CN216608076U - Clamp for aero-engine casing - Google Patents

Abstract

The utility model provides a clamp for an aero-engine casing, which relates to the technical field of aero-engine production. The clamp of the aero-engine casing includes a positioning seat, a support and an inner clamping block. A plurality of supports are circularly arrayed on the positioning seat. The inner jacking block is connected to the positioning seat through the adjusting mechanism, and the inner jacking block can abut on the inner side of the casing. The adjusting mechanism is used to move the inner pressing block along the radial direction of the positioning seat. Put the casing on the positioning seat, and make the inner top tightening block on the inner side of the casing, and then move the inner top tightening block along the radial direction of the positioning seat, so that the inner top tightening block is tightly pressed on the inner wall of the casing. Fix the receivers of various sizes to avoid the deformation of the receiver during the processing.

Description

A clamp for aero-engine casing

technical field

The utility model relates to the technical field of aero-engine production, in particular to a clamp for an aero-engine casing.

Background technique

The casing is one of the important parts of the aero-engine, mostly made of titanium alloy material. It is the base of the entire engine and the main load-bearing component of the aero-engine.

When machining the aero-engine case, the current tooling cannot fix the case well, which leads to the problem that it is not easy to control the roundness of the case during the machining process (that is, the case is easily deformed during the machining process). ,Room for improvement.

Utility model content

In view of the above situation, the utility model provides a clamp for an aero-engine casing, which solves the problem that when the aero-engine casing is machined at present, the tooling used cannot fix the casing well, which causes the casing to be easily processed during the processing. Deformed technical issues.

To achieve the above object, the utility model provides the following technical solutions:

The utility model relates to a clamp for an aero-engine casing, which mainly includes: a positioning seat, a support and an inner clamping block. A plurality of supports are circularly arrayed on the positioning seat. The inner jacking block is connected to the positioning seat through the adjusting mechanism, and the inner jacking block can abut on the inner side of the casing. The adjusting mechanism is used to move the inner pressing block along the radial direction of the positioning seat.

In some embodiments of the present invention, the adjustment mechanism includes an adjustment rod, a movable member and a guide assembly. The adjustment rod is rotatably connected to the support, and the movable piece is sleeved on one end of the adjustment rod and is connected with the movable piece by threads. The inner top tightening block is installed on the movable part. The guide assembly can make the movable member move along the radial direction of the positioning seat.

In some embodiments of the present invention, the guide assembly includes a guide member mounted on the support. The outer side of the movable piece is provided with a guide groove matched with the guide piece, the guide groove is arranged along the radial direction of the positioning seat, and the lower part of the guide piece can extend into the guide groove.

In some embodiments of the present invention, the support is provided with a connecting hole, and the connecting hole is provided with a limiting shoulder. One end of the adjusting rod extends into the connecting hole, the adjusting rod is provided with a first limiting piece and a second limiting piece, the first limiting piece and the second limiting piece are respectively abutted on both sides of the limiting shoulder.

In some embodiments of the present invention, the support is detachably connected to the positioning base.

In some embodiments of the present invention, the support is connected with the positioning seat through screws.

In some embodiments of the present invention, the positioning seat is provided with a positioning sleeve, the positioning sleeve is inserted into the support, and the screw is connected to the positioning seat after passing through the positioning sleeve.

In some embodiments of the present invention, a protective pad is provided on the side of the inner jacking block facing the casing.

In some embodiments of the present invention, a guide rod is provided on the inner pressing block, one end of the guiding rod is mounted on the inner pressing block, and the other end is inserted into the support.

In some embodiments of the present invention, the clamp of the aero-engine casing further includes a pressing plate detachably connected to the positioning seat, and the pressing plate can be pressed against the outer side of the casing.

The embodiments of the present utility model at least have the following advantages or beneficial effects:

Put the casing on the positioning seat, and make the inner top tightening block on the inner side of the casing, and then move the inner top tightening block along the radial direction of the positioning seat, so that the inner top tightening block is tightly pressed on the inner wall of the casing. Fix the receivers of various sizes to avoid the deformation of the receiver during the processing.

Other features and advantages of the invention will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained in the description, claims and drawings.

Description of drawings

In order to explain the technical solutions of the embodiments of the present application more clearly, the following briefly introduces the drawings that are used in the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

Fig. 1 is the structural representation of the clamp of aero-engine casing;

Fig. 2 is the structural schematic diagram of the positioning seat, the support and the inner top tightening block;

Fig. 3 is a partial enlarged view of position A in Fig. 1;

Fig. 4 is the structural representation of the support;

Fig. 5 is the structural representation along the left side of Fig. 4;

Fig. 6 is the structural representation of the adjustment rod;

Figure 7 is a schematic diagram of the structure of the movable part

FIG. 8 is a schematic view of the structure along the left side of FIG. 7 .

