CN213109810U

CN213109810U - Aircraft engine nacelle and aircraft engine

Info

Publication number: CN213109810U
Application number: CN202021056400.1U
Authority: CN
Inventors: 梁晓波; 李雪; 白杰
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-06-10
Filing date: 2020-06-10
Publication date: 2021-05-04
Anticipated expiration: 2030-06-10

Abstract

The utility model relates to an aeroengine nacelle and aeroengine, aeroengine nacelle includes: a first member; a second member spaced from the first member; the sealing component (1) is arranged between the first component and the second component, the sealing component (1) comprises a sealing component body (11) and two protruding parts (12) arranged at one end of the sealing component body (11), and the two protruding parts (12) respectively protrude towards two sides of the sealing component body (11); and the connecting component (2) comprises a first clamping groove (21) and a second clamping groove (22) which are respectively clamped with the two bulges (12), the first clamping groove (21) and the second clamping groove (22) are separately arranged and are connected with the first component, and at least one of the first clamping groove (21) and the second clamping groove (22) is detachably connected with the first component. Use the technical scheme of the utility model, improve the problem of easy damage when the seal part installation difficulty that exists and dismantle among the correlation technique.

Description

Aircraft engine nacelle and aircraft engine

Technical Field

The utility model relates to an aeronautical equipment field particularly, relates to an aeroengine nacelle and aeroengine.

Background

Fig. 1 shows a schematic structural view of a sealing structure of a related art aircraft engine nacelle, and fig. 2 shows a schematic sectional structural view of the sealing structure of the related art aircraft engine nacelle. As shown in connection with fig. 1 and 2, a sealing member 1 is provided between a first member 2 and a second member 3 of a nacelle for an aircraft engine to perform a fire or gas leakage prevention function. The first part 2 is provided with a bayonet slot 4 for mounting the seal 1.

One end of the sealing member 1 is provided with two protrusions 11 protruding toward both sides, respectively. The seal 1 is omega-shaped, optionally the seal 1 is a rubber seal. The uncovered that the inner chamber of draw-in groove 4 has, uncovered inside both sides are provided with respectively with protruding 11 looks adaptations's cavity, and two protruding 11 of sealing member 1 are during the inner chamber of draw-in groove 4 is filled in by draw-in groove 4's uncovered after the extrusion, and protruding 11 is arranged in corresponding cavity to install sealing member 11 on draw-in groove 1. When the seal 1 is removed from the locking groove 4, the seal 1 needs to be pulled out from the locking groove 4.

The mounting distance between the first and

second members

2, 3 is greater than the size of the seal 1 in the expanded state 1a, and the seal 1 is in the compressed state 1b after the first and

second members

2, 3 are fully mounted.

The recess of the locking groove 4 for receiving the protrusion 11 of the sealing element 1 needs to be designed to be shallow in order to be able to easily mount and dismount the sealing element 1, but such a design will also result in a loose fit between the sealing element 1 and the locking groove 4, which may be released in the use state.

Above-mentioned mounting means all need a lot of extrusion sealing member 1, and the operation is got up comparatively difficultly, and the back is dismantled many times very easily damages sealing member 1, leads to the cost-push, and sealing member 1 and draw-in groove 4 cooperation are inseparable.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aeroengine nacelle and aeroengine to improve the problem of easy damage when the seal part installation difficulty that exists and dismantle among the correlation technique.

According to an aspect of the embodiments of the present invention, there is provided an aircraft engine nacelle, including:

a first member;

a second member spaced from the first member;

the sealing component is arranged between the first component and the second component and comprises a sealing component body and two convex parts arranged at one end of the sealing component body, and the two convex parts respectively protrude towards two sides of the sealing component body; and

the connecting part comprises a first clamping groove and a second clamping groove which are respectively clamped with the two bulges, the first clamping groove and the second clamping groove are separately arranged and are connected with the first part, and at least one of the first clamping groove and the second clamping groove is detachably connected with the first part.

In some embodiments, the first card slot comprises:

a first base plate between the sealing member and the first member; and

the first clamping portion is connected to one end of the first base plate and used for clamping the protruding portion.

