CN114955231A

CN114955231A - Aeroengine packing plant and clamp subassembly thereof

Info

Publication number: CN114955231A
Application number: CN202110213645.3A
Authority: CN
Inventors: 张潇; 王海晨; 李磊; 欧阳醌; 陈栋权
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-02-25
Filing date: 2021-02-25
Publication date: 2022-08-30
Anticipated expiration: 2041-02-25
Also published as: CN114955231B

Abstract

The invention discloses an aircraft engine packaging device and a clamp assembly thereof, wherein the clamp assembly comprises a first clamp, a second clamp and a fastener, the first clamp is provided with a first concave part, the second clamp is provided with a second concave part, the first concave part and the second concave part are opposite in position and form a mounting hole, the mounting hole can be used for accommodating and fixing a connecting shaft, and the fastener is used for detachably connecting the first clamp and the second clamp together. First clamp has the orientation the spacing arch that the second clamp stretches out, spacing arch is located the outside of second clamp. Because spacing arch is located the outside of second clamp, consequently when the effect of external load, when producing relative translational motion's trend between first clamp and the second clamp, spacing arch can share at least some external load to alleviate the load of fastener, reduced the risk that the clamp subassembly became invalid, improved the security of clamp subassembly.

Description

Aeroengine packing plant and clamp subassembly thereof

Technical Field

The invention relates to the field of aero-engine packaging, in particular to an aero-engine packaging device and a hoop component thereof.

Background

The aircraft engine needs to be transported by a packing box or a transport vehicle. As shown in fig. 1, during transportation, the front and rear mounting sections of the engine are connected to the support frame assembly 100' of the packing box or the transport vehicle through connecting members. Specifically, the aero-engine has two front mounting sections and two rear mounting sections, and the support frame assembly 100 'is provided with two connecting shafts 3' and two pull rods 4 ', wherein the two connecting shafts 3' are respectively and correspondingly connected to the two front mounting sections, and the two pull rods 4 'are correspondingly connected to the two rear mounting sections, so that the aero-engine is connected to the support frame assembly 100'.

In the prior art, the connecting shaft 3 'is generally fixed to the support bracket assembly 100' by a clip assembly 5 ', and in the conventional clip assembly 5', as shown in fig. 2, two half ring portions 1 'of the clip assembly form a mounting hole 2', and the connecting shaft 3 'is disposed in the mounting hole 2'.

Impact loads can be generated in the process of transporting the aircraft engine, and the impact can be mainly applied to the part, connected with the connecting shaft, of the front mounting section of the engine due to the fact that the center of gravity of the engine is close to the front mounting section of the engine and is influenced by the structural characteristics of the support frame assembly. However, as shown in fig. 2, the two half ring portions 1 ' of the prior art clip assembly 5 ' are connected by means of the connecting bolt 6 ', and the connecting bolt 6 ' simultaneously bears impact force or acceleration force in all directions, which results in very complicated stress conditions of the connecting bolt 6 ' of the prior art clip assembly 5 ', and the clip assembly 5 ' has a high risk of failure, and the safety thereof still needs to be further improved.

Disclosure of Invention

The invention aims to overcome the defects of high failure risk and poor safety of a hoop component in the prior art, and provides an aeroengine packaging device and the hoop component thereof.

The invention solves the technical problems through the following technical scheme:

a clip assembly for an aircraft engine packaging device, the clip assembly comprising:

a first clip having a first recess;

the second clamp is provided with a second concave part, and the first concave part is opposite to the second concave part in position and forms a mounting hole;

a fastener for removably connecting the first and second clips together;

its characterized in that, first clamp has the orientation the spacing arch that the second clamp stretches out, spacing arch is located the outside of second clamp.

In this scheme, form the mounting hole after first clamp and the connection of second clamp, the connecting axle can be by the lock in the mounting hole, is favorable to the convenient installation of connecting axle, because first clamp is connected for dismantling with the second clamp, consequently the engine can conveniently carry out the dismouting with clamp subassembly. Because spacing arch is located the outside of second clamp, consequently under the effect of external load, when producing relative translational motion's trend between first clamp and the second clamp, spacing arch can share at least partly external load to prevent that external load from being used in on the fastener completely, thereby alleviateed the load of fastener, reduced the risk that the clamp subassembly became invalid, improved the security of clamp subassembly.

