[0006] From the above, it is obvious that the prior art has inconvenience and defects in actual use, so it is necessary to improve. INVENTION CONTENTS

[0007] In view of the defects in the prior art, the utility model provides a turbojet engine guider roundness quick correction device to solve the problems that the guider roundness measurement method in the traditional technology is low in efficiency, and after the guider roundness measurement, the guider still needs to be put into the correction tool for correction operation, which is tedious and time-consuming.

[0008] To achieve the above purpose, the utility model provides the following technical scheme:

[0009] The turbojet engine guider roundness quick correction device comprises a bottom platform, the upper surface of the bottom platform is provided with a profile correcting seat matched with the guider, a positioning block is vertically lifted above the profile correcting seat, and a guider correction area is formed between the profile correcting seat and the positioning block,

[0010] The bottom platform is internally provided with a cooling structure.

[0011] As an optimized scheme, the cooling structure comprises a cooling water channel in the form of M arranged in the interior of the bottom platform.

[0012] As an optimization scheme, the side wall of the bottom platform is provided with a water inlet and a water outlet respectively connected with the cooling water channel.

[0013] As an optimization scheme, the upper surface of the bottom platform is provided with a positioning groove, and the lower end of the type correcting seat is clamped in the positioning groove.

[0014] As an optimization scheme, the lower end of the positioning block is provided with a reduced diameter positioning section inserted into the guide.

[0015] As an optimization scheme, the upper side of the bottom platform is fixed with a top plate in parallel, the top plate is vertically screw-connected with a screw rod, and the lower end of the screw rod is fixedly connected with the upper surface of the positioning block.

[0016] As an optimization scheme, the top plate is vertically and fixedly connected with a threaded sleeve in a penetrating mode, and the screw rod is screw-connected with the threaded sleeve.

[0017] As an optimization scheme, the bottom platform is fixedly connected with two side plates in parallel, and the lower surface of the top plate is fixedly connected with the upper end of the two side plates.

[0018] As an optimization scheme, the upper end of the side plate and the top plate and the lower end of the side plate and the bottom platform are respectively connected through a bolt assembly.

[0019] Compared with the prior art, the utility model has the beneficial effects that:

[0020] By using the tool, the roundness of the guide can be directly corrected, the work of measuring the roundness of the guide is saved, and the labor intensity is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the specific embodiment of the utility model or the technical scheme in the prior art, the drawings needed to be used in the specific embodiment or the prior art description will be briefly introduced below. In all the drawings, similar elements or parts are generally indicated by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual proportion.

[0022] Figure 1 It is a structural schematic view of the utility model;

[0023] Figure 2 It is a structural schematic view of the cooling water channel of the utility model.

[0024] In the drawings: 1 - bottom platform; 2 - type correcting seat; 3 - positioning block; 4 - guide; 5 - water inlet; 6 - water outlet; 7 - cooling water channel; 8 - top plate; 9 - threaded sleeve; 10 - screw rod; 11 - side plate; 12 - bolt assembly. DETAILED DESCRIPTION

[0025] The embodiments of the technical scheme of the utility model will be described in detail below with reference to the drawings. The following embodiments are only used to more clearly illustrate the technical scheme of the utility model, therefore only as an example, and cannot limit the protection scope of the utility model.

[0026] As shown in Figure 1 and Figure 2 The quick correction device for the roundness of the guide vane of the turbojet engine comprises a bottom platform 1, the upper surface of the bottom platform 1 is provided with a type correction seat 2 matched with the guide vane 4, the positioning block 3 is vertically lifted above the type correction seat 2, and the guide vane 4 correction area is formed through the area between the type correction seat 2 and the positioning block 3,

[0027] The inside of the bottom platform 1 is provided with a cooling structure.

[0028] The cooling structure comprises a cooling waterway 7 in the shape of M arranged in the inside of the bottom platform 1.

