Inserted lip-shaped sealing structure for high-pressure pipeline of aero-engine

Abstract

The invention belongs to the field of pipeline systems, and particularly relates to a plug-in lip-shaped sealing structure for a high-pressure pipeline of an aero-engine. According to the structure, a boss is arranged on the outer side of a movable connector, and a first annular groove and a second annular groove are formed in the boss; a stepped hole is formed in the inner side of the movable connecting nozzle, the movable connector is sleeved with the movable connecting nozzle, the inner side of the movable connecting nozzle is in clearance fit with the boss, and an external thread section is arranged on the outer side of the movable connecting nozzle; the movable joint nut is arranged on the movable joint and the movable mouthpiece in a sleeving manner, the inner side of the movable joint nut performs unilateral axial limiting on the movable joint through the check ring, and the movable joint nut is in threaded fit with the external thread section of the movable mouthpiece; the rubber ring is mounted in the first annular groove; and the lip-type K-shaped protection ring is mounted in the second annular groove. The problem of oil leakage of a large-pipe-diameter pipeline of a high-pressure working medium can be solved, the sealing capacity of a pipeline connecting part is improved, and then the working reliability of an engine is improved.

Description

Technical Field

[0001] This application belongs to the field of pipeline systems, and specifically relates to an insert-type lip seal structure for high-pressure pipelines of aero-engines. Background Technology

[0002] In various engineering fields such as aerospace, special vehicles, marine vessels, and oil and gas, pipeline systems are ubiquitous in their power, braking, cooling, and lubrication systems, serving as an indispensable and crucial component. In the external piping systems of aero-engines, pipeline joint seals have a wide range of applications. These seals connect conduits, valves, sensors, and other structures to form the entire delivery system, preventing leakage of high-pressure media within the pipeline system.

[0003] Separable pipeline joint seals for aviation include 74-degree conical seals, spherical seals, and beam seals. The sealing band contact clamping force of these seal types is provided by the axial preload generated by the tightening torque applied to the outer nut. In existing engine technology, small-diameter pipeline seals typically employ 74-degree conical or spherical seal structures. Under the axial preload generated by the tightening torque applied to the outer nut, the outer nut compresses the inner conical joint, causing the conical surfaces of the inner and outer conical joints to press against each other, forming a sealing area between them. Large-diameter pipeline seals use flange-type or insert-type rubber ring seal structures, forming a sealing band through the compression deformation of the rubber ring. When the medium pressure is high and the pipe diameter is large, repeated relative displacement occurs between the joints under the repeated impact of the working medium. The rubber ring is locally squeezed into the gap between the joints and repeatedly rubbed and twisted. After prolonged engine operation, this easily causes damage to the rubber ring, making it difficult to guarantee a reliable seal between pipelines and affecting engine safety.

[0004] Currently, the pressure of the working medium in aero-engine pipelines is increasing, and the pipe diameter is also increasing. During actual service, due to vibration, high and low temperature environments, and the infiltration and lubrication of internal fluid media, the thread friction and sealing contact pressure change, which may lead to poor sealing of the contact surface and fluid leakage. This can cause hydraulic system failure or even flight accidents. Therefore, the sealing of pipeline systems, especially high-pressure, large-diameter pipelines, is a very important engineering problem.

[0005] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0006] The purpose of this application is to provide an insert-type lip seal structure for high-pressure pipelines of aircraft engines to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is:

[0008] An insert-type lip seal structure for high-pressure pipelines in aero-engines includes:

[0009] The movable joint has a boss on its outer side, and the boss has a first annular groove and a second annular groove.

[0010] The movable connector has a stepped hole formed on its inner side. The movable connector is sleeved on the movable joint. The inner side of the movable connector is clearance-fitted with the boss. The outer side of the movable connector is provided with an external thread section.

[0011] A movable joint nut is sleeved on the movable joint and the movable nozzle. The inner side of the movable joint nut is axially limited on one side by a retaining ring. The movable joint nut is threadedly engaged with the external thread section of the movable nozzle.

[0012] A rubber ring, wherein the rubber ring is installed in the first annular groove;

[0013] A lip-type K-shaped protective ring is installed in the second annular groove.

