CN216632293U

CN216632293U - One-step forming composite die for aircraft engine retainer ring

Info

Publication number: CN216632293U
Application number: CN202123273514.9U
Authority: CN
Inventors: 马永春
Original assignee: Dalian Mengyu Machinery Co ltd
Current assignee: Dalian Mengyu Machinery Co ltd
Priority date: 2021-12-23
Filing date: 2021-12-23
Publication date: 2022-05-31
Anticipated expiration: 2031-12-23

Abstract

The utility model discloses a one-step forming composite die for an aircraft engine retainer ring, and belongs to the technical field of aircraft engine retainer ring processing. The die comprises an upper die base and a lower die base which are opposite from each other, wherein a fixed plate and a spring a which penetrates through the fixed plate are fixed at the bottom of the upper die base, the spring a is connected with a stop plate, the stop plate is connected with a stripper plate through a spring b, the top of a male die penetrates through the stripper plate and is fixed on the stop plate, and a push rod fixed on the upper die base sequentially penetrates through the fixed plate, the stop plate and the stripper plate. The beneficial effects of the utility model are: when the die is assembled, the female die is matched with the male die, the opposite shaping blocks are matched, and the machining and forming of the arc-shaped part and the clamping opening part of the clamping ring can be completed at one time through a group of dies, so that the machining process is simplified, the machining cost is reduced, and the machining efficiency is improved.

Description

One-step forming composite die for aircraft engine retainer ring

Technical Field

The utility model relates to an one-step forming composite die for an aircraft engine retainer ring, and belongs to the technical field of aircraft engine retainer ring processing.

Background

The aero-engine retainer ring comprises an arc-shaped part and a clamping opening part, secondary forming processing needs to be carried out through two sets of dies, and the machining process is complex, low in efficiency and high in cost.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects in the prior art, the utility model aims to provide the one-step forming composite die for the aircraft engine collar, which simplifies the processing flow, improves the efficiency and reduces the cost.

The technical scheme of the utility model is as follows: the one-step forming composite die for the retainer ring of the aero-engine comprises an upper die base and a lower die base which are opposite from each other, wherein a fixed plate and a spring a penetrating through the fixed plate are fixed at the bottom of the upper die base, the spring a is connected with a stop plate, the stop plate is connected with a stripper plate through a spring b, the top of a male die penetrates through the stripper plate and is fixed on the stop plate, a push rod fixed on the upper die base sequentially penetrates through the fixed plate, the stop plate and the stripper plate, shaping blocks which are opposite to each other are arranged at the bottom of the push rod, thrust inclined planes are arranged at the bottom end of the push rod, stress inclined planes matched with the thrust inclined planes are arranged on the shaping blocks, the shaping end faces of the two shaping blocks are opposite to each other, a female die matched with the male die is located between the oppositely arranged shaping end faces, the bottom end of the female die is fixed on the lower die base, a base plate is fixed on the base plate, and two ends of a return spring are respectively connected with a stop block and an equal-height bolt, the equal-height bolt penetrates through the stop block and is connected with the sliding seat, the sliding seat is connected with the base plate in a sliding mode, and the shaping block is fixed on the sliding seat.

The female die penetrates through the base plate.

The spring is located the upper die base middle part.

The male die is positioned in the middle of the stop plate.

And the springs b are symmetrically arranged at two ends of the stop plate and the stripper plate.

The utility model has the beneficial effects that: when the die is assembled, the female die is matched with the male die, the opposite shaping blocks are matched, and the machining and forming of the arc-shaped part and the clamping opening part of the clamping ring can be completed at one time through a group of dies, so that the machining process is simplified, the machining cost is reduced, and the machining efficiency is improved.

Drawings

FIG. 1 is a first state diagram of the present invention;

FIG. 2 is a second state diagram of the present invention.

The reference numbers in the figures are as follows: 1. the material removing device comprises an upper die base, 2, a fixing plate, 3, a stop plate, 4, a material removing plate, 5, a push rod, 6, springs a and 7, a male die, 8, a stop block, 9, an equal-height bolt, 10, a return spring, 11, a sliding seat, 12, a base plate, 13, a lower die base, 14, a shaping block, 15, a female die, 16, springs b and 17 and a material sheet.

Detailed Description

The utility model is further illustrated with reference to the accompanying figures 1-2:

the compound die for one-step forming of the aircraft engine collar comprises an upper die base 1 and a lower die base 13 which are opposite from each other up and down, wherein a fixed plate 2 and a spring a6 penetrating through the fixed plate 2 are fixed at the bottom of the upper die base 1, the spring a6 positioned in the middle of the upper die base 1 is connected with a stop plate 3, the stop plate 3 is connected with a stripper plate 4 through a spring b16, the spring b16 is symmetrically arranged at two ends of the stop plate 3 and the stripper plate 4, the top of a male die 7 penetrates through the stripper plate 4 and is fixed in the middle of the stop plate 3, a push rod 5 fixed on the upper die base 1 sequentially penetrates through the fixed plate 2, the stop plate 3 and the stripper plate 4, shaping blocks 14 which are opposite to each other are arranged at the bottom of the push rod 5, thrust inclined planes are arranged at the bottom ends of the push rod 5, stress inclined planes matched with the thrust inclined planes are arranged on the shaping blocks 14, shaping end faces of the two shaping blocks 14 are opposite to each other, and a female die 15 matched with the male die 7 is positioned between the shaping end faces which are opposite to each other, the bottom end of a female die 15 is fixed on a lower die base 13, the female die 15 penetrates through a cushion plate 12, the cushion plate 12 is fixed on the lower die base 13, a stop block 8 is fixed on the cushion plate 12, two ends of a return spring 10 are respectively connected with the stop block 8 and an equal-height bolt 9, the equal-height bolt 9 penetrates through the stop block 8 and is connected with a sliding base 11, the sliding base is in sliding connection with the cushion plate 12, and a shaping block 14 is fixed on the sliding base 11.

The material sheet 17 is formed into the clamping ring through the composite die in one step, and the specific processing process is as follows:

in the die opening state (as shown in fig. 1), a material sheet 17 is placed on a shaping block 14 in the center, the middle part of the material sheet 17 is located between a male die 7 and a female die 15, an upper die holder 1 is driven by a driving cylinder to move up and down to realize die closing and die opening, in the die closing process, the upper die holder 1 drives the male die 7, a push rod 5, a stripper plate 4 and the like to move down, the male die 7 is contacted with the material sheet 17 in advance, the material sheet 17 is pressed down towards the female die 15 along with the continuous downward movement of the male die 7, an arc-shaped part of a clamping ring is finally formed, after the male die 7 moves down to a proper position, the upper die holder 1 can also continue to move down due to the arrangement of a spring a6 and a spring b8, the upper die holder 1 drives the push rod 5 to synchronously move down, a thrust inclined plane at the bottom end of the push rod 5 pushes a sliding seat 11 to move towards the female die 15 through a stress inclined plane, the sliding seat 11 drives the shaping block 14 on the sliding seat to move towards the female die 15, and the shaping block 14 is matched with the male die 7, and pressing and forming two ends of the arc-shaped part, and finally forming a bayonet part.

After the clamping ring is machined and formed, the upper die base 1 moves upwards to open the die, at the initial stage of moving upwards, due to the action of the spring, the male die 7 cannot be separated from the female die 15 immediately, but the push rod 5 moves upwards first to be separated from the sliding base 11, the sliding base moves towards two sides to be separated from the formed clamping ring under the action of the return spring 10, the male die 7 drives the clamping ring on the sliding base to start moving upwards along with the continuous moving upwards of the upper die base 1, the stripper plate 4 moves downwards relative to the male die 7 under the action of the spring b16 and acts on two ends of the clamping ring to push the clamping ring down from the male die 7, after the upper die base 1 moves to the position, the clamping ring is manually removed, and then a new material piece to be machined is placed in, and the next working cycle is started.

The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.

Claims

1. The one-step forming composite die for the aircraft engine retainer ring is characterized by comprising an upper die base (1) and a lower die base (13) which are opposite from top to bottom, wherein the bottom of the upper die base (1) is fixedly provided with a fixed plate (2) and a spring a (6) which penetrates through the fixed plate (2), the spring a (6) is connected with a stop plate (3), the stop plate (3) is connected with a stripper plate (4) through a spring b (16), the top of a male die (7) penetrates through the stripper plate (4) and is fixed on the stop plate (3), a push rod (5) fixed on the upper die base (1) sequentially penetrates through the fixed plate (2), the stop plate (3) and the stripper plate (4), the bottom of the push rod (5) is provided with a shaping block (14) which is opposite to one another, the bottom end of the push rod (5) is provided with a thrust inclined surface, the shaping block (14) is provided with a stress inclined surface matched with the thrust inclined surface, and the shaping end surfaces of the two shaping blocks (14) are opposite to one another, the female die (15) matched with the male die (7) is located between the opposite shaping end faces, the bottom end of the female die (15) is fixed on the lower die seat (13), the backing plate (12) is fixed on the lower die seat (13), the stop block (8) is fixed on the backing plate (12), the two ends of the return spring (10) are respectively connected with the stop block (8) and the equal-height bolt (9), the equal-height bolt (9) penetrates through the stop block (8) and is connected with the sliding seat (11), the sliding seat is in sliding connection with the backing plate (12), and the shaping block (14) is fixed on the sliding seat (11).

2. The composite die for one-step forming of an aeroengine collar according to claim 1, wherein the female die (15) penetrates through the shim plate (12).

3. The aero-engine collar one-shot molding compound die as claimed in claim 1, wherein the spring a (6) is located in the middle of the upper die holder (1).

4. The aircraft engine collar one-shot composite moulding tool according to claim 1, characterised in that the male mould (7) is located in the middle of the stop plate (3).

5. The aero-engine collar one-step molding composite die as claimed in claim 1, wherein the springs b (16) are symmetrically arranged at two ends of the stop plate (3) and the stripper plate (4).