Icon: 11-positioning seat, 111-positioning sleeve, 112-eye bolt, 113-weight reduction hole, 12-support, 121-connecting hole, 122-limiting shoulder, 123-first screw, 124-split washer, 13-Inner clamping block, 131-Protective pad, 132-Guide rod, 14-Adjustment mechanism, 141-Adjust rod, 142-Moveable piece, 143-Guide piece, 144-Guide groove, 145-First limit piece, 146-Second limiting piece, 147-Connecting pin, 148-Handle, 16-Press plate, 161-Second screw, 2-Case.

Detailed ways

In the following, only certain exemplary embodiments are briefly described. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the embodiments of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature and not restrictive.

In the description of the embodiments of the present invention, it should be understood that the terms "upper", "lower", "top", "inner", "outer", "axial", "radial", etc. The orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the embodiments of the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, with a specific orientation. The orientation configuration and operation are therefore not to be construed as limitations on the embodiments of the present invention.

In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature defined as "first" or "second" may expressly or implicitly include one or more of that feature. In the description of the embodiments of the present invention, "a plurality" means two or more, unless otherwise expressly and specifically defined.

In the embodiments of the present utility model, unless otherwise expressly specified and limited, terms such as "installation", "connection", "connection", and "fixation" should be understood in a broad sense, for example, it may be a fixed connection or a Removably connected, or integrated; it can be a mechanical connection, an electrical connection, or a communication; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal connection of two elements or the connection between the two elements. interaction relationship. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific situations.

The embodiments of the present utility model will be described in detail below with reference to the accompanying drawings.

Example

Referring to FIGS. 1-8 , the present embodiment provides a fixture for an aero-engine casing, which may mainly include: a positioning seat 11 , a support 12 and an inner tightening block 13 . A plurality of supports 12 (6 pieces) are circularly arrayed on the positioning seat 11 . The inner pressing block 13 is connected to the positioning base 11 through the adjusting mechanism 14 , and the inner pressing block 13 can abut on the inner side of the casing 2 . The adjusting mechanism 14 is used to move the inner pressing block 13 along the radial direction of the positioning seat 11 .

The virtual outline shown by the double-dot chain line in FIGS. 1 and 2 is the outline of the casing 2 . When fixing the casing 2, the casing 2 can be placed on the positioning seat 11 first, and the inner clamping block 13 can be located on the inner side of the casing 2, and then the inner clamping block 13 can be moved along the radial direction of the positioning seat 11 to make The inner top tightening block 13 can be pressed on the inner wall of the casing 2 to realize the fixing of the casing 2 of various sizes, so as to prevent the casing 2 from being deformed during the processing.

In this embodiment, preferably, the adjustment mechanism 14 may mainly include an adjustment rod 141 , a movable member 142 and a guide assembly. The adjustment rod 141 is rotatably connected to the support 12 , and the movable member 142 is sleeved on one end of the adjustment rod 141 and is connected with the movable member 142 by threads. The inner clamping block 13 is installed on the movable member 142 . The guide assembly can make the movable member 142 move along the radial direction of the positioning seat 11 . More specifically, the movable member 142 is provided with an inner thread, and the adjusting rod 141 is provided with an outer thread matching the inner thread. Rotating the adjusting rod 141 can drive the movable piece 142, and the rotation of the movable piece 142 is restricted by the guide assembly, so that the movable piece 142 can move in the radial direction of the positioning seat 11, and the inner pressing block 13 can be pressed against the casing. 2 , so that the casing 2 is fixed by a plurality of inner clamping blocks 13 .

In this embodiment, preferably, the guide assembly may mainly include a guide member 143 mounted on the support 12 . The guide member 143 can be screwed on the upper part of the support 12, for example. The outer side of the movable member 142 is provided with a guide groove 144 matching with the guide member 143 . When the adjusting rod 141 is rotated, the guide member 143 can make the movable member 142 move along the axial direction of the adjusting rod 141 .

In this embodiment, the rotational connection between the adjusting rod 141 and the support 12 can be realized by the following methods: the support 12 is provided with a connecting hole 121 , and the connecting hole 121 is provided with a limiting shoulder 122 . One end of the adjusting rod 141 protrudes into the connecting hole 121 . The adjusting rod 141 is provided with a first limiting member 145 and a second limiting member 146 . Both sides of the shoulder 122 are located.

The first limiting member 145 can be connected with the adjusting rod 141 through the connecting pin 147, so as to facilitate the disassembly and replacement of the first limiting member 145.

One end of the adjusting rod 141 is connected with a handle 148 to facilitate the rotation of the adjusting rod 141 .

In order to facilitate disassembly and replacement of the support 12 , the support 12 is detachably connected to the positioning base 11 , for example, the support 12 can be connected to the positioning base 11 through the first screw 123 .

In order to facilitate the connection between the support 12 and the positioning base 11 , a positioning sleeve 111 is provided on the positioning base 11 . When the support 12 is fixed on the positioning base 11 , the support 12 can be connected with the positioning sleeve 111 first, and then the first screw 123 can be inserted through the positioning sleeve 111 and then connected with the positioning base 11 .

A split washer 124 may be sleeved on the first screw 123 to prevent the first screw 123 from loosening.

The positioning seat 11 may also be provided with lifting ring screws 112 (4 pieces) to facilitate the handling of the clamp of the aero-engine casing.

