Tool clamp for aero-engine blade disc

Abstract

The utility model discloses a frock clamp for aero-engine bladed disc, including base and mounting post, mounting post is installed on the top of base, its characterized in that: the side edge of mounting post is located the moving plate, on the mounting post passes through the limit post, moving plate, limit post and mounting post mutually cooperate to realize the clamping fixation. According to the tool clamp for the aero-engine bladed disc, aero-engine bladed discs of different specifications can be limited through the arrangement of the mounting columns, the aero-engine bladed discs are kept in the middle positions through the mounting columns, stress on the peripheries of the aero-engine bladed discs is the same, damage to the aero-engine bladed discs is reduced, machining of the aero-engine bladed discs is facilitated, and the machining efficiency is improved. The movable plate moves in the horizontal direction through the special structure of the through groove, and the positions of the limiting columns on the periphery are changed through movement of the movable plate.

Description

TECHNICAL FIELD

[0001] The utility model relates to tool fixture technical field, concretely is a tool fixture for aero -engine blade disc. BACKGROUND

[0002] The aero -engine is a kind of highly complex and precision thermodynamic machinery, as the heart of aircraft, not only the power of aircraft flight, also is the important impetus to promote the development of aviation industry, aero -engine includes turbofan engine, turboprop engine, ramjet and piston engine and multiple types, not only as the military and civilian aircraft of various purposes, unmanned aerial vehicle and cruise missile power, and gas turbine derived from aero -engine is also widely used in ground power generation, marine power, mobile power station, natural gas and oil pipeline pump station and other fields, wherein impeller blade disc belongs to one of the important spare parts of assembled engine, before assembling, it needs to be fixed to tool fixture, pre-test operation.

[0003] Such as the publication number CN217914928U for aero -engine impeller blade disc test's tool fixture, the top of base is provided with positioning rod, and in the inner cavity of base assembly is equipped with limiting device, the outer surface of rotating shaft is equipped with elastic mechanism, wherein elastic mechanism is torsion spring, one end of elastic mechanism is connected with clamping block, the other end is connected with limiting rod, make clamping block turn to one side when being pressed, and the inner wall of engine impeller blade disc is tightly pressed by the counterforce of elastic mechanism.

[0004] The above-mentioned tool fixture makes clamping block realize clamping fixed by the counterforce of elastic mechanism, since the installation hole size specifications of different specifications aero -engine impeller blade disc are different, positioning rod is provided with cylindrical structure, when aero -engine impeller blade disc installation hole is too large, it is difficult to keep aero -engine impeller blade disc installation hole in the most middle position in the process of placing, when aero -engine impeller blade disc installation position is offset, affect and process it later. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing a kind of tool fixture for aero -engine blade disc to solve the problem that aero -engine blade disc is difficult to locate in middle position in the above background art.

[0006] To achieve the above object, the utility model provides the following technical scheme: a kind of tool fixture for aero -engine blade disc, including base and installation column, installation column is installed at the top of base, characterized in that, mobile plate is located at the side of installation column, limiting column is penetrated on installation column, mobile plate, limiting column and installation column three mutually cooperate and realize clamping fixed.

[0007] Preferably, the installation column is a circular truncated cone structure, and an inclined through slot is formed in the mobile plate.

[0008] Preferably, the base is equiangularly mounted with a fixed rod, which is inserted into the interior of the moving plate.

[0009] Preferably, the moving plate is provided with a through hole near one end of the mounting column, and a limiting column is inserted into the through hole.

[0010] Preferably, the limiting column is penetrated by an annular upper mounting ring, and a threaded rod is rotatably connected to the moving plate and is in threaded connection with one of the limiting columns.

[0011] Preferably, the through slot is penetrated by an annular lower mounting ring, and the lower mounting ring is attached to the inclined side of the through slot.

[0012] Preferably, the base is provided with a servo motor, and a lead screw is mounted at the output end of the servo motor and is in threaded connection with the lower mounting ring.

[0013] Compared with the prior art, the utility model has the beneficial effects that:

[0014] 1. The utility model sets up the mounting column, the mounting column is the circular table structure, and the setting can limit the aero-engine disc of different specifications through the mounting column, the aero-engine disc is kept in the middle position through the mounting column, the aero-engine disc is forced same around, reduces the damage to the aero-engine disc, and the aero-engine disc is conveniently processed.

[0015] 2. The utility model sets up the moving plate, the through slot and the lower mounting ring, and the lower mounting ring is extruded to the through slot and is moved downward, and the special structure of the through slot makes the horizontal movement of the moving plate, and the position of the limiting column around is changed through the movement of the moving plate, can be adjusted according to the specification of the clamped aero-engine disc, greatly improves the overall application range. BRIEF DESCRIPTION OF DRAWINGS

[0016] Fig. 1 It is the three-dimensional structure schematic diagram of the utility model;

[0017] Fig. 2 It is the side view structure schematic diagram of the utility model;

[0018] Fig. 3 It is the three-dimensional structure schematic diagram of the moving plate of the utility model.

