Sealing structure of aero-engine double-layer outer culvert penetrating casing structure

Abstract

The invention belongs to the technical field of sealing design of aero-engine double-layer outer culvert casing structures, and particularly relates to a sealing structure of an aero-engine double-layer outer culvert casing structure, which is characterized in that sealing is realized by only designing a sliding sleeve and a floating ring, connection on an outer culvert casing can be realized by a small number of bolts and connecting pieces thereof, the disassembly and assembly are simple and convenient, and the sealing effect is good. The sliding sleeve is arranged in a manner of crossing an outer culvert flow path between the outer-layer casing and the inner-layer casing, so that the problem that the assembly space between the outer-layer casing and the inner-layer casing is insufficient can be effectively avoided, interference with the outer-layer casing is avoided, disassembly and assembly are facilitated, and due to the design of an annular mounting flange on the sliding sleeve, the situation that the sliding sleeve falls into the outer culvert flow path is avoided; and good assembly and maintenance characteristics are realized.

Description

Technical Field

[0001] This application belongs to the technical field of the sealing design of the structure of an aero-engine with a double-layer outer casing, and particularly relates to a sealing structure of the structure of an aero-engine with a double-layer outer casing. Background Art

[0002] The outer casing is an important component of an aero-engine. The traditional configuration of an aero-engine has only one outer flow path, and the used outer casing is a single layer. The single-layer outer casing and the inner core engine component casing form an outer flow path. The new configuration of an aero-engine has a double outer flow path. In addition to forming an outer flow path with the inner core engine component casing, the outer casing itself adopts a double-layer structure, that is, a double-layer casing. A second outer flow path is formed between the double-layer outer casings.

[0003] There are various structures passing through the outer casing on the outer casing of an aero-engine, such as ventilation pipelines, oil pipelines, lead pipelines, exploration channels, etc., and sealing needs to be carried out at the outer casing. The structures passing through the outer casing are usually fixed on the core engine casing. During the operation of the aero-engine, due to the different materials and working temperatures of the outer casing and the core engine casing, the thermal expansion amounts generated by heat are also different, and there will be a large deformation difference in the axial and radial directions. Therefore, when designing the sealing structure of the structure passing through the outer casing, corresponding thermal compensation needs to be considered to avoid generating large stresses between the outer casing and the core engine casing.

[0004] Currently, for the sealing structure of the structure passing through the outer casing of an aero-engine at the outer casing, a floating seal structure is usually adopted. For the structure of a double-layer outer casing, the design of the floating seal structure is as Figure 1 shown. On the outer layer casing and the inner layer casing, a sliding sleeve and its floating ring are respectively arranged. By using the relative movement between the structure of the double-layer outer casing and the floating ring, and between the floating ring and the sliding sleeve, the thermal compensation for the double-layer outer casing and the core engine casing is realized. This technical solution has the following defects:

[0005] 1) On the outer layer casing and the inner layer casing, a sliding sleeve and its floating ring are respectively arranged, which requires a large number of bolts and their connecting parts for connection. The disassembly and assembly process is cumbersome, and the space between the outer layer casing and the inner layer casing is narrow, and there is insufficient assembly space. It is inconvenient to disassemble and assemble the sliding sleeve and its floating ring arranged on the inner layer casing, and it is easy to interfere with the outer layer casing.

[0006] 2) The sliding sleeve and its floating ring arranged on the inner layer outer casing are in the outer flow path. During the disassembly and assembly process, they may fall into the outer flow path and are difficult to take out, which greatly increases the difficulty of the structure in terms of assembly and maintenance.

[0007] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0008] The object of the present application is to provide a floating seal structure for a sealing structure of an aeroengine with a double-layer outer casing structure, so as to overcome or mitigate at least one aspect of the known technical defects.

[0009] The technical solution of the present application is as follows:

[0010] A sealing structure for an aeroengine with a double-layer outer casing structure, characterized by comprising an outer casing, an inner casing, a sliding sleeve, a floating ring, and a cover plate;

[0011] The outer casing has an outer casing mounting hole, and an outer annular mounting boss surrounding the outer casing mounting hole on the outer wall;

[0012] The inner casing is arranged inside the outer casing, and has an inner casing mounting hole thereon, and an inner annular mounting boss protruding towards the outer casing, the inner annular mounting boss surrounds the inner casing mounting hole, and an annular channel communicating with its interior is provided on the inner annular mounting boss;

[0013] The double-layer outer casing structure passes through the inner casing mounting hole and the outer casing mounting hole;

[0014] The lower end of the sliding sleeve passes through the outer casing mounting hole and extends into the annular channel, and the outer wall is in sealing contact with the inner wall of the annular channel. The upper end outer wall has an annular mounting flange, and the annular mounting flange is located outside the outer casing;

[0015] The floating ring is arranged inside the sliding sleeve, the outer edge is in sealing contact with the inner wall of the sliding sleeve, the inner edge is stuck in an annular floating groove formed on the double-layer outer casing structure, and there is an active gap with the annular floating groove;

[0016] The cover plate is sleeved on the outer periphery of the sliding sleeve, there is an active gap with the sliding sleeve, it is connected to the outer wall of the outer casing, and an annular mounting groove is formed with the outer casing. The annular mounting flange is stuck in the annular mounting groove, and there is an active gap with the annular mounting groove.