[0029] The side wall of the bottom platform 1 is respectively provided with a water inlet 5 and a water outlet 6 communicated with the cooling waterway 7.

[0030] The upper surface of the bottom platform 1 is provided with a positioning groove, and the lower end of the type correction seat 2 is clamped in the positioning groove.

[0031] The lower end of the positioning block 3 is provided with a reduced diameter positioning section inserted into the guide vane 4.

[0032] The top plate 8 is fixed above the bottom platform 1 in parallel, the screw rod 10 is vertically screw connected on the top plate 8, and the lower end of the screw rod 10 is fixedly connected with the upper surface of the positioning block 3.

[0033] The threaded sleeve 9 is vertically and penetratingly fixed on the top plate 8, and the screw rod 10 is screw connected on the threaded sleeve 9.

[0034] Two side plates 11 are fixed on the bottom platform 1 in parallel, and the lower surface of the top plate 8 is fixed on the upper end of the two side plates 11 in parallel.

[0035] The upper end of the side plate 11 and the top plate 8, and the lower end of the side plate 11 and the bottom platform 1 are respectively connected through the bolt assembly 12.

[0036] The working principle of the device is as follows:

[0037] The heated guide vane 4 is placed on the type correction seat 2, and the workpiece can be easily placed on the type correction seat 2 due to the size increase after heating;

[0038] The screw rod 10 moves downward with the positioning block 3, presses and positions the workpiece, opens the water inlet pipe, and the cooling water passes through the cooling water path 7 to accelerate the cooling of the bottom platform 1, releases the stress of the heated workpiece, and corrects the roundness.

[0039] By using the tool, the roundness of the guide 4 can be directly corrected, the work of measuring the roundness of the guide 4 is saved, and the tool is convenient and fast, and the labor intensity is reduced.

[0040] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should be covered in the scope of the claims and the description of the present application.

Claims

1. A device for rapid correction of the roundness of a turbojet engine guide vane, characterized in that: The application relates to a guiding device for guiding a guide (4), which comprises a bottom platform (1), wherein the upper surface of the bottom platform (1) is provided with a type-checking seat (2) matched with the guide (4), the type-checking seat (2) is vertically lifted above the positioning block (3), and a guide correction area is formed through the area between the type-checking seat (2) and the positioning block (3). The bottom platform (1) is internally provided with a cooling structure.

2. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 1, characterized in that: The cooling structure comprises an M-shaped cooling water channel (7) arranged in the bottom platform (1).

3. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 2, characterized in that: The side wall of the bottom platform (1) is respectively provided with a water inlet (5) and a water outlet (6) communicated with the cooling water channel (7).

4. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 1, characterized in that: The upper surface of the bottom platform (1) is provided with a positioning groove, and the lower end of the type-checking seat (2) is clamped in the positioning groove.

5. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 1, characterized in that: The lower end of the positioning block (3) is provided with a reduced-diameter positioning section inserted into the guide (4).

6. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 1, characterized in that: The upper surface of the bottom platform (1) is provided with a top plate (8) fixed in parallel, the top plate (8) is vertically screwed with a screw rod (10), and the lower end of the screw rod (10) is fixedly connected with the upper surface of the positioning block (3).

7. The quick correction device for roundness of a guide vane of a turbojet engine according to claim 6, characterized in that: The top plate (8) is vertically and penetratingly fixedly connected with a threaded sleeve (9), and the screw rod (10) is screwed on the threaded sleeve (9).

8. The quick correction device for roundness of a variable stator vane of a turbojet engine according to claim 7, characterized in that: The bottom platform (1) is fixedly connected with two side plates (11) in parallel, and the lower surface of the top plate (8) is fixedly connected with the upper end of the two side plates (11).

9. The quick correction device for roundness of a variable stator vane of a turbojet engine according to claim 8, characterized in that: The upper end of the side plate (11) and the top plate (8) and the lower end of the side plate (11) and the bottom platform (1) are respectively connected through a bolt assembly (12).

Images