Preferably, the second clamp is provided with a limiting groove, and the limiting protrusion is fittingly inserted into the limiting groove.

In this scheme, spacing groove has played certain limiting displacement to spacing arch, and spacing arch is spacing as far as possible on being on a parallel with the interface of first clamp and second clamp, therefore the external load is on a parallel with the main effect of the ascending weight of interface side on spacing arch, and the external load that acts on the fastener is mainly for the ascending external load of perpendicular to interface side, has alleviateed the fastener burden greatly, has reduced the risk of the inefficacy of fastener. In addition, when the fastener is designed and selected, the fastener can be mainly reinforced in the direction perpendicular to the interface surface, and the load in other directions can be resisted with less consideration, so that the flexibility of the fastener selection and design is improved. In addition, the cooperation of the limiting protrusion and the limiting groove is utilized, so that the assembly alignment of the clamp assembly is facilitated, and the installation of the clamp assembly is facilitated.

Preferably, two different sides of the first clamp are respectively provided with one limiting protrusion.

In this scheme, because the both sides of first clamp respectively are provided with a spacing arch, consequently spacing arch is spacing simultaneously in the different both sides of second clamp, has improved the reliability that first clamp is connected with the second clamp to can undertake the load in the direction of difference, thereby further reduce the load of using on the fastener, improve the holistic reliability of clamp subassembly and security.

Preferably, spacing arch has first medial surface and the second medial surface that is the contained angle, the second clamp has first lateral surface and the second lateral surface that is the contained angle, first medial surface and the cooperation of first lateral surface, second medial surface and the cooperation of second lateral surface.

In this scheme, under the combined action of first medial surface and second medial surface, single spacing arch just can undertake the external load of a plurality of directions simultaneously under the condition of the spacing groove of not with the help of the second clamp, has improved spacing bellied bearing capacity to further share the bearing burden of fastener, also reduced the processing degree of difficulty of second clamp. Preferably, the first inner side face is perpendicular to the second inner side face, and the limiting protrusion is located at the corner of the second hoop.

Preferably, the limiting protrusion partially surrounds the outer side of the second clamp.

In this scheme, because spacing arch is partial around the second clamp, consequently can be under the prerequisite that does not influence the connecting axle installation for a plurality of direction loads are undertaken to single spacing arch. The cross section of the limiting protrusion can be arc-shaped, and correspondingly, the second clamp is provided with an arc-shaped outer side face matched with the arc-shaped limiting protrusion.

Preferably, the limiting protrusion is located on a first side of the clip assembly, and the first side is different from two axial sides of the mounting hole.

In this scheme, the first side of clamp subassembly is not located the axial both sides of mounting hole, and consequently spacing arch is far away from the connecting axle, and when clamp subassembly installation connecting axle, spacing arch can not take place to interfere with the connecting axle, also reduces the influence of spacing arch to the connecting axle dismouting as far as possible.

Preferably, the second clamp has a limit protrusion protruding toward the first clamp, and the limit protrusion is located at an outer side of the first clamp.

In this scheme, similar to spacing arch, spacing lug also plays the effect of sharing the first clamp with the ascending effect of second clamp interface side to further alleviate the external load that acts on the fastener. Preferably, the retention bumps and the retention tabs are located on different sides (e.g., opposite sides) of the clip assembly such that the retention bumps and the retention tabs can act in concert in different directions to carry loads in different directions.

Preferably, the clip assembly further includes a bushing matingly disposed within the mounting bore, the bushing having an inner bore for receiving the connecting shaft.

In this scheme, the connecting axle is installed in the hole, and the bush sets up between clamp subassembly and connecting axle.

Preferably, the bushing comprises a first half ring portion located within the first recess and a second half ring portion located within the second recess.

In this scheme, first semi-ring portion encloses into the hole with second semi-ring portion jointly, only need when the installation connecting axle with first semi-ring portion and second semi-ring portion lock in the outside of connecting axle, it is comparatively convenient to assemble.

An aircraft engine packaging device comprising a clip assembly as hereinbefore described.

