CN114955231B - Aeroengine packaging device and clamp assembly thereof - Google Patents

Abstract

The invention discloses an aeroengine packaging device and a clamp assembly thereof. The first clamp has the spacing arch that stretches out towards the second clamp, spacing arch is located the outside of second clamp. Because spacing protruding outside that is located the second clamp, consequently when producing relative translational motion's trend between first clamp and the second clamp under the effect of external load, spacing protruding outside load of at least part can be shared to alleviateed the load of fastener, reduced the risk that clamp subassembly became invalid, improved the security of clamp subassembly.

Description

Aeroengine packaging device and clamp assembly thereof

Technical Field

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

Background

The aero-engine needs to be transported by a packing box or a transport vehicle. As shown in fig. 1, during transportation, front and rear mounting sections of the engine are connected to a supporting frame assembly 100' of a packing box or a transport vehicle through a connecting member. 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 tie rods 4', wherein the two connecting shafts 3' are respectively and correspondingly connected to the two front mounting sections, and the two tie 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 supporting frame assembly 100' by a clip assembly 5', and the two half ring portions 1' of the clip assembly form mounting holes 2 'as shown in fig. 2 in the conventional clip assembly 5', and the connecting shaft 3 'is disposed in the mounting holes 2'.

Impact loads are generated during the transportation of the aero-engine, and are mainly applied to the connecting part of the front mounting joint of the engine and the connecting shaft due to the fact that the gravity center of the engine is close to the front mounting joint 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 existing clip assembly 5' are connected by means of the connecting bolts 6', and the connecting bolts 6' are simultaneously subjected to impact forces or acceleration forces in all directions, which results in the connecting bolts 6' of the existing clip assembly 5' being subjected to very complex stress conditions, and the clip assembly 5' has a high risk of failure, and the safety thereof is still further improved.

Disclosure of Invention

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

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

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

a first clip having a first recess;

a second clip having a second recess, the first recess being located opposite the second recess and forming a mounting hole;

a fastener for detachably connecting the first clip and the second clip together;

the novel clamping device is characterized in that the first clamping band is provided with a limiting protrusion extending towards the second clamping band, and the limiting protrusion is located on the outer side of the second clamping band.

In this scheme, form the mounting hole after first clamp and second clamp connection, the connecting axle can be buckled in the mounting hole, is favorable to the convenient installation of connecting axle, because first clamp and second clamp are detachable connection, therefore the engine can conveniently carry out dismouting with the clamp subassembly. Because spacing protruding outside that is located the second clamp, consequently when producing relative translational motion's trend between first clamp and the second clamp under the effect of external load, spacing protruding can share at least partial external load to prevent that external load from acting on the fastener completely, thereby alleviateed the load of fastener, reduced the risk that 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 inserted in the limiting groove in a matched mode.

In this scheme, the spacing groove has played certain spacing effect to spacing arch, and spacing arch is spacing as far as possible on being parallel to the interface of first clamp and second clamp, therefore the external load is on the spacing arch is mainly all acted on to the component on the interface direction in parallel to, and the external load on the fastener is mainly the external load on the perpendicular to interface direction, has alleviateed the fastener burden greatly, has reduced the risk of fastener inefficacy. In addition, when the fastener is designed and selected, the fastener can be reinforced mainly in the direction perpendicular to the joint surface, and loads in other directions can be resisted less, so that the flexibility of the fastener in selection and design is improved. In addition, the cooperation of spacing arch and spacing groove is also favorable to the assembly counterpoint of clamp subassembly, the installation of the clamp subassembly of being convenient for.

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

In this scheme, owing to the both sides of first clamp respectively are provided with a spacing arch, consequently spacing arch carries out spacingly simultaneously in the both sides that the second clamp is different, has improved the reliability that first clamp and second clamp are connected to can bear the load in different directions, thereby further reduce the load that acts on the fastener, improve holistic reliability and the security of clamp subassembly.

Preferably, the limiting protrusion has a first inner side surface and a second inner side surface which form an included angle, the second clamp has a first outer side surface and a second outer side surface which form an included angle, and the first inner side surface is matched with the first outer side surface, and the second inner side surface is matched with the second outer side surface.

In this scheme, under the combined action of first medial surface and second medial surface, single spacing arch just can bear 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 shared the bearing burden of fastener, also reduced the processing degree of difficulty of second clamp. Preferably, the first inner side surface and the second inner side surface are mutually perpendicular, and the limiting protrusion is positioned at the corner of the second clamp.

Preferably, the limit projection partially surrounds the outer side of the second clip.

