A sealing structure between an aero-engine casing and a pipeline

Abstract

The application belongs to the technical field of sealing design between an aero-engine casing and a pipeline, and particularly relates to a sealing structure between an aero-engine casing and a pipeline, which is convenient for assembly, has a vibration damping effect, can reduce wear between structures, and performs wear compensation, can avoid leakage, and can perform axial displacement compensation, lateral displacement compensation and angular displacement compensation, can reduce the requirement for machining accuracy, ensure the sealing effect between the pipeline and the casing, reduce the installation stress generated during installation and the thermal stress generated during the operation of the aero-engine, and can have a relatively high service life.

Description

Technical Field

[0001] This application belongs to the technical field of sealing design between an aero-engine casing and pipelines, and particularly relates to a sealing structure between an aero-engine casing and pipelines. Background Technique

[0002] In an aero-engine, there are structures where multiple pipelines pass through the casing. In order to ensure the sealing between the pipelines and the casing and reduce the installation stress generated during installation and the thermal stress generated during the operation of the aero-engine, corresponding sealing structures are designed.

[0003] Currently, the sealing structures between an aero-engine casing and pipelines mainly have the following two forms:

[0004] 1) The integral ball head and sleeve seal seat structure, as Figure 1 shown, realizes the sealing between the casing and the pipeline by means of the small clearance fit between the spherical surface of the ball head and the cylindrical surface of the sleeve. It has the functions of angular displacement and axial displacement compensation, but does not have the function of lateral displacement compensation. Moreover, the integral ball head and sleeve seal seat have high requirements for machining accuracy, there is a certain leakage, there is no damping structure between them, it is easy to wear, and the leakage will increase after wear;

[0005] 2) The split floating seal ring and sleeve seal seat structure, as Figure 2 shown, realizes the sealing between the casing and the pipeline by means of the small clearance fit between the split floating seal ring and the sleeve seal seat and the seal seat. It has the functions of lateral displacement, axial displacement and angular displacement compensation. The split floating seal ring, sleeve seal seat and seal seat have high requirements for machining accuracy, there is a certain leakage, there is no damping structure between them, it is easy to wear, and the leakage will increase after wear.

[0006] In view of the existence of the above technical defects, this application is proposed.

[0007] It should be noted that the disclosure of the above background technical content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background technology should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide a sealing structure between an aero-engine casing and pipelines to overcome or mitigate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] A sealing structure between an aero-engine casing and pipelines, comprising:

[0011] The casing has mounting holes thereon;

[0012] The outer support cylinder, one end of which extends into the casing from the mounting hole, has an annular support protrusion on the inner wall of this end, and an annular mounting edge on the outer wall of the other end; the annular mounting edge is connected to the casing;

[0013] The inner support cylinder is arranged inside the outer support cylinder, there is a radial gap between it and the outer support cylinder, and the inner wall of the end facing the annular support protrusion has an annular limit protrusion;

[0014] The lower crimping cylinder is arranged inside the inner support cylinder, one end of which passes through the annular limit protrusion and extends into the annular support protrusion, there is a radial gap between this end and the annular support protrusion, and the outer wall of the other end has a lower annular crimping protrusion;

[0015] The upper crimping cylinder, one end of which extends into the inner support cylinder, has an upper annular crimping protrusion on the outer wall of this end;

[0016] The crimping ring is sleeved on the outer periphery of the upper crimping cylinder, is located inside the outer support cylinder, and there is a radial gap between it and the outer support cylinder;

[0017] The sealing ring is sleeved on the outer periphery of the upper crimping cylinder, is located inside the outer support cylinder, there is a radial gap between it and the outer support cylinder, and an annular sealing groove is formed between it and the crimping ring;

[0018] The sealing gasket is arranged in the annular sealing groove and is located on the outer periphery of the upper crimping cylinder;

[0019] The mounting ring is sleeved on the outer periphery of the upper crimping cylinder, there is a radial gap between it and the upper crimping cylinder, it is connected to the casing, and presses the sealing ring and the crimping ring;

[0020] The pipeline penetrates through the mounting ring, the upper crimping cylinder, and the lower crimping cylinder;

[0021] The ball head is sleeved on the pipeline, is located between the upper crimping cylinder and the lower crimping cylinder, and has a spherical fit with the upper crimping cylinder and the lower crimping cylinder;

[0022] Two preloading springs, one preloading spring is sleeved on the outer periphery of the lower crimping cylinder, and both ends abut between the annular limit protrusion and the lower annular crimping protrusion, and the other preloading spring is sleeved on the outer periphery of the upper crimping cylinder, and both ends abut between the upper annular crimping protrusion and the crimping ring, so that the upper crimping cylinder and the lower crimping cylinder are pressed against the ball head, and the inner support cylinder is pressed against the annular support protrusion, and an axial gap is left between the crimping ring and the inner support cylinder.