[0017] According to at least one embodiment of the present application, in the above-mentioned sealing structure for an aeroengine with a double-layer outer casing structure, the outer wall of the lower end of the sliding sleeve is in spherical contact with the inner wall of the annular channel.

[0018] According to at least one embodiment of the present application, in the above-mentioned sealing structure for an aeroengine with a double-layer outer casing structure, the outer edge of the floating ring is in spherical contact with the inner wall of the sliding sleeve.

[0019] According to at least one embodiment of the present application, in the above-mentioned sealing structure for an aeroengine with a double-layer outer casing structure, the floating ring is of a split structure.

[0020] According to at least one embodiment of the present application, in the sealing structure of the double-layer outer casing structure of an aero-engine, the cover plate is bolted to the outer wall of the outer casing.

[0021] The present application has at least the following beneficial technical effects:

[0022] A sealing structure for a double-layer outer casing structure of an aero-engine is provided. Only a sliding sleeve and a floating ring are designed to achieve sealing. The connection on the outer casing can be realized with a relatively small number of bolts and their connectors, and the disassembly and assembly are simple and convenient. Moreover, the sliding sleeve is arranged across the outer flow path between the outer casing and the inner casing, which can effectively avoid the problem of insufficient assembly space between the outer casing and the inner casing, will not interfere with the outer casing, and is convenient for disassembly and assembly. Due to the design of the annular mounting flange on the sliding sleeve, it will not fall into the outer flow path, and it has good assembly and maintenance characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic diagram of the floating seal structure of the existing double-layer outer casing structure of an aero-engine;

[0024] Figure 2 is a schematic diagram of the floating seal structure of the sealing structure of the double-layer outer casing structure of an aero-engine provided by an embodiment of the present application;

[0025] Wherein:

[0026] 1 - outer casing; 2 - inner casing; 3 - sliding sleeve; 4 - floating ring; 5 - cover plate; 6 - double-layer outer casing structure.

[0027] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, and are only used for exemplary illustration and should not be construed as a limitation to the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0028] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and not to limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0029] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should have the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0030] In addition, the terms indicating orientation used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to specific circumstances.

[0031] A sealing structure for an aeroengine with a double-layer outer casing structure, as Figure 2 shown, includes an outer casing 1, an inner casing 2, a sliding sleeve 3, a floating ring 4, and a cover plate 5.

[0032] The outer casing 1 has an outer casing mounting hole, and its outer wall has an outer annular mounting boss surrounding the outer casing mounting hole.

[0033] The inner casing 2 is arranged inside the outer casing 1. It has an inner casing mounting hole and an inner annular mounting boss protruding towards the outer casing 1. The inner annular mounting boss surrounds the inner casing mounting hole, and there is an annular channel communicating with its interior on the inner annular mounting boss.

[0034] The double-layer outer casing structure 6 passes through the inner casing mounting hole and the outer casing mounting hole.

[0035] The lower end of the sliding sleeve 3 passes through the outer casing mounting hole and extends into the annular channel. The outer wall is in spherical contact with the inner wall of the annular channel to achieve sealing. The upper end outer wall has an annular mounting flange, and the annular mounting flange is located outside the outer casing 1.

[0036] The floating ring 4 is arranged inside the sliding sleeve 3, close to the outer casing 1. The outer edge is in spherical contact with the inner wall of the sliding sleeve 3 to achieve sealing. The inner edge is stuck in the annular floating groove opened on the double-layer outer casing structure 6 to achieve sealing, and there is a horizontal movement gap between it and the annular floating groove. For the convenience of assembly on the double-layer outer casing structure 6, the floating ring 4 can be designed as a split structure.

[0037] The cover plate 5 is sleeved on the outer periphery of the sliding sleeve 3, and there is a horizontal movement gap between it and the sliding sleeve 3. It is connected to the outer wall of the outer casing 1, specifically by bolts. An annular mounting groove is formed between it and the outer casing 1. The annular mounting flange is stuck in the annular mounting groove to achieve sealing, and there is a horizontal movement gap between it and the annular mounting groove.

[0038] The sealing structure of the double-layer outer casing structure of an aeroengine disclosed in the above embodiments can be assembled with reference to the following method:

[0039] Snap the inner edge of the floating ring 4 into the annular floating groove provided on the double-layer outer casing structure 6;

[0040] Pass the lower end of the sliding sleeve 3 through the outer casing mounting hole on the outer casing 1 and extend it into the annular channel of the inner casing 2, and sleeve it on the outside of the floating ring 4;

[0041] Connect the cover plate 5 to the outer wall of the outer casing 1 and press the annular mounting flange on the sliding sleeve 3.