In the scheme, the limiting bulge partially surrounds the second clamp, so that a single limiting bulge bears loads in multiple directions on the premise of not influencing the installation of the connecting shaft. The cross section of the limiting protrusion can be arc-shaped, and correspondingly, the second clamp is provided with an arc-shaped outer side surface 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 sides of the mounting hole in the axial direction.

In this scheme, clamp subassembly's first side is not located mounting hole axial both sides, therefore spacing protruding distance connecting axle is farther, and when clamp subassembly installation connecting axle, spacing protruding can not take place to interfere with the connecting axle, also reduces the influence of spacing protruding to the connecting axle dismouting as far as possible.

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

In this scheme, similar to spacing protruding, spacing lug also plays the effect of sharing the ascending load of first clamp and second clamp interface to further alleviate the external load on the fastener. Preferably, the spacing protrusion and the spacing bump are located on different sides (e.g., opposite sides) of the clamp assembly such that the spacing protrusion and the spacing bump are capable of acting in unison 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 internal bore, and the bush sets up between clamp subassembly and connecting axle.

Preferably, the bushing includes a first half-ring portion located in the first recess and a second half-ring portion located in the second recess.

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

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

In this scheme, because aircraft engine packing plant has used foretell clamp subassembly, can utilize spacing protruding sharing at least partial external load to prevent that external load from acting 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, thereby guaranteed aircraft engine packing plant's reliability, reduced the possibility that the aircraft engine took place the damage in the transportation. In particular, the aircraft engine packaging device may be a packaging box or a support frame.

The invention has the positive progress effects that: according to the clamp assembly, at least one part of external load is shared by the limiting protrusions, so that the external load is prevented from being completely acted on the fastening piece, the load of the fastening piece is reduced, the risk of failure of the clamp assembly is reduced, and the safety of the clamp assembly is improved; by applying the clamp assembly, the reliability of the aero-engine packaging device is ensured, and the possibility of damage of the aero-engine in the transportation process is reduced.

Drawings

Fig. 1 is a schematic structural view of a prior art support bracket assembly.

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

Fig. 3 is an exploded view of a clip assembly according to one 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 section reference numerals

Half ring part 1'

Mounting hole 2'

Connecting shaft 3'

Pull rod 4'

Clamp assembly 5'

Support frame assembly 100'

Description of the reference numerals

Clamp assembly 10

First clamp 1

First concave portion 11

Through hole 12

Second clamping band 2

Second concave portion 21

Screw hole 22

Mounting hole 3

Fastener 4

Spacing bump 5

Lead angle 51

Limiting groove 6

Connecting shaft 7

Step portion 71

Lock nut 8

Bushing 9

First half ring portion 91

Second half ring portion 92

Detailed Description

The invention is further illustrated by means of examples which follow, without thereby restricting the scope of the invention thereto.

The present embodiment provides an aircraft engine packaging device and a clip assembly 10 thereof, wherein, as shown in fig. 3 to 5, the clip assembly 10 includes a first clip 1, a second clip 2, and a fastener 4, the first clip 1 has a first recess 11, the second clip 2 has a second recess 21, the first recess 11 is located opposite to the second recess 21 and forms a mounting hole 3, and the mounting hole 3 can be used to accommodate and fix a connecting shaft 7.

The fastener 4 is used to detachably connect the first clip 1 and the second clip 2 together, and the fastener 4 is preferably a screw or bolt. The first clamp 1 and the second clamp 2 form the mounting hole 3 after being connected, and the connecting shaft 7 can be buckled in the mounting hole 3, so that the convenient installation of the connecting shaft 7 is facilitated, and the first clamp 1 and the second clamp 2 are detachably connected, so that the engine can be conveniently disassembled and assembled with the clamp assembly 10.

The X direction, Y direction, and Z direction in this 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 between the first clamp 1 and the second clamp 2; the Y direction is the direction perpendicular to the X direction and the Z direction.

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

The first clip 1 has a limit projection 5 projecting toward the second clip 2, the limit projection 5 being located outside the second clip 2. Since the limit protrusion 5 is located at the outer side of the second clip 2, when a tendency of relative translational movement occurs between the first clip 1 and the second clip 2 under the action of an external load, the limit protrusion 5 can share at least a portion of the external load (i.e., a portion of the load in the Y direction), thereby preventing the external load from being completely applied to the fastener 4, thereby reducing the load of the fastener 4, particularly, the impact load of the fastener 4 in the Y direction, reducing the risk of failure of the clip assembly 10, and improving the safety of the clip assembly 10. Preferably, the root of the limiting protrusion 5 is provided with a corner guide 51 to reduce stress concentration at the root of the limiting protrusion 5 and improve the bearing capacity of the limiting protrusion 5.