[0023] According to at least one embodiment of the present application, in the above sealing structure between the aeroengine casing and the pipeline, the annular mounting edge and the mounting ring are connected to the casing by bolts.

[0024] According to at least one embodiment of the present application, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the sealing ring is a C-shaped metal sealing ring.

[0025] According to at least one embodiment of the present application, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the mounting ring has an annular positioning protrusion, and the annular positioning protrusion is snapped into one end of the outer support cylinder having an annular mounting edge.

[0026] According to at least one embodiment of the present application, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the pipeline and the ball head are connected by welding.

[0027] The present application has at least the following beneficial technical effects:

[0028] A sealing structure between the aero-engine casing and the pipeline is provided, which is convenient for assembly, has a vibration damping effect, can reduce wear between structures, and performs wear compensation, can avoid leakage, and can perform axial displacement compensation, lateral displacement compensation and angular displacement compensation, can reduce the requirement for machining accuracy, ensure the sealing effect between the pipeline and the casing, reduce the installation stress generated during installation and the thermal stress generated during the operation of the aero-engine, and can have a relatively high service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 is a schematic diagram of the overall ball head and sleeve seal seat sealing structure between the existing aero-engine casing and the pipeline;

[0030] Figure 2 is a schematic diagram of the split-type floating seal ring and sleeve seal seat sealing structure between the existing aero-engine casing and the pipeline;

[0031] Figure 3 is a schematic diagram of the sealing structure between the aero-engine casing and the pipeline provided by the embodiment of the present application;

[0032] Figure 4 is a schematic diagram of the assembly process of the sealing structure between the aero-engine casing and the pipeline provided by the embodiment of the present application;

[0033] Figure 5 is a schematic diagram of the lateral displacement compensation of the sealing structure between the aero-engine casing and the pipeline provided by the embodiment of the present application;

[0034] Figure 6 is a schematic diagram of the axial displacement compensation of the sealing structure between the aero-engine casing and the pipeline provided by the embodiment of the present application;

[0035] Figure 7 is a schematic diagram of the angular displacement compensation of the sealing structure between the aero-engine casing and the pipeline provided by the embodiment of the present application;

[0036] Wherein:

[0037] 1 - Pipeline; 2 - Sealing ring; 3 - Installation ring; 4 - Bolt; 5 - Preloading spring; 6 - Ball head; 7 - Inner support cylinder; 8 - Lower crimping cylinder; 9 - Upper crimping cylinder; 10 - Sealing ring; 11 - Crimping ring; 12 - Outer support cylinder; 13 - Casing.

[0038] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and should not be construed as a limitation to this application. Detailed implementation manners

[0039] To make the technical solutions and their advantages of this application clearer, the technical solutions of this 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 part of the embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the field to which this application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or position relationships, rather than implying that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly. Therefore, it should not be construed as a limitation to this application. The terms "first", "second", "third" and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and cannot be construed as indicating or implying relative importance. The words "a", "one" or "the" and similar words used in the description of this application should not be construed as an absolute limitation on the quantity, but should be understood as having at least one. The terms "including" or "comprising" and similar words used in the description of this application are intended to cover the elements or items listed after the word and their equivalents that appear before the word, without excluding other elements or items.

[0041] In addition, it should be noted that, unless otherwise clearly specified and limited, the similar terms such as "installed", "connected", and "linked" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0042] The following further elaborates on this application in conjunction with the Figures 1 to 7 accompanying drawings.