In some embodiments, the first base plate extends from one side of the seal member toward the other side and beyond a middle portion of the seal member, the first base plate being fixedly attached to the first member.

In some embodiments, the first base plate is connected to the first member by a rivet.

In some embodiments, the second card slot comprises:

a second base plate which is positioned between the sealing member and the first member and is abutted against the first base plate; and

and the second clamping part is connected to one end, far away from the first clamping groove, of the second bottom plate and used for clamping the protruding part.

In some embodiments, the second base plate is removably connected to the first member.

In some embodiments, the second base plate is bolted to the first member.

In some embodiments, the first and second card slots are symmetrically disposed on either side of the sealing member.

In some embodiments, the sealing member abuts the first member.

According to the utility model discloses an on the other hand still provides an aeroengine, and aeroengine includes foretell aeroengine nacelle.

By applying the technical scheme of the utility model, when the sealing component is installed, the first clamping groove can be firstly fixed on the first component, then a convex part of the sealing component is plugged into the first clamping groove, and then the second clamping groove is fixed on the first component; when dismantling sealing member, can dismantle one in first draw-in groove and the second draw-in groove from first part at first, alright dismantle sealing member under the prerequisite that does not harm sealing member, consequently, the technical scheme of this embodiment has improved the problem that sealing member installation difficulty and easy damage when dismantling that exists among the correlation technique.

Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention or the related art, the drawings required to be used in the description of the embodiments or the related art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive labor.

FIG. 1 is a schematic structural view showing a sealing structure of a related art nacelle for an aircraft engine;

FIG. 2 is a schematic cross-sectional structural view showing a sealing structure of a related art nacelle for an aircraft engine;

fig. 3 shows a schematic structural view of a sealing structure of an aircraft engine nacelle according to a first embodiment of the present invention;

FIG. 4 shows a schematic cross-sectional structural view of a sealing structure of the nacelle of the aircraft engine shown in FIG. 3;

fig. 5 shows a structural schematic view of a sealing structure of an aircraft engine nacelle according to a second embodiment of the present invention; and

FIG. 6 shows a schematic cross-sectional structural view of the sealing structure of the nacelle of the aircraft engine shown in FIG. 5.

In the figure:

1. a sealing member; 11. a seal member body; 12. a projection; 2. a connecting member; 21. A first card slot; 211. a first base plate; 212. a first clamping part; 22. a second card slot; 221. A second base plate; 222. a second clamping part; 3. riveting; 4. a bolt; 5. and (4) bolts.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

Example one

FIG. 3 is a schematic structural view showing a sealing structure of the nacelle for an aircraft engine of the present embodiment; fig. 4 shows a schematic cross-sectional structural view of the sealing structure of the nacelle of the aircraft engine shown in fig. 3.

Referring to fig. 3 and 4, in the present embodiment, the nacelle for an aircraft engine includes a first member, a second member disposed apart from the first member, a sealing member 1 and a connecting member 2 disposed between the first member and the second member.

The sealing member 1 includes a sealing member body 11 and two protruding portions 12 provided at one end of the sealing member body 11, and the two protruding portions 12 protrude toward both sides of the sealing member body 11, respectively.

The connecting part 2 includes a first engaging groove 21 and a second engaging groove 22 respectively engaging with the two protrusions 12, the first engaging groove 21 and the second engaging groove 22 are separately disposed and are both connected to the first part, and at least one of the first engaging groove 21 and the second engaging groove 22 is detachably connected to the first part.

In this embodiment, when the sealing member 1 is mounted, the first engaging groove 21 may be first fixed to the first member, then one of the protruding portions 12 of the sealing member 1 is inserted into the first engaging groove 21, and then the second engaging groove 22 is fixed to the first member; when the sealing component 1 is disassembled, one of the first clamping groove 21 and the second clamping groove 22 can be disassembled from the first component at first, and the sealing component 1 can be disassembled on the premise of not damaging the sealing component, so that the technical scheme of the embodiment improves the problems that the sealing component is difficult to install and easy to damage during disassembly in the related technology.

In the present embodiment, the cross section of the sealing member 1 is Ω -shaped.

