Clamping device for heat treatment of low-pressure turbine blade of aero-engine

Abstract

The utility model provides an aero-engine low-pressure turbine blade heat treatment clamping device, which relates to the technical field of turbine blade clamping, and comprises a square foot support, the square foot support comprises a plurality of first transverse plates, a plurality of second transverse plates and a plurality of vertical plates, the opposite sides of the adjacent first transverse plates are provided with supporting grooves in a penetrating manner; guide rods are jointly arranged in the opposite supporting grooves in a sliding mode, and turbine blade bodies are jointly arranged on rod bodies of the adjacent guide rods. A worker controls the guide rods to move to enable the guide rods to move in the direction of the supporting grooves, then the worker places a turbine blade body between the adjacent guide rods, the worker controls the guide rods to move again, the adjacent guide rods clamp the turbine blade body, the number of clamping steps is small, the number of single-time clamping is large, and the working efficiency is high. And the contact area of the turbine blade body and the guide rod is small, so that the turbine blade body cannot be polluted by the guide rod in heat treatment.

Description

TECHNICAL FIELD

[0001] The utility model relates to turbine blade clamping technical field, specifically, relate to a kind of aero-engine low pressure turbine blade heat treatment clamping device. BACKGROUND

[0002] Aero-engine low pressure turbine blade is the important component in aero-engine, located at the end of engine, mainly responsible for the high-temperature high-pressure gas energy conversion into mechanical energy, drive engine operation in heat treatment to blade, it needs to use clamping device to clamp it. The existing public number CN221935958U for processing heavy combustion big blade clamping device, the first adjusting positioning block and the second adjusting positioning block of the above utility model are oppositely arranged and installed on the shroud side of big blade of clamp body, third adjusting positioning block is installed between the first adjusting positioning block and the second adjusting positioning block, and the adjusting direction of third adjusting positioning block is towards the shroud side head of big blade;First auxiliary positioning block is installed on the clamp body, and the first auxiliary positioning block is located at the right side of the first adjusting positioning block and the second adjusting positioning block;Fourth adjusting positioning block and fifth adjusting positioning block are oppositely staggered and installed on the big blade root side of clamp body, and fourth adjusting positioning block and fifth adjusting positioning block are supported in the lower part of big blade root;Two press fittings are pressed in the upper part of big blade. The above utility model is used for processing heavy combustion big blade clamping.

[0003] But in the above scheme, since the clamping process of the above-mentioned clamping device to blade is more cumbersome, the clamping quantity is relatively single, so that the time required for blade heat treatment is longer, the production efficiency is affected, and in the clamping process, the contact area between blade and clamping structure is too large, and the blade is easily polluted by tooling when heat treated. UTILITY MODEL CONTENTS

[0004] The main purpose of the utility model is to provide a kind of aero-engine low pressure turbine blade heat treatment clamping device, can effectively solve the clamping process of the clamping device to blade in background art is more cumbersome, clamping quantity is relatively single, so that the time required for blade heat treatment is longer, the production efficiency is affected, and in the clamping process, the contact area between blade and clamping structure is too large, and the blade is easily polluted by tooling when heat treated.

[0005] To achieve the above object, the technical scheme adopted by the utility model is as follows:

[0006] A kind of aero-engine low pressure turbine blade heat treatment clamping device, including four square foot support, the four square foot support includes a plurality of first horizontal plate, second horizontal plate, vertical plate;

[0007] The first transverse plates are provided with support grooves on opposite sides, and guide rods are slidably arranged in the opposite support grooves.

[0008] Preferably, the guide rod is provided with a positioning assembly at both ends.

[0009] Preferably, the positioning assembly comprises a threaded section provided on the corresponding end of the guide rod, and a positioning bolt is arranged on the surface of the threaded section.

[0010] Preferably, the first transverse plate is provided with two first clamping grooves on the surface of the side close to the guide rod, and the second transverse plate is provided with a first clamping block on each side.

[0011] Preferably, the first transverse plate is provided with a second clamping groove on each side of the lower surface, and the vertical plate is provided with a second clamping block on each side.

[0012] Compared with the prior art, the present application has the following advantages:

[0013] (1) The staff controls the movement of the guide rod to move along the direction of the support groove, and then the staff places the turbine blade body between the adjacent guide rods, and then controls the movement of the guide rod again to clamp the turbine blade body, so that the number of clamping steps is reduced, the number of clamping at a time is increased, and the contact area between the turbine blade body and the guide rod is small, so that the turbine blade body is not polluted by the guide rod during heat treatment. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is a whole structure schematic view of the low-pressure turbine blade heat treatment clamping device of the aero-engine.

[0015] Figure 2 It is a front view structure schematic view of the low-pressure turbine blade heat treatment clamping device of the aero-engine.

[0016] Figure 3 It is a sectional structure schematic view of the low-pressure turbine blade heat treatment clamping device of the aero-engine. Figure 2 at A-A.

[0017] Figure 4 It is a sectional structure schematic view of the low-pressure turbine blade heat treatment clamping device of the aero-engine. Figure 2 at B-B.

[0018] Figure 5The utility model relates to an aero-engine low-pressure turbine blade heat treatment clamping device Figure 3 The enlarged schematic view of the structure at position A in the middle;

[0019] Figure 6 The utility model relates to an aero-engine low-pressure turbine blade heat treatment clamping device Figure 4 The enlarged schematic view of the structure at position B in the middle.