[0043] A sealing structure between an aero-engine casing and a pipeline, as Figure 3 shown, includes:

[0044] The casing 13, which has mounting holes thereon;

[0045] The outer support cylinder 12, one end of which extends into the casing 13 from the mounting hole. The inner wall of this end has a circular support protrusion, and the outer wall of the other end has a circular mounting edge; the circular mounting edge is connected to the casing 13;

[0046] The inner support cylinder 7, which is arranged inside the outer support cylinder 12 and has a radial gap with the outer support cylinder 12. The inner wall of the end facing the circular support protrusion has a circular limit protrusion;

[0047] The lower crimping cylinder 8, which is arranged inside the inner support cylinder 7. One end passes through the circular limit protrusion and extends into the circular support protrusion, and there is a radial gap between this end and the circular support protrusion. The outer wall of the other end has a lower circular crimping protrusion;

[0048] The upper crimping cylinder 9, one end of which extends into the inner support cylinder 7. The outer wall of this end has an upper circular crimping protrusion;

[0049] The crimping ring 11, which is sleeved on the outer periphery of the upper crimping cylinder 9, is located inside the outer support cylinder 12, and has a radial gap with the outer support cylinder 12;

[0050] The sealing ring 10, which is sleeved on the outer periphery of the upper crimping cylinder 9, is located inside the outer support cylinder 12, has a radial gap with the outer support cylinder 12, and forms an annular sealing groove with the crimping ring 11;

[0051] The sealing ring 2, which is arranged in the annular sealing groove and is located on the outer periphery of the upper crimping cylinder 9;

[0052] The mounting ring 3, which is sleeved on the outer periphery of the upper crimping cylinder 9, has a radial gap with the upper crimping cylinder 9, is connected to the casing 13, and presses the sealing ring 10 and the crimping ring 11;

[0053] The pipeline 1 is installed through the installation ring 3, the upper crimping cylinder 9, and the lower crimping cylinder 8;

[0054] The ball head 6 is sleeved on the pipeline 1, located between the upper crimping cylinder 9 and the lower crimping cylinder 8, and is in spherical fit with the upper crimping cylinder 9 and the lower crimping cylinder 8;

[0055] Two preloading springs 5. One preloading spring 5 is sleeved on the outer periphery of the lower crimping cylinder 8, and its two ends abut between the annular limiting protrusion and the lower annular crimping protrusion. The other preloading spring 5 is sleeved on the outer periphery of the upper crimping cylinder 9, and its two ends abut between the upper annular crimping protrusion and the crimping ring 11, so that the upper crimping cylinder 9 and the lower crimping cylinder 8 are pressed tightly on the ball head 6, and the inner support cylinder 7 is pressed tightly on the annular support protrusion, and an axial gap is left between the crimping ring 11 and the inner support cylinder 7.

[0056] The sealing structure between the aero-engine casing and the pipeline disclosed in the above embodiment is convenient to assemble. For the specific assembly process, reference can be made to Figure 4 which is supported by the outer support cylinder 12 and pressed by the installation ring 3, so that the outer support cylinder 12, the installation ring 3, the inner support cylinder 7, the crimping ring 11, and the sealing ring 10 are in sealing contact axially. In this way, leakage can be avoided. And it is preloaded by the preloading spring 5 between the upper and lower annular crimping protrusions of the lower crimping cylinder 8 and the annular limiting protrusion on the inner support cylinder 7, and between the upper annular crimping protrusion on the upper crimping cylinder 9 and the crimping ring 11. The preloading spring 5 can have a damping effect, and an axial gap is left between the crimping ring 11 and the inner support cylinder 7, which can reduce the wear between structures, and can perform wear compensation to ensure the sealing performance of the structure, and can perform axial displacement compensation, as Figure 5 shown.

[0057] In the sealing structure between the aero-engine casing and the pipeline disclosed in the above embodiment, there are radial gaps in multiple places in the radial direction, including between the inner support cylinder 7 and the outer support cylinder 12, between the crimping ring 11 and the outer support cylinder 12, between the sealing ring 10 and the outer support cylinder 12, between the installation ring 3 and the upper crimping cylinder 9, etc., which can perform lateral displacement compensation, as Figure 6 shown.

[0058] In the sealing structure between the aero-engine casing and the pipeline disclosed in the above embodiment, the ball head 6 sleeved on the pipeline 1 is in spherical fit contact with the upper crimping cylinder 9 and the lower crimping cylinder 8, and is clamped by the preloading force of the two preloading springs 5, which can effectively perform angular displacement compensation.