[0042] In the sealing structure of the double-layer outer casing structure of an aeroengine disclosed in the above embodiments, the sliding of the floating ring 4 in the annular floating groove on the double-layer outer casing structure 6 along the x direction can be used to compensate for the axial deformation difference between the core casing and the inner casing 2; the sliding of the floating ring 4 in the sliding sleeve 3 along the y direction can be used to compensate for the radial deformation difference between the core casing and the inner casing 2; the sliding of the annular mounting flange on the sliding sleeve 3 in the annular mounting groove between the cover plate 5 and the outer casing 1 along the x direction can be used to compensate for the axial deformation difference between the outer casing 1 and the inner casing 2; the sliding of the sliding sleeve 3 in the annular channel of the inner casing 2 along the y direction can be used to compensate for the radial deformation difference between the outer casing 1 and the inner casing 2.

[0043] Design the outer wall of the lower end of the sliding sleeve 3 to be in spherical contact with the inner wall of the annular channel, and the outer edge of the floating ring 4 to be in spherical contact with the inner wall of the sliding sleeve 3. The characteristics of easy sliding and deflection of spherical contact can be used to avoid jamming of the relative sliding between the sliding sleeve 3 and the annular channel, and between the sliding sleeve 3 and the floating ring 4, and can adaptively compensate for the multi-angle non-regular deformation between the outer casing 1, the inner casing 2, and the core casing.

[0044] The sealing structure of the double-layer outer casing structure of an aeroengine disclosed in the above embodiments is only designed to achieve sealing with one sliding sleeve 3 and one floating ring 4. It can be connected to the outer casing with a relatively small number of bolts and their connectors, and the disassembly and assembly are simple. Moreover, the sliding sleeve 3 is arranged across the outer flow path between the outer casing 1 and the inner casing 2, which can effectively avoid the problem of insufficient assembly space between the outer casing 1 and the inner casing 2, will not interfere with the outer casing 1, is convenient for disassembly and assembly, and due to the design of the annular mounting flange on the sliding sleeve 3, it will not fall into the outer flow path, and has good assembly and maintenance characteristics.

[0045] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to related technical features, and the technical solutions after such changes or substitutions will fall within the protection scope of the present application.

Claims

1. A sealing structure for an aero-engine with a double-layer outer casing structure, characterized in that It includes an outer casing (1), an inner casing (2), a sliding sleeve (3), a floating ring (4), and a cover plate (5); The outer casing (1) has an outer casing mounting hole, and its outer wall has an outer annular mounting boss surrounding the outer casing mounting hole; The inner casing (2) is arranged inside the outer casing (1), and has an inner casing mounting hole thereon, and an inner annular mounting boss protruding towards the outer casing (1). The inner annular mounting boss surrounds the inner casing mounting hole, and there is an annular channel communicating with its interior on the inner annular mounting boss; The double-layer outer bypass casing structure (6) passes through the inner casing mounting hole and the outer casing mounting hole; The lower end of the sliding sleeve (3) passes through the outer casing mounting hole and extends into the annular channel. The outer wall is in sealing contact with the inner wall of the annular channel. The upper end outer wall has an annular mounting flange, and the annular mounting flange is located outside the outer casing (1); The floating ring (4) is arranged inside the sliding sleeve (3). The outer edge is in sealing contact with the inner wall of the sliding sleeve (3). The inner edge is stuck in an annular floating groove opened on the double-layer outer bypass casing structure (6), and there is a movable gap with the annular floating groove; The cover plate (5) is sleeved on the outer periphery of the sliding sleeve (3), and there is a movable gap between the cover plate (5) and the sliding sleeve (3). The cover plate (5) is connected to the outer wall of the outer casing (1), and an annular mounting groove is formed between the cover plate (5) and the outer casing (1). The annular mounting flange is stuck in the annular mounting groove, and there is a movable gap between the annular mounting flange and the annular mounting groove.

2. The sealing structure of a double-layer outer bypass casing structure of an aero-engine according to claim 1, characterized in that The outer wall of the lower end of the sliding sleeve (3) is in spherical contact with the inner wall of the annular channel.

3. The sealing structure of a double-layer outer bypass casing structure of an aero-engine according to claim 2, characterized in that The outer edge of the floating ring (4) is in spherical contact with the inner wall of the sliding sleeve (3).

4. The sealing structure of a double-layer outer bypass casing structure of an aero-engine according to claim 3, characterized in that The floating ring (4) is of a split structure.

5. The sealing structure of a double-layer outer bypass casing structure of an aero-engine according to claim 4, characterized in that The cover plate (5) is connected to the outer wall of the outer casing (1) by bolts.

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