[0020] In the figure: 1, square foot support; 101, first cross plate; 102, second cross plate; 103, vertical plate; 2, support groove; 3, guide rod; 4, turbine blade body; 5, positioning assembly; 501, threaded section; 502, positioning bolt; 6, first clamping groove; 7, first clamping block; 8, second clamping groove; 9, second clamping block. DETAILED DESCRIPTION

[0021] The technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the utility model.

[0022] As Figures 1-6 shown, an aero-engine low-pressure turbine blade heat treatment clamping device, including square foot support 1, square foot support 1 includes a plurality of first cross plate 101, second cross plate 102, vertical plate 103;

[0023] The opposite side of adjacent first cross plate 101 is provided with support groove 2, and the opposite support grooves 2 are provided with guide rod 3, and the adjacent guide rod 3 is provided with turbine blade body 4.

[0024] The staff controls the movement of guide rod 3, so that it moves along the direction of support groove 2, then the staff places turbine blade body 4 between adjacent guide rods 3, and then the staff controls the movement of guide rod 3 again, so that adjacent guide rods 3 clamp turbine blade body 4, the clamping steps are less, the single clamping quantity is more, and the contact area of turbine blade body 4 and guide rod 3 is small, so that turbine blade body 4 is not polluted by guide rod 3 in heat treatment.

[0025] In another embodiment of the utility model, the both ends of the guide rod 3 are provided with the positioning assembly 5 for positioning.

[0026] The positioning assembly 5 includes threaded section 501, threaded section 501 is provided in the corresponding end of guide rod 3, and the surface of threaded section 501 is provided with positioning bolt 502.

[0027] After the guide rod 3 clamps the turbine blade body 4, the worker rotates the positioning bolt 502, moves along the threaded section 501, is tightly attached with the side corresponding to the first transverse plate 101, so that the guide rod 3 position is fixed, and the turbine blade body 4 is prevented from falling.

[0028] In another embodiment of the utility model, two first clamping grooves 6 are arranged on the surface of each first transverse plate 101 close to the guide rod 3, and each second transverse plate 102 is fixedly provided with a first clamping block 7 on both sides, and each first clamping groove 6 is inserted into the corresponding first clamping block 7.

[0029] The lower surface of each first transverse plate 101 is provided with a second clamping groove 8 on both sides, and each vertical plate 103 is fixedly provided with a second clamping block 9 on both sides, and each second clamping block 9 is inserted into the corresponding second clamping groove 8.

[0030] The first clamping groove 6 and the first clamping block 7 are arranged, so that the worker can quickly disassemble the first transverse plate 101 and the second transverse plate 102, the second clamping groove 8 and the second clamping block 9 are arranged, so that the worker can disassemble the first transverse plate 101 and the vertical plate 103, and the worker can store the four-square foot support 1.

[0031] The working principle of the low-pressure turbine blade heat treatment clamping device of the aircraft engine is as follows:

[0032] In use, the worker controls the movement of the guide rod 3, so that the guide rod 3 moves along the supporting groove 2, then the worker places the turbine blade body 4 between the adjacent guide rods 3, and then the worker controls the movement of the guide rod 3 again, so that the adjacent guide rods 3 clamp the turbine blade body 4, the clamping steps are less, the number of single clamping is more, and the contact area between the turbine blade body 4 and the guide rod 3 is small, so that the turbine blade body 4 is not polluted by the guide rod 3 in the heat treatment.

[0033] Obviously, the above embodiments of the utility model are only examples for clearly illustrating the utility model, and are not the limitation of the utility model embodiments, and for ordinary skilled in the art, other different forms of changes or changes can be made on the basis of the above description, and all the embodiments cannot be exhausted, and all the embodiments of the utility model are still within the protection scope of the utility model.

Claims

1. An aeroengine low pressure turbine blade heat treatment clamping device comprising a square foot support (1), characterized in that: The quadrilateral foot support (1) comprises a plurality of first horizontal plates (101), second horizontal plates (102) and vertical plates (103); Opposite sides of adjacent first horizontal plates (101) are provided with support grooves (2), opposite support grooves (2) are provided with guide rods (3) that slide together, and adjacent guide rods (3) are provided with turbine blade bodies (4) that slide together.

2. The aero-engine low pressure turbine blade heat treatment clamping device according to claim 1, characterized in that: Both ends of the guide rod (3) are provided with positioning components (5) for positioning.

3. The aero-engine low pressure turbine blade heat treatment clamping device according to claim 2, characterized in that: The positioning component (5) comprises a threaded section (501) provided at a corresponding end of the guide rod (3), and the threaded section (501) is provided with a positioning bolt (502) that is threaded on the surface.

4. The aero-engine low pressure turbine blade heat treatment clamping device according to claim 3, characterized in that: Each first horizontal plate (101) is provided with two first clamping grooves (6) on the side surface near the guide rod (3), each second horizontal plate (102) is provided with a first clamping block (7) on both sides, and each first clamping groove (6) is in penetrating cooperation with a corresponding first clamping block (7).

5. The aero-engine low pressure turbine blade heat treatment clamping device according to claim 4, characterized in that: Each first horizontal plate (101) is provided with a second clamping groove (8) on the lower surface on both sides, each vertical plate (103) is provided with a second clamping block (9) on both sides, and each second clamping block (9) is in penetrating cooperation with a corresponding second clamping groove (8).

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