In this embodiment, as shown in fig. 3 and 4, the second clip 2 is provided with a limit groove 6, and the limit projection 5 is fittingly inserted into the limit groove 6. The limiting groove 6 plays a certain limiting role on the limiting protrusion 5, and the limiting protrusion 5 is limited as far as possible on the interface parallel to the first clamp 1 and the second clamp 2. In particular, in this embodiment, the limiting projection 5 is completely limited in the X direction, and is limited on one side in the Y direction. The components of the external load in the direction parallel to the interface are therefore mainly applied to the limit projection 5, whereas the external load applied to the fastener 4 is mainly in the Z-direction, thus greatly reducing the load on the fastener 4 and the risk of failure of the fastener 4. In addition, when the fastener 4 is designed and selected, the fastener 4 can be reinforced mainly in the direction perpendicular to the interface, and loads in other directions can be resisted less, so that the flexibility of the fastener 4 in the selection and design is improved. In addition, the cooperation of limit bulge 5 and spacing groove 6 is also favorable to the assembly counterpoint of clamp subassembly 10, is convenient for the installation of clamp subassembly 10.

The two different sides of the first clamping hoop 1 are respectively provided with a limiting bulge 5. Because the two sides of the first clamp 1 are respectively provided with the limiting protrusions 5, the limiting protrusions 5 simultaneously limit the two different sides of the second clamp 2, the reliability of connection between the first clamp 1 and the second clamp 2 is improved, and the load can be borne in different directions, so that the load applied to the fastening piece 4 is further reduced, and the overall reliability and safety of the clamp assembly 10 are improved.

In particular, in the present embodiment, as shown in fig. 3 and 4, the first clip 1 is disposed above the second clip 2, and the first recess 11 and the second recess 21 are both semi-annular. The interface of the first clamp 1 and the second clamp 2 is a horizontal plane, and the screw extends along the vertical direction. The first clip 1 has two limit protrusions 5, and the mounting hole 3 is located between the two limit protrusions 5 (one of the limit protrusions 5 is not shown in the drawing). Correspondingly, the second clamp 2 is provided with two limit grooves 6 which are in one-to-one correspondence with the limit protrusions 5, after the limit grooves 6 are matched with the limit protrusions 5, the first clamp 1 and the second clamp 2 are completely limited in the horizontal direction, so that under ideal conditions, external load in the horizontal direction acts on the limit protrusions 5 completely, the first clamp 1 and the second clamp 2 can be guaranteed not to generate relative displacement in the horizontal direction, and the screw can not bear load in the horizontal direction completely.

In some other preferred embodiments, the limiting projection 5 has a first inner side and a second inner side that are angled, and the second clip 2 has a first outer side and a second outer side that are angled, the first inner side mating with the first outer side and the second inner side mating with the second outer side.

Under the combined action of the first inner side surface and the second inner side surface, the single limiting bulge 5 can bear external loads in multiple directions simultaneously under the condition of not using the limiting groove 6 of the second clamp 2, so that the bearing capacity of the limiting bulge 5 is improved, the bearing load of the fastener 4 is further shared, and the processing difficulty of the second clamp 2 is also reduced. 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 clip 2. For example, the cross section of the limit projection 5 may be L-shaped. Alternatively, the cross section of the limiting protrusion 5 may be approximately C-shaped, i.e. the limiting protrusion 5 further has a third inner side surface, the first inner side surface being perpendicular to the second inner side surface, the second inner side surface being perpendicular to the third inner side surface, and the limiting protrusion 5 being partially enclosed at a side portion of the second clip 2.

Furthermore, the limit projection 5 can also partly surround the outside of the second clip 2. Since the limit projection 5 partially surrounds the second clip 2, a single limit projection 5 can be made to bear loads in multiple directions without affecting the mounting of the connecting shaft 7. For example, the cross section of the limiting projection 5 may be arc-shaped, and accordingly, the second clip 2 has an arc-shaped outer side surface which is matched with the arc-shaped limiting projection 5.

The limit projection 5 is located on a first side of the clip assembly 10, which is a side different from both sides of the mounting hole 3 in the axial direction. The first side of the clamp assembly 10 is not located on two sides of the mounting hole 3 in the axial direction, so that the limiting protrusion 5 is far away from the connecting shaft 7, and when the clamp assembly 10 is used for mounting the connecting shaft 7, the limiting protrusion 5 cannot interfere with the connecting shaft 7, and the influence of the limiting protrusion 5 on the dismounting of the connecting shaft 7 is reduced as much as possible. In this embodiment, as shown in fig. 3, the limiting protrusion 5 is located at the Y-direction side of the clip assembly 10, but not at the X-direction side of the clip assembly 10, so that the limiting protrusion 5 is away from the mounting hole 3 and the connection shaft 7.