[0014] In at least one embodiment of this application, the end of the movable connector away from the movable nozzle is welded to the conduit.

[0015] In at least one embodiment of this application, the end of the movable nozzle away from the movable connector is welded to the conduit.

[0016] In at least one embodiment of this application, the movable joint is provided with a chamfer at one end near the second annular groove to facilitate the installation of the lip-type K-shaped protective ring.

[0017] In at least one embodiment of this application, the lip-type K-shaped protective ring includes an upper lip body, a lower lip body, and a support body, wherein,

[0018] The upper lip abuts against the inner side of the movable nozzle, and the lower lip abuts against the bottom surface of the second annular groove, forming a first sealing pair;

[0019] The outer ring of the support body abuts against the inner side of the movable connector, and the inner ring abuts against the bottom surface of the second annular groove, forming a second sealing pair.

[0020] In at least one embodiment of this application, the material of the lip-type K-shaped protective ring is non-metallic.

[0021] In at least one embodiment of this application, the outer ring of the rubber ring abuts against the inner side of the movable connector, and the inner ring abuts against the bottom surface of the first annular groove, forming a third sealing pair.

[0022] The invention has at least the following beneficial technical effects:

[0023] The high-pressure pipeline insertion lip seal structure of this application is suitable for sealing connections of high-pressure, large-diameter pipelines in aero engines. It can solve the problem of oil leakage in large-diameter pipelines with high-pressure working media, improve the sealing capability of pipeline connections, and thus improve the reliability of engine operation. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of an insert-type lip seal structure for a high-pressure pipeline of an aircraft engine according to one embodiment of this application;

[0025] Figure 2 This is a schematic diagram of a sealing pair according to one embodiment of this application.

[0026] in:

[0027] 1-Modible connector; 2-Modible connector nut; 3-Modible connector; 4-Rubber ring; 5-Lip K-shaped protective ring. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0029] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0030] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0031] This application provides an insert-type lip seal structure for high-pressure pipelines of aircraft engines, including: a movable joint 1, a movable joint nut 2, a movable nozzle 3, a rubber ring 4, and a lip-type K-shaped protective ring 5.

[0032] Specifically, such as Figure 1 As shown, the movable joint 1 is cylindrical with an inner hole on the inner side. A boss is provided at one end of the outer side of the movable joint 1. A first annular groove and a second annular groove are provided on the boss. The second annular groove is closer to the end of the movable joint 1 than the first annular groove.

[0033] The movable connector 3 includes a first connector section and a second connector section, both of which are cylindrical with an inner bore. The inner bore diameter of the first connector section is larger than that of the second connector section, and the inner bore diameter of the second connector section is equal to that of the movable connector 1. The inner bores of the two connector sections form a stepped hole. The first connector section is fitted onto the movable connector 1, and the inner side of the first connector section is clearance-fitted with the boss of the movable connector 1. Simultaneously, the stepped hole of the movable connector 3 can limit the movement of the movable connector 1. An external thread section is provided on the outer side of the first connector section.

[0034] The movable joint nut 2 is sleeved on the movable joint 1 and the movable nozzle 3. The inner side of the movable joint nut 2 is axially limited on one side of the movable joint 1 by a stop ring to prevent the movable joint 1 from moving in the direction of medium flow. The movable joint nut 2 is threadedly engaged with the external thread section of the movable nozzle 3.

[0035] The rubber ring 4 is installed in the first annular groove; the lip-type K-shaped protective ring 5 has a K-shaped cross-section and is installed in the second annular groove.

[0036] In a preferred embodiment of this application, the end of the movable connector 1 furthest from the movable nozzle 3 is designed as a welded structure and is welded integrally with the conduit. The end of the movable nozzle 3 furthest from the movable connector 1 is designed as a welded structure and is welded integrally with the conduit.

[0037] In a preferred embodiment of this application, the movable joint 1 is provided with a chamfer at one end near the second annular groove to facilitate the installation of the lip-type K-shaped protective ring 5.