In this scheme, because foretell clamp subassembly has been used to aeroengine packing plant, can utilize spacing arch to share at least some external load to prevent that external load from being used in the fastener completely, thereby alleviateed the load of fastener, reduced the risk that clamp subassembly became invalid, improved clamp subassembly's security, thereby guaranteed aeroengine packing plant's reliability, reduced aeroengine and taken place the possibility of damaging in the transportation. Specifically, the aeroengine packaging device can be a packaging box or a supporting frame.

The positive progress effects of the invention are as follows: according to the hoop component, at least part of external load is shared by the limiting protrusions, so that the external load is prevented from completely acting on the fastening piece, the load of the fastening piece is reduced, the risk of failure of the hoop component is reduced, and the safety of the hoop component is improved; according to the aero-engine packaging device, the hoop component is applied, so that the reliability of the aero-engine packaging device is guaranteed, and the possibility of damage to an aero-engine in the transportation process is reduced.

Drawings

Fig. 1 is a schematic structural view of a support frame assembly in the prior art.

Fig. 2 is a schematic view of a prior art clip assembly.

Fig. 3 is an exploded view of a clip assembly according to an embodiment of the present invention.

Fig. 4 is a schematic structural view of a clip assembly according to an embodiment of the present invention in a use state.

Fig. 5 is an exploded view of a clip assembly and a connecting shaft according to an embodiment of the present invention.

Description of the background art

Semi-ring part 1'

Mounting hole 2'

Connecting shaft 3'

Pull rod 4'

Hoop component 5'

Support frame assembly 100'

Description of the reference numerals

Clip assembly 10

First clamp 1

First recess 11

Through-hole 12

Second clamp 2

Second recess 21

Threaded hole 22

Mounting hole 3

Fastener 4

Spacing bulge 5

Lead angle part 51

Spacing groove 6

Connecting shaft 7

Step 71

Lock nut 8

Bushing 9

First semi-ring part 91

Second half ring portion 92

Detailed Description

The invention is further illustrated by the following examples, which are not intended to limit the scope of the invention.

The present embodiment provides an aircraft engine packaging device and a clamp assembly 10 thereof, wherein, as shown in fig. 3 to 5, the clamp assembly 10 includes a first clamp 1, a second clamp 2 and a fastening member 4, the first clamp 1 has a first concave portion 11, the second clamp 2 has a second concave portion 21, the first concave portion 11 is opposite to the second concave portion 21 and forms a mounting hole 3, and the mounting hole 3 can be used for accommodating and fixing a connecting shaft 7.

A fastener 4 is used to detachably connect the first clamp 1 and the second clamp 2 together, preferably, the fastener 4 is a screw or bolt. First clamp 1 forms mounting hole 3 after being connected with second clamp 2, and connecting axle 7 can be by the lock in mounting hole 3, is favorable to the convenient installation of connecting axle 7, because first clamp 1 is connected for dismantling with second clamp 2, consequently the engine can conveniently carry out the dismouting with clamp subassembly 10.

The X direction, Y direction and Z direction in the present embodiment are specifically the directions of arrows as shown in fig. 3. The X direction refers to the axial direction of the mounting hole 3; the Z direction is a direction perpendicular to the interface of the first clamp 1 and the second clamp 2; the Y direction is a direction perpendicular to the X direction and the Z direction.

Specifically, in this embodiment, the second yoke 2 is provided with four threaded holes 22, the first yoke 1 is provided with through holes 12 corresponding to the threaded holes 22 one by one, and screws pass through and are screwed into the threaded holes 22.

The first clamp 1 has a limit protrusion 5 protruding toward the second clamp 2, and the limit protrusion 5 is located outside the second clamp 2. Because the limiting protrusion 5 is located on the outer side of the second clamp 2, when a relative translational movement trend is generated between the first clamp 1 and the second clamp 2 under the action of an external load, the limiting protrusion 5 can share at least a part of the external load (i.e., a part of the load along the Y direction), so that the external load is prevented from completely acting on the fastener 4, the load of the fastener 4 is reduced, particularly the impact load of the fastener 4 along the Y direction is reduced, the risk of failure of the clamp assembly 10 is reduced, and the safety of the clamp assembly 10 is improved. Preferably, the root of the limiting protrusion 5 is provided with a leading corner part 51 to reduce the stress concentration at the root of the limiting protrusion 5 and improve the bearing capacity of the limiting protrusion 5.