[0019] In the drawing: 1, base;2, fixed rod;3, lower mounting ring;4, moving plate;5, threaded rod;6, upper mounting ring;7, mounting column;8, limiting column;9, through slot;10, through hole;11, lead screw;12, servo motor. DETAILED DESCRIPTION

[0020] Clearly and completely describe the technical scheme in the embodiments of the utility model with reference to the drawings in the embodiments of the utility model, obviously, the described embodiments are only a part of the embodiments of the utility model, and not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor belong to the scope of protection of the utility model.

[0021] Please refer to Figs. 1-3 The utility model provides the following technical scheme:

[0022] A tool fixture for aero-engine blade disc, including base 1 and installation column 7, installation column 7 is installed at the top of base 1, moving plate 4 is located at the side of installation column 7, and limiting column 8 is penetrated through installation column 7, moving plate 4, limiting column 8 and installation column 7 are mutually matched to realize clamping and fixing, and installation column 7 is a circular table structure.

[0023] Place the aero-engine blade disc on the installation column 7, and the installation column 7 penetrates the middle position of the aero-engine blade disc, since the installation column 7 is a circular table structure, the installation column 7 moves downward due to its own gravity, when the installation hole of the installation column 7 contacts the side of the installation column 7, the side of the installation column 7 abuts against the installation column 7 to keep the aero-engine blade disc stable and located in the middle position, and the fixture can make the aero-engine blade disc uniformly stressed around when clamping the aero-engine blade disc, thereby avoiding damage of the aero-engine blade disc due to uneven stress.

[0024] An inclined through groove 9 is formed in the moving plate 4, a lower installation ring 3 in the shape of a circular ring is penetrated through the through groove 9, the lower installation ring 3 is attached to the inclined side of the through groove 9, the base 1 is provided with a fixed rod 2 at an equal angle, the fixed rod 2 is inserted into the inside of the moving plate 4, a servo motor 12 is installed on the base 1, a lead screw 11 is installed at the output end of the servo motor 12, and the lead screw 11 is threadedly connected with the lower installation ring 3.

[0025] According to the change of the transverse position of the limiting column 8 according to the specification size of the aero-engine blade disc, the servo motor 12 is started, the servo motor 12 is operated to rotate the lead screw 11, when the lead screw 11 rotates to move the lower installation ring 3 downward, since the contact side of the through groove 9 and the lower installation ring 3 is an inclined side, the lower installation ring 3 pushes the through groove 9 when moving downward, moves the moving plate 4 to the middle position, moves the moving plate 4 to drive the limiting column 8 to move synchronously, and then the servo motor 12 is turned off after the limiting column 8 moves above the aero-engine blade disc.

[0026] A through hole 10 is formed in the end of the moving plate 4 close to the installation column 7, the limiting column 8 is inserted into the through hole 10, an upper installation ring 6 in the shape of a circular ring is penetrated through the limiting column 8, a threaded rod 5 is rotatably connected to the moving plate 4, and the threaded rod 5 is threadedly connected with one of the limiting columns 8.

[0027] When the threaded rod 5 is rotated by hand, one of the limiting posts 8 is moved downward, and the remaining limiting posts 8 are synchronously moved by the upper mounting ring 6, until the lower ends of the limiting posts 8 abut against the upper ends of the aero-engine disk, and then the threaded rod 5 is not rotated any more, at this time, the upper ends of the aero-engine disk are fixed by the limiting posts 8, the lower ends are fixed by the side edges of the mounting posts 7, and the aero-engine disk is clamped on the mounting posts 7, so the application range is wide.

[0028] Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part of the technical features, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A tooling fixture for an aircraft engine bladed disk, comprising a base (1) and a mounting post (7), the mounting post (7) being mounted on the top of the base (1), characterized in that, The movable plate (4) is located on the side of the mounting column (7), and the mounting column (7) has a limiting column (8) running through it. The movable plate (4), the limiting column (8) and the mounting column (7) cooperate with each other to achieve clamping and fixing.

2. The tooling fixture for an aero-engine bladed disk according to claim 1, characterized in that: The mounting column (7) is a frustum structure, and the movable plate (4) has an inclined through groove (9).

3. The tooling fixture for an aero-engine bladed disk according to claim 1, characterized in that: The base (1) is equipped with a fixing rod (2) at equal angles, and the fixing rod (2) is inserted into the inside of the movable plate (4).

4. A tooling fixture for an aero-engine bladed disk according to claim 1, characterized in that: The movable plate (4) has a through hole (10) at one end near the mounting post (7), and a limit post (8) is inserted inside the through hole (10).

5. A tooling fixture for an aero-engine bladed disk according to claim 1, characterized in that: A circular upper mounting ring (6) passes through the limiting post (8), and a threaded rod (5) is rotatably connected to the moving plate (4). The threaded rod (5) is threadedly connected to one of the limiting posts (8).

6. A tooling fixture for an aero-engine bladed disk according to claim 2, characterized in that: A circular mounting ring (3) is inserted through the inside of the through groove (9), and the lower mounting ring (3) is in contact with the inclined edge of the through groove (9).

7. A tooling fixture for an aero-engine bladed disk according to claim 1, characterized in that: A servo motor (12) is installed on the base (1), and a lead screw (11) is installed at the output end of the servo motor (12). The lead screw (11) is threadedly connected to the lower mounting ring (3).

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