In some other preferred embodiments, the second clip 2 has a limit projection projecting toward the first clip 1, the limit projection being located outside the first clip 1. Similar to the limit projection 5, the limit projection also serves to share the load in the direction of the interface of the first clip 1 and the second clip 2, thereby further reducing the external load acting on the fastener 4. Preferably, the spacing protrusion 5 and the spacing bump are located on different sides (e.g., opposite sides) of the clamp assembly 10 so that the spacing protrusion 5 and the spacing bump can act cooperatively 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 internal bore for receiving the connecting shaft 7. The connecting shaft 7 is installed in the inner hole, and the bushing 9 is arranged between the clamp assembly 10 and the connecting shaft 7 to improve the fixing effect of the clamp assembly 10 to the connecting shaft 7. The bushing 9 includes a first half ring portion 91 located in the first recess 11, and a second half ring portion 92 located in the second recess 21. The first semi-ring portion 91 and the second semi-ring portion 92 enclose an inner hole together, and only the first semi-ring portion 91 and the second semi-ring portion 92 need to be buckled on the outer side of the connecting shaft 7 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 mounted in the inner hole, and the connecting shaft 7 is axially positioned by the lock nut 8 and its own stepped portion 71, so that the connecting shaft 7 is completely positioned.

According to the aero-engine packaging device, due to the fact that the clamp assembly 10 is used, at least part of external load can be shared by the limiting protrusions 5, so that the external load is prevented from being completely acted on the fastening piece 4, the load of the fastening piece 4 is reduced, the risk of failure of the clamp assembly 10 is reduced, the safety of the clamp assembly 10 is improved, the reliability of the aero-engine packaging device is guaranteed, and the possibility of damage of the aero-engine in the transportation process is reduced. Specifically, the aircraft engine packaging device may be a packaging box or a supporting frame, or may be a carrier vehicle to which the clip assembly 10 is mounted.

In the description of the present invention, it should 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 the device or component in normal use, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or component in question must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed 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 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 principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.

Claims (7)

1. An aircraft engine packaging device comprises a support frame assembly, wherein the support frame assembly comprises two connecting shafts correspondingly connected with two front mounting sections of an aircraft engine and two pull rods correspondingly connected with two rear mounting sections of the aircraft engine, the center of gravity of the aircraft engine is close to the front mounting sections, the connecting shafts are fixed on the support frame assembly through a clamp assembly, and the aircraft engine packaging device is characterized in that,

the clip assembly includes:

a first clip having a first recess;

a second clip having a second recess, the first recess being located opposite the second recess and forming a mounting hole for receiving and securing a connection shaft;

a fastener for detachably connecting the first clip and the second clip together;

the clamping device is characterized in that two different sides of the first clamping band are respectively provided with a limiting protrusion extending towards the second clamping band, the limiting protrusions are located on the outer side of the second clamping band, the second clamping band is provided with limiting grooves corresponding to the limiting protrusions respectively, the limiting protrusions are inserted into the limiting grooves in a matched mode, so that the limiting protrusions are limited in the direction parallel to the joint surface of the first clamping band and the second clamping band, and further components of external load in the direction parallel to the joint surface are all applied to the limiting protrusions.

2. The aircraft engine packaging device of claim 1, wherein the limit projection has first and second angled inner sides, and the second clip has first and second angled outer sides, the first and second inner sides mating with the first outer side, and the second inner side mating with the second outer side.

3. The aircraft engine packaging device according to claim 1, wherein the limit projection partially surrounds the outer side of the second clip.

4. The aircraft engine packaging device of claim 1, wherein said stop tab is located on a first side of said yoke assembly, said first side being a different side than the axial sides of said mounting hole.

5. The aircraft engine packaging device according to claim 1, wherein the second clip has a limit tab projecting toward the first clip, the limit tab being located outside of the first clip.

6. The aircraft engine packaging device according to any one of claims 1-5, wherein the yoke assembly further comprises a bushing matingly disposed within the mounting hole, the bushing having an inner bore for receiving a connecting shaft.

7. The aircraft engine packaging device of claim 6, wherein said bushing includes a first half-ring portion located within said first recess and a second half-ring portion located within said second recess.