In the present embodiment, as shown in fig. 3 and 4, the second yoke 2 is provided with a stopper groove 6, and the stopper protrusion 5 is fittingly inserted in the stopper groove 6. The limiting groove 6 plays a certain limiting role for the limiting protrusion 5, and the limiting protrusion 5 is limited as much as possible on the interface parallel to the first clamping hoop 1 and the second clamping hoop 2. In the present embodiment, the limiting protrusion 5 is completely limited in the X direction, and is limited in the Y direction by one side. Therefore, the component of the external load in the direction parallel to the interface surface is mainly applied to the limiting bulge 5, and the external load applied to the fastening piece 4 is mainly the external load in the Z direction, so that the burden of the fastening piece 4 is greatly reduced, and the risk of failure of the fastening piece 4 is reduced. Furthermore, in the design and selection of the fastener 4, the reinforcement can be mainly performed in the direction perpendicular to the interface of the fastener 4, and the load in other directions can be less considered to be resisted, so that the flexibility of the selection and design of the fastener 4 is improved. In addition, the cooperation of the limiting protrusions 5 and the limiting grooves 6 is also beneficial to the assembly and alignment of the hoop component 10, and the installation of the hoop component 10 is convenient.

Two different sides of the first clamp 1 are respectively provided with a limiting bulge 5. Because the both sides of first clamp 1 respectively are provided with a spacing arch 5, consequently spacing arch 5 carries on spacingly simultaneously in the different both sides of second clamp 2, has improved the reliability that first clamp 1 is connected with second clamp 2 to can bear the load in the direction of difference, thereby further reduce the load of using on fastener 4, improve the holistic reliability and the security of clamp subassembly 10.

Specifically, in the present embodiment, as shown in fig. 3 and 4, the first yoke 1 is disposed above the second yoke 2, and the first recess 11 and the second recess 21 are both semi-annular. The interface of first clamp 1 and second clamp 2 is the horizontal plane, and the screw extends along vertical direction. The first clamp 1 has two limiting protrusions 5, and the mounting hole 3 is located between the two limiting protrusions 5 (one of the limiting protrusions 5 is not shown in the figure). Correspondingly, second clamp 2 has two spacing grooves 6 with 5 one-to-one of spacing arch, and after spacing

groove

6 and 5 cooperation of spacing arch, first clamp 1 was spacing completely in the horizontal direction with second clamp 2, consequently, under ideal conditions, the external load of horizontal direction acted on spacing arch 5 completely, just can guarantee that first clamp 1 can not take place the ascending relative displacement of horizontal direction with second clamp 2, and the screw can not undertake the ascending load of horizontal direction completely.

In some other preferred embodiments, the limiting protrusion 5 has a first inner side and a second inner side forming an included angle, the second band 2 has a first outer side and a second outer side forming an included angle, the first inner side is engaged with the first outer side, and the second inner side is engaged with the second outer side.

Under the combined action of first medial surface and second medial surface, single spacing arch 5 just can undertake the external load of a plurality of directions simultaneously under the condition of the spacing groove 6 of not with the help of second clamp 2, has improved spacing arch 5's bearing capacity to further share fastener 4's the burden of bearing, also reduced second clamp 2's the processing degree of difficulty. Preferably, the first inner side surface and the second inner side surface are perpendicular to each other, and the limiting protrusion 5 is located at a corner of the second yoke 2. For example, the stop protrusion 5 may have an L-shaped cross section. Alternatively, the cross section of the limiting protrusion 5 may be approximately C-shaped, that is, the limiting protrusion 5 further has a third inner side surface, the first inner side surface is perpendicular to the second inner side surface, the second inner side surface is perpendicular to the third inner side surface, and the limiting protrusion 5 partially surrounds one side portion of the second clamp 2.

Furthermore, the stop projection 5 can also partially surround the outside of the second clip 2. Since the limit projection 5 partially surrounds the second yoke 2, a single limit projection 5 can bear a plurality of directional loads without affecting the installation of the connecting shaft 7. For example, the cross section of the limit projection 5 may be arc-shaped, and accordingly, the second yoke 2 has an arc-shaped outer side surface to be fitted with the arc-shaped limit projection 5.

