Connection compensation structure of airplane pipeline system

Abstract

The utility model relates to the technical field of pipeline compensation, and discloses a connection compensation structure of an aircraft pipeline system, which comprises a first connected pipeline, a second connected pipeline and a middle section arranged between the first connected pipeline and the second connected pipeline, the first connected pipeline and one end of the middle section are each provided with an inclined flaring structure, and the other end of the middle section and one end of the second connected pipeline are each provided with a spherical flaring structure. By means of the inclined flaring structure and the spherical flaring structure, the spherical surface of the spherical flaring is matched with the inclined surface of the inclined flaring to form a revolution surface, angular compensation and transverse compensation are achieved, connection is reliable, pipeline safety and reliability are effectively improved, and safety of aero-engines and airplanes is further improved.

Description

Technical Field

[0001] The utility model relates to the technical field of pipeline compensation, in particular to a connection compensation structure of an aircraft pipeline system. Background Art

[0002] Aircraft engine and aircraft piping systems have complex paths and operate in harsh conditions. Manufacturing tolerances, assembly, and deformation due to stress and heat all impact safety. Piping is often segmented, so connecting structures are required to ensure reliable connections and provide some compensation.

[0003] The existing structures include:

[0004] Sliding joints, such as those described in the existing patent CN 214839212 U, can provide axial, angular, and lateral compensation, but their seals are prone to failure, require high fitting precision, cannot adjust the sealing effect, and are prone to disengagement due to large axial deformation, making them unsuitable for high-temperature and high-pressure working conditions.

[0005] Bellows are mainly used to compensate for pipeline deformation, but they have no limit and are prone to excessive deformation and damage. In addition, they have poor stability and are prone to instability, causing damage to the pipeline system.

[0006] Spherical joints are mainly used to compensate for angular deformation of pipelines. However, the deformation of pipeline systems is complex, with angular and axial deformations occurring simultaneously. A single spherical joint cannot meet the compensation requirements, and its structure is complex and difficult to process.

[0007] The above structure is complex and cannot meet the requirements of both lateral compensation and reliable connection. Therefore, a connection compensation structure that can meet the requirements of pipeline deformation compensation and reliable connection and sealing is needed. Utility Model Content

[0008] The purpose of the utility model is to solve the problems existing in the prior art and to propose a connection compensation structure for an aircraft piping system.

[0009] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0010] A connection and compensation structure for an aircraft piping system includes a first connected piping, a second connected piping, and an intermediate section disposed between the first connected piping and the second connected piping, wherein one end of each of the first connected piping and the intermediate section is provided with an oblique flaring structure, and the other end of the intermediate section and one end of the second connected piping are both provided with a spherical flaring structure.

[0011] A female fastener head is fixedly provided on the outer side of one end of the first connected pipeline and the middle section, and a male fastener head is movably provided on the outer side of the other end of the middle section and one end of the second connected pipeline, and the male fastener head and the female fastener head are detachably connected. An opening is provided on the side of the male fastener head, and the inner diameter of the opening is larger than the outer diameter of the side of the spherical flaring structure away from the oblique flaring structure.

[0012] Preferably, the male head of the fastener is provided with an external thread, the inner periphery of the male head of the fastener is provided with a guide bevel, and a spherical support structure is provided deep inside the guide bevel.

[0013] Preferably, the female fastener head is provided with an internal thread and is designed as an external hexagonal structure, the internal thread is adapted to the external thread, and the side inner wall of the female fastener head is provided with an inclined support structure, and the inclined support structure is adapted to the oblique flaring structure.

[0014] Preferably, the inclined support structure and the spherical support structure are both made of graphite.

[0015] Preferably, a plurality of slots are provided on the side of the male head of the fastener, and the plurality of slots are arranged in a rectangular array.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] The utility model provides an oblique flaring structure and a spherical flaring structure, wherein the spherical surface of the spherical flaring cooperates with the inclined surface of the oblique flaring to form a rotating surface, thereby realizing angular compensation and lateral compensation, and the connection is reliable, effectively improving the safety and reliability of the pipeline, and further improving the safety of aircraft engines and aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a front view of a connection and compensation structure for an aircraft piping system proposed by the present invention;

[0019] Figure 2 This is a schematic diagram of the connection between the oblique flaring structure and the spherical flaring structure of the connection compensation structure of the aircraft piping system proposed by the present invention;

[0020] Figure 3 This is a cross-sectional view of a male fastener head of a connection compensation structure for an aircraft piping system proposed by the present invention;

[0021] Figure 4 This is a side view of a fastener of a connection and compensation structure of an aircraft piping system proposed by the utility model.