The positioning seat 11 is provided with a number of weight-reducing holes 113 (12), that is, hollowing out the position where the tooling is not responsible for connection and support, so as to reduce the weight of the tooling as much as possible. On the other hand, it helps to improve the accuracy of rotation positioning (when the weight of the part is constant, the heavier the tooling, the greater the inertia, and the worse the accuracy of rotation positioning) to ensure the machining accuracy.

A protective pad 131 is provided on the side of the inner top tightening block 13 facing the casing 2 , and the protective pad 131 may be, for example, a soft rubber to protect the inner profile of the casing 2 from being bruised by the inner top tightening block 13 .

The inner clamping block 13 is provided with guide rods 132 (two pieces), one end of the guiding rod 132 is mounted on the inner clamping block 13 , and the other end is inserted into the support 12 . The guide rod 132 can guide the inner pressing block 13 to ensure that the inner pressing block 13 can move in the radial direction of the positioning seat 11 .

In order to better fix the casing 2 , the clamp of the aero-engine casing may further include a pressing plate 16 detachably connected to the positioning base 11 , and the pressing plate 16 can be pressed against the outer side of the casing 2 . The pressing plate 16 is Z-shaped, and there are many ways to detachably connect the pressing plate 16 and the positioning base 11 .

It should be noted that the purpose of pressing the pressing plate 16 against the outer side of the casing 2 is to better fix the casing 2. Therefore, the force of the pressing plate 16 on the casing 2 can not only be directed towards the positioning seat 11, so that the casing 2 is pressed on the positioning seat 11, and a force can also be applied to the casing 2 along the radial direction of the casing 2, so as to fix the casing 2 through the pressing plate 16 and the inner clamping block 13.

In combination with the above structure, the working principle of the clamp of the aero-engine casing will be described in detail below.

When fixing the casing 2, the casing 2 can be placed on the positioning seat 11 first, and the inner clamping block 13 can be located on the inner side of the casing 2, and then the inner clamping block 13 can be moved along the radial direction of the positioning seat 11 to make The inner top tightening block 13 can be pressed on the inner wall of the casing 2 to realize the fixing of the casing 2 of various sizes, so as to prevent the casing 2 from being deformed during the processing.

In order to better fix the casing 2, the pressure plate 16 can also be abutted on the outside of the casing 2, and then the pressure plate 16 and the positioning seat 11 are connected by a second screw 161, so that the pressure plate 16 is pressed tightly on the casing 2, The pressing plate 16 can limit the movement of the casing 2 .

Finally, it should be noted that the above are only the preferred embodiments of the present utility model, and are not intended to limit the present utility model. For those skilled in the art, the present utility model may have various modifications and changes. In this case, the embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims (10)

1. A clamp of an aeroengine casing is characterized by comprising: the positioning seat, the support and the inner jacking block;

a plurality of support seats are circularly arrayed on the positioning seat;

the inner jacking block is connected to the positioning seat through an adjusting mechanism and can abut against the inner side of the casing;

the adjusting mechanism is used for enabling the inner jacking block to move along the radial direction of the positioning seat.

2. The clamp of an aircraft engine case according to claim 1, wherein the adjustment mechanism comprises an adjustment rod, a movable member and a guide member;

the adjusting rod is rotationally connected to the support,

the movable piece is sleeved at one end of the adjusting rod and is in threaded connection with the movable piece; the inner jacking block is arranged on the movable piece;

the guide assembly can enable the movable piece to move along the radial direction of the positioning seat.

3. The aero engine case clamp of claim 2 wherein the guide assembly comprises a guide mounted on the mount;

the outer side of the moving part is provided with a guide groove matched with the guide piece, the guide groove is arranged along the radial direction of the positioning seat, and the lower part of the guide piece can extend into the guide groove.

4. The clamp of the aeroengine case as defined in claim 2, wherein the support is provided with a connecting hole, and a limiting shoulder is arranged in the connecting hole;

one end of the adjusting rod extends into the connecting hole, a first limiting part and a second limiting part are arranged on the adjusting rod, and the first limiting part and the second limiting part are respectively abutted to two sides of the limiting shoulder.

5. The aero-engine case clamp according to claim 1, wherein the mount is removably attached to the positioning socket.

6. The aero-engine case clamp according to claim 5 wherein the mount is attached to the locating socket by screws.

7. The clamp of the aero-engine case according to claim 6, wherein the positioning seat is provided with a positioning sleeve, the positioning sleeve is inserted into the support, and the screw penetrates through the positioning sleeve and then is connected with the positioning seat.

8. The clamp of an aircraft engine casing according to claim 1, wherein a side of the inner jacking block facing the casing is provided with a protective pad.

9. The clamp of the aero-engine case according to claim 1, wherein a guide rod is disposed on the inner tightening block, one end of the guide rod is mounted on the inner tightening block, and the other end of the guide rod is inserted into the support.

10. The aircraft engine case clamp according to any one of claims 1 to 9, further comprising a pressure plate detachably connected to the positioning seat, wherein the pressure plate can be pressed against the outer side of the case.

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