The limit protrusion 5 is located on a first side of the clip assembly 10, which is a side different from both axial sides of the mounting hole 3. The first side of clamp subassembly 10 is not located the axial both sides of mounting hole 3, therefore spacing arch 5 is far away from connecting axle 7, and when clamp subassembly 10 installation connecting axle 7, spacing arch 5 can not take place to interfere with connecting axle 7, also reduces the influence of spacing arch 5 to the dismouting of connecting axle 7 as far as possible. In the present embodiment, as shown in fig. 3, the limiting protrusion 5 is located at the side of the clip assembly 10Y, but not at the side of the clip assembly 10X, so that the limiting protrusion 5 is away from the mounting hole 3 and the connecting shaft 7.

In some other preferred embodiments, the second clamp 2 has a limit projection protruding toward the first clamp 1, and the limit projection is located outside the first clamp 1. Like the stopper projection 5, the stopper projection also functions to share the load in the direction of the interface of the first yoke 1 and the second yoke 2, thereby further relieving the external load acting on the fastening member 4. Preferably, the limit protrusions 5 and the limit projections are located on different sides (e.g., opposite sides) of the clip assembly 10, such that the limit protrusions 5 and the limit projections can act in concert in different directions to carry loads in different directions.

The clip assembly 10 further includes a bushing 9 matingly disposed within the mounting bore 3, the bushing 9 having an inner bore for receiving the connecting shaft 7. The connecting shaft 7 is mounted in the inner bore, and the bushing 9 is disposed between the clip assembly 10 and the connecting shaft 7 to improve the fixing effect of the clip assembly 10 to the connecting shaft 7. The bushing 9 comprises a first half ring 91 located in the first recess 11 and a second half ring 92 located in the second recess 21. The first semi-ring part 91 and the second semi-ring part 92 jointly enclose an inner hole, and the first semi-ring part 91 and the second semi-ring part 92 are buckled on the outer side of the connecting shaft 7 only when the connecting shaft 7 is installed, so that the assembly is convenient.

As shown in fig. 4 and 5, the connecting shaft 7 can be installed in the inner hole, and the connecting shaft 7 is axially positioned by the lock nut 8 and the stepped portion 71 thereof, so that the connecting shaft 7 is completely positioned.

The aeroengine packing plant of this embodiment owing to used foretell clamp subassembly 10, can utilize spacing arch 5 to share at least some external load to prevent that external load from being used in fastener 4 completely, thereby alleviateed fastener 4's load, reduced the risk that clamp subassembly 10 became invalid, improved clamp subassembly 10's security, thereby guaranteed aeroengine packing plant's reliability, reduced the possibility that aeroengine takes place the damage in the transportation. Specifically, the aeroengine packaging device may be a packaging box or a supporting frame, and may also be a transport vehicle for installing the hoop assembly 10.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on normal use of the device or assembly, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or assembly referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the present invention.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims

1. A clip assembly for an aircraft engine packaging device, the clip assembly comprising:

a first clip having a first recess;

a fastener for removably connecting the first and second clips together;

2. The clip assembly of claim 1 wherein the second clip is provided with a retaining groove, the retaining projection being matingly inserted in the retaining groove.

3. The clip assembly of claim 1 wherein the first clip is provided with one of the retaining tabs on each of two distinct sides.

4. The clip assembly of claim 1 wherein the retaining protrusion has a first inner side and a second inner side that form an included angle, and the second clip has a first outer side and a second outer side that form an included angle, the first inner side engaging the first outer side and the second inner side engaging the second outer side.

5. The clip assembly of claim 1 wherein the retaining protrusion partially surrounds the outside of the second clip.

6. The clip assembly of claim 1 wherein the retaining protrusion is located on a first side of the clip assembly, the first side being different from the two axial sides of the mounting hole.

7. The clip assembly of claim 1 wherein the second clip has a stop tab extending toward the first clip, the stop tab being located on an outer side of the first clip.

8. The clip assembly of any one of claims 1-7 further comprising a bushing matingly disposed within the mounting bore, the bushing having an inner bore for receiving a connecting shaft.

9. The clamp assembly of claim 8, wherein the bushing includes a first half ring portion located in the first recess and a second half ring portion located in the second recess.

10. An aircraft engine packaging device, characterised in that it comprises a clip assembly according to any one of claims 1 to 9.