[0022] In the figure: 1. first connected pipeline; 11. oblique flaring structure; 21. middle section; 22. male fastener; 23. female fastener; 211. spherical flaring structure; 221. spherical support structure; 222. slot; 231. oblique support structure; 3. second connected pipeline; 223. guide bevel. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0024] Reference Figures 1-4 A connection and compensation structure for an aircraft piping system includes a first connected pipe 1, a second connected pipe 3, and an intermediate section 21 disposed between the first connected pipe 1 and the second connected pipe 3. An oblique flaring structure 11 is disposed at one end of each of the first connected pipe 1 and the intermediate section 21. The inner wall of the oblique flaring structure 11 is made of a sealing material, such as rubber, and is used to cooperate with a spherical flaring structure 211 to form a sealing surface. The other end of the intermediate section 21 and one end of the second connected pipe 3 are both disposed with a spherical flaring structure 211.

[0025] A female fastener head 23 is fixedly provided on the outer side of one end of the first connected pipeline 1 and the middle section 21, and a male fastener head 22 is movably provided on the outer side of the other end of the middle section 21 and one end of the second connected pipeline 3. The male fastener head 22 and the female fastener head 23 are detachably connected, and an opening is provided on the side of the male fastener head 22, and the inner diameter of the opening is larger than the outer diameter of the spherical flaring structure 211 away from the oblique flaring structure 11.

[0026] When the present structure is in use, the spherical flaring structure 211 cooperates with the oblique flaring structure 11 between the pipelines, and by tightening the male head and the female head, the oblique flaring structure 11 is pressed by the inclined support structure 231, and the spherical support structure 221 presses the spherical flaring structure 211. After circumferential compression, a sealing surface is formed between the two flaring structures. When the inner inclined surface of the male head is squeezed with the oblique flaring structure 11, the oblique flaring structure 11 can produce elastic deformation, thereby increasing the sealing area and improving the sealing reliability. The spherical flaring structure 211 cooperates with the oblique flaring structure 11 and can be deflected within a certain angle while still maintaining sealing contact, thereby performing angular and lateral compensation and maintaining sealing. Compared with the prior art, the present structure, through the provision of the oblique flaring structure 11 and the spherical flaring structure 211, the spherical surface of the spherical flaring cooperates with the inclined surface of the oblique flaring to form a rotating surface, thereby realizing angular compensation and lateral compensation, and the connection is reliable, effectively improving the safety and reliability of the pipeline, and further improving the safety of aircraft engines and aircraft.

[0027] In this embodiment, the fastener male head 22 is provided with an external thread, and the inner periphery of the fastener male head 22 is provided with a guide bevel 223. The guide bevel 223 has a certain angle to facilitate the assembly and tightening of the oblique flare structure 11. A spherical support structure 221 is provided deep in the guide bevel 223. The spherical support structure 221 is installed on the inner wall of the fastener male head 22, and its spherical surface cooperates with the outer surface of the spherical flare.

[0028] In this embodiment, the fastener female head 23 is provided with an internal thread and is designed as an external hexagonal structure. The external hexagonal structure is a standard structure, which is convenient for tool operation. The internal thread is adapted to the external thread, and the internal thread is used to tighten with the external thread. The side inner wall of the fastener female head 23 is provided with an inclined support structure 231, and the inclined support structure 231 is adapted to the oblique flaring structure 11 and has a pressing effect.

[0029] In this embodiment, the materials of the inclined support structure 231 and the spherical support structure 221 are both graphite, which has a lubricating effect.

[0030] In this embodiment, a plurality of slots 222 are provided on the side of the male head 22 of the fastener, and the plurality of slots 222 are arranged in a rectangular array, which is convenient for the tightening operation and the tool clamping.

[0031] The above is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A connection compensation structure for an aircraft piping system, comprising a first connected piping, a second connected piping, and an intermediate section disposed between the first connected piping and the second connected piping, characterized in that: The first connected pipeline and one end of the middle section are both provided with an oblique flaring structure, and the other end of the middle section and one end of the second connected pipeline are both provided with a spherical flaring structure; A female fastener head is fixedly provided on the outer side of one end of the first connected pipeline and the middle section, and a male fastener head is movably provided on the outer side of the other end of the middle section and one end of the second connected pipeline, and the male fastener head and the female fastener head are detachably connected. An opening is provided on the side of the male fastener head, and the inner diameter of the opening is larger than the outer diameter of the side of the spherical flaring structure away from the oblique flaring structure.

2. The connection and compensation structure of an aircraft piping system according to claim 1, characterized in that: The male head of the fastener is provided with an external thread, the inner periphery of the male head of the fastener is provided with a guide bevel, and a spherical support structure is provided deep inside the guide bevel.

3. The connection and compensation structure of an aircraft piping system according to claim 2, characterized in that: The female fastener head is provided with an internal thread and is designed in an external hexagonal structure. The internal thread is adapted to the external thread. The inner wall of the side of the female fastener head is provided with an inclined support structure, and the inclined support structure is adapted to the oblique flaring structure.

4. The connection and compensation structure of an aircraft piping system according to claim 3, characterized in that: The inclined support structure and the spherical support structure are both made of graphite.

5. The connection and compensation structure of an aircraft piping system according to claim 2, characterized in that: A plurality of slots are provided on the side of the male head of the fastener, and the slots are arranged in a rectangular array.

Images