[0038] like Figure 2As shown, in a preferred embodiment of this application, the lip-type K-shaped protective ring 5 includes an upper lip, a lower lip, and a support. The upper lip deforms under medium pressure and abuts against the inner side of the movable connector 3, while the lower lip deforms under medium pressure and abuts against the bottom surface of the second annular groove, forming a first sealing pair. The outer ring of the support has an initial size slightly larger than the inner hole size of the movable connector 3, and the inner ring has an initial size slightly smaller than the groove size of the movable connector 1. The outer ring of the support abuts against the inner side of the movable connector 3, and the inner ring abuts against the bottom surface of the second annular groove, forming a second sealing pair. The lip-type K-shaped protective ring 5 is made of non-metallic material. In this embodiment, the outer ring of the rubber ring 4 abuts against the inner side of the movable connector 3, and the inner ring abuts against the bottom surface of the first annular groove. The rubber ring 4 undergoes elastic compression deformation between the groove of the movable connector 1 and the inner hole of the movable connector 3, forming a third sealing pair.

[0039] The high-pressure pipeline insertion lip seal structure of this application has a K-shaped protective ring 5. When the support body is pre-compressed, it generates a rebound force. The upper and lower end faces and the side edges contact the groove of the movable joint 1 and the movable nozzle 3 and generate a self-tightening seal. At the same time, it provides radial support for the movable joint 1 and the rubber ring 4, reducing the relative displacement between the joints under repeated impact of the medium.

[0040] The high-pressure pipeline insertion lip seal structure of this application for aero-engines has a lip K-shaped protective ring 5 installed at the front end of the movable joint 1, which cooperates with the rubber ring 5 to form a multi-seal structure between the movable joint 1 and the movable nozzle 3. It is easy to install, has a simple and compact structure, and can realize the connection and sealing of large-diameter pipelines for high-pressure working media.

[0041] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft engine high pressure line plug lip seal structure, comprising: include: The movable joint (1) has a boss on its outer side, and a first annular groove and a second annular groove are provided on the boss. The movable connector (3) has a stepped hole formed on its inner side. The movable connector (3) is sleeved on the movable joint (1). The inner side of the movable connector (3) is in clearance fit with the boss. The outer side of the movable connector (3) is provided with an external thread section. The movable joint nut (2) is sleeved on the movable joint (1) and the movable nozzle (3). The inner side of the movable joint nut (2) is axially limited on one side by a stop ring. The movable joint nut (2) is threadedly engaged with the external thread section of the movable nozzle (3). A rubber ring (4) is installed in the first annular groove; A lip-type K-shaped protective ring (5) is installed in the second annular groove.

2. The insertion-type lip seal structure for high-pressure pipelines of aero-engines according to claim 1, characterized in that, The end of the movable connector (1) away from the movable nozzle (3) is welded to the conduit.

3. The insertion-type lip seal structure for high-pressure pipelines of aero-engines according to claim 2, characterized in that, The end of the movable nozzle (3) away from the movable connector (1) is welded to the conduit.

4. The insertion-type lip seal structure for high-pressure pipelines of aero-engines according to claim 3, characterized in that, The movable joint (1) has a chamfered corner at one end near the second annular groove to facilitate the installation of the lip-type K-shaped protective ring (5).

5. The insert-type lip seal structure for high-pressure pipelines of aero-engines according to claim 4, characterized in that, The lip-type K-shaped protective ring (5) includes an upper lip body, a lower lip body, and a support body, wherein, The upper lip abuts against the inner side of the movable nozzle (3), and the lower lip abuts against the bottom surface of the second annular groove, forming a first sealing pair; The outer ring of the support body abuts against the inner side of the movable connector (3), and the inner ring abuts against the bottom surface of the second annular groove, forming a second sealing pair.

6. The insert-type lip seal structure for high-pressure pipelines of aero-engines according to claim 5, characterized in that, The material of the lip-type K-shaped protective ring (5) is non-metallic.

7. The insert-type lip seal structure for high-pressure pipelines of aero-engines according to claim 6, characterized in that, The outer ring of the rubber ring (4) abuts against the inner side of the movable connector (3), and the inner ring abuts against the bottom surface of the first annular groove, forming a third sealing pair.

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