[0059] In some alternative embodiments, in the above sealing structure between the aero-engine casing and the pipeline, the annular mounting edge and the installation ring 3 are connected to the casing 13 by bolts 4.

[0060] In some alternative embodiments, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the sealing ring 2 is a C-shaped metal sealing ring, which has the properties of high temperature resistance, wear resistance, and easy sliding.

[0061] In some alternative embodiments, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the mounting ring 3 has a circular positioning protrusion, and the circular positioning protrusion is snapped into one end of the outer support cylinder 12 having a circular mounting edge for centering and positioning.

[0062] In some alternative embodiments, in the above-mentioned sealing structure between the aero-engine casing and the pipeline, the pipeline 1 and the ball head 6 are connected by welding.

[0063] The various embodiments in the specification are described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0064] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the 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 the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A sealing structure between an aero-engine casing and a pipeline, characterized in that, Comprising: A casing (13) with mounting holes thereon; An outer support cylinder (12), one end of which extends into the casing (13) from the mounting hole. The inner wall of this end has an annular support protrusion, and the outer wall of the other end has an annular mounting edge; the annular mounting edge is connected to the casing (13); An inner support cylinder (7) disposed within the outer support cylinder (12), having a radial gap with the outer support cylinder (12). The inner wall of the end facing the annular support protrusion has an annular limit protrusion; A lower crimping cylinder (8) disposed within the inner support cylinder (7), one end of which passes through the annular limit protrusion and extends into the annular support protrusion, having a radial gap with the annular support protrusion. The outer wall of the other end has a lower annular crimping protrusion; An upper crimping cylinder (9), one end of which extends into the inner support cylinder (7). The outer wall of this end has an upper annular crimping protrusion; A crimping ring (11) sleeved on the outer periphery of the upper crimping cylinder (9), located within the outer support cylinder (12), having a radial gap with the outer support cylinder (12); A sealing ring (10) sleeved on the outer periphery of the upper crimping cylinder (9), located within the outer support cylinder (12), having a radial gap with the outer support cylinder (12), and forming an annular sealing groove with the crimping ring (11); A sealing ring (2) disposed in the annular sealing groove, located on the outer periphery of the upper crimping cylinder (9); A mounting ring (3) sleeved on the outer periphery of the upper crimping cylinder (9), having a radial gap with the upper crimping cylinder (9), connected to the casing (13), pressing the sealing ring (10) and the crimping ring (11); A pipeline (1) passing through the mounting ring (3), the upper crimping cylinder (9), and the lower crimping cylinder (8); A ball head (6) sleeved on the pipeline (1), located between the upper crimping cylinder (9) and the lower crimping cylinder (8), and having a spherical fit with the upper crimping cylinder (9) and the lower crimping cylinder (8); Two pre-tightening springs (5), one pre-tightening spring (5) is sleeved on the outer periphery of the lower crimping cylinder (8), and both ends abut between the annular limit protrusion and the lower annular crimping protrusion. The other pre-tightening spring (5) is sleeved on the outer periphery of the upper crimping cylinder (9), and both ends abut between the upper annular crimping protrusion and the crimping ring (11), pressing the upper crimping cylinder (9) and the lower crimping cylinder (8) against the ball head (6), and pressing the inner support cylinder (7) against the annular support protrusion, and leaving an axial gap between the crimping ring (11) and the inner support cylinder (7).

2. The sealing structure between an aero-engine casing and a pipeline according to claim 1, characterized in that, The annular mounting edge and the mounting ring (3) are connected to the casing (13) by bolts (4).

3. The sealing structure between an aero-engine casing and a pipeline according to claim 1, characterized in that, The sealing ring (2) is a C-shaped metal sealing ring.

4. The sealing structure between an aero-engine casing and a pipeline according to claim 1, characterized in that, The mounting ring (3) has an annular positioning protrusion, and the annular positioning protrusion is snapped into one end of the outer support cylinder (12) with an annular mounting edge.

5. The sealing structure between an aero-engine casing and a pipeline according to claim 1, characterized in that, The pipeline (1) and the ball head (6) are connected by welding.

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