As shown in fig. 4, the first card slot 21 includes a first bottom plate 211 and a first card portion 212. The first bottom plate 211 is located between the sealing member 1 and the first member; the first clamping portion 212 is connected to one end of the first base plate 211 for clamping the protrusion 12.

The first base plate 211 extends from one side of the sealing member 1 to the other side, and exceeds the middle of the sealing member 1, and the first base plate 211 is fixedly connected to the first member.

In some embodiments, the first base plate 211 is connected to the first member by rivets 3.

The second card slot 22 includes a second bottom plate 221 and a second card portion 222. The second bottom plate 221 is positioned between the seal member 1 and the first member, and abuts against the first bottom plate 211; the second clamping portion 222 is connected to an end of the second bottom plate 221 away from the first clamping groove 21 for clamping the protrusion 12.

In this embodiment, the second base plate 221 is detachably connected to the first member.

In some embodiments, the second base plate 221 is connected to the first member by bolts 4.

When the sealing component 1 is assembled on the first component, the first clamping groove 21 is firstly installed on the first component of the aircraft engine nacelle through the rivet 3, then the sealing component 1 is placed in place, and finally the second clamping groove 22 is fixed on the first component through the bolt 4. When the sealing member 1 is detached from the connecting member 2, the second engaging groove 22 may be detached from the first member, and then the sealing member 1 may be removed.

According to the utility model discloses a further aspect provides an aeroengine, and this aeroengine includes foretell aeroengine nacelle.

Example two

FIG. 5 is a schematic structural view showing a sealing structure of the nacelle for an aircraft engine of the present embodiment; FIG. 6 shows a schematic cross-sectional structural view of the sealing structure of the nacelle of the aircraft engine shown in FIG. 5.

As shown in fig. 5 and 6, the present embodiment is different from the first embodiment in that: the first and

second card slots

21 and 22 are symmetrically disposed at both sides of the sealing member 1. The seal member 1 abuts against the first member. One or both of the first card slot 21 and the second card slot 22 are connected to the first component by the bolt 5.

The above description is only exemplary embodiments of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine nacelle, comprising:

a first member;

a second member spaced from the first member;

the sealing component (1) is arranged between the first component and the second component, the sealing component (1) comprises a sealing component body (11) and two protruding parts (12) arranged at one end of the sealing component body (11), and the two protruding parts (12) respectively protrude towards two sides of the sealing component body (11); and

the connecting component (2) comprises a first clamping groove (21) and a second clamping groove (22) which are respectively clamped with the two protrusions (12), the first clamping groove (21) and the second clamping groove (22) are separately arranged and are connected with the first component, and at least one of the first clamping groove (21) and the second clamping groove (22) is detachably connected with the first component.

2. The nacelle according to claim 1, characterised in that said first blocking slot (21) comprises:

a first bottom plate (211) located between the sealing member (1) and the first member; and

and the first clamping part (212) is connected to one end of the first base plate (211) and is used for clamping the protruding part (12).

3. The nacelle according to claim 2, characterised in that the first floor (211) extends from one side of the sealing element (1) towards the other and beyond the middle of the sealing element (1), the first floor (211) being fixedly connected to the first element.

4. The nacelle according to claim 3, characterised in that the first floor (211) and the first component are connected by means of rivets (3).

5. The aircraft engine nacelle according to claim 2, characterised in that said second blocking slot (22) comprises:

a second bottom plate (221) which is positioned between the seal member (1) and the first member and which abuts against the first bottom plate (211); and

and the second clamping part (222) is connected to one end, far away from the first clamping groove (21), of the second bottom plate (221) and used for clamping the protruding part (12).

6. The nacelle according to claim 5, characterised in that the second floor (221) is removably connected to the first component.

7. The nacelle according to claim 6, characterised in that the second floor (221) is connected to the first component by means of bolts (4).

8. The aircraft engine nacelle according to claim 1, characterised in that the first and second clamping grooves (21, 22) are symmetrically arranged on both sides of the sealing part (1).

9. The nacelle according to claim 8, characterised in that the sealing component (1) abuts against the first component.

10. An aircraft engine comprising an aircraft engine nacelle according to any of claims 1 to 9.