A connecting structure between an aero-engine casing and a nozzle

Abstract

The present application relates to a connection structure between an aero-engine casing and a nozzle, comprising: a casing connection ring, the outer wall of the front end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the rear end of the casing through bolt fasteners. The outer wall of the rear end has an annular step, and there is an annular protrusion outside the annular step, and the cross-section of the annular protrusion is semi-circular; a nozzle connection ring, the outer wall of the rear end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the front end of the nozzle through bolt fasteners. The outer wall of the front end has an outward annular flange, and the outward annular flange covers the annular step and is in small-gap fit with the annular protrusion; there is a gap between the front end of the nozzle connection ring and the rear end of the casing connection ring; a W-shaped sealing ring, axially sealed between the annular step and the annular flange; a quick-release ring, which is a two-half docking structure, and both ends have inward annular flanges; the annular step and the outward annular flange are located between the two inward annular flanges.

Description

Technical Field

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

[0002] Currently, at the rear end of the aero-engine casing and the front end of the nozzle, they are connected, transmit force, and are sealed through a ring-shaped connection edge using bolt fasteners. This technical solution has the following defects:

[0003] 1) A large number of bolt fasteners are required, which is not convenient for quickly connecting the casing and the nozzle;

[0004] 2) In some scenarios, the casing needs to be assembled with the nozzle in sections onto the aircraft, and it is inconvenient to perform the connection operation using bolt fasteners;

[0005] 3) The connection between the casing and the nozzle is a rigid connection, without the ability of deformation compensation. Under the action of high temperature, large stress concentration is likely to occur, and then it is damaged.

[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 connection structure between an aero-engine casing and a nozzle to overcome or mitigate at least one aspect of the known technical defects.

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

[0010] A connection structure between an aero-engine casing and a nozzle, comprising:

[0011] A casing connection ring, the outer wall of the front end has a ring-shaped connection edge, and this ring-shaped connection edge is connected to the ring-shaped connection edge at the rear end of the casing through bolt fasteners; the outer wall of the rear end of the casing connection ring has a ring-shaped step, and there is a ring-shaped protrusion outside the ring-shaped step, and the cross-section of the ring-shaped protrusion is semi-circular;

[0012] A nozzle connection ring, the outer wall of the rear end has a ring-shaped connection edge, and this ring-shaped connection edge is connected to the ring-shaped connection edge at the front end of the nozzle through bolt fasteners; the outer wall of the front end of the nozzle connection ring has an outward ring-shaped folded edge, the outward ring-shaped folded edge covers the ring-shaped step, and has a small clearance fit with the ring-shaped protrusion; there is a gap between the front end of the nozzle connection ring and the rear end of the casing connection ring;

[0013] The W-shaped seal ring is sleeved on the outer periphery of the casing connecting ring and axially seals between the annular step and the annular flange;

[0014] The quick-release ring is a two-half docking structure with inward annular flanges at both ends; the annular step and the outward annular flange are located between the two inward annular flanges.

[0015] According to at least one embodiment of the present application, in the connection structure between the aero-engine casing and the nozzle described above, the quick-release ring is in a small-clearance fit with the annular step and the outward annular flange.

[0016] According to at least one embodiment of the present application, in the connection structure between the aero-engine casing and the nozzle described above, the ends of the two inward annular flanges are bent inward and are in a small-clearance fit with the annular step and the outward annular flange respectively.

[0017] According to at least one embodiment of the present application, in the connection structure between the aero-engine casing and the nozzle described above, the two half quick-release rings are connected by bolts and fasteners through the mounting edge. Brief Description of the Drawings

[0018] Figure 1 It is a schematic diagram of the connection structure between the aero-engine casing and the nozzle provided by the embodiment of the present application;

[0019] Wherein:

[0020] 1 - casing connecting ring; 2 - casing; 3 - nozzle connecting ring; 4 - nozzle; 5 - W-shaped seal ring; 6 - quick-release ring.

[0021] For better illustrating 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 the present application. Detailed Description of the Embodiment

[0022] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in detail below with reference to the drawings. It can be understood that the specific embodiments described herein are only part of the 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. Without conflict, the embodiments and the technical features in the embodiments of the present application can be combined with each other to obtain new embodiments.

[0023] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. 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 positional 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 object being described changes, its relative positional 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 should not be construed as indicating or implying relative importance. The similar words such as "a", "an", or "the" 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 similar words such as "including" or "comprising" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0024] In addition, it should be noted that, unless otherwise clearly specified and limited, the similar words such as "installed", "connected", and "joined" 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 directly connected or indirectly connected 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.

[0025] The following further elaborates on this application in conjunction with the Figure 1 accompanying drawings.

[0026] A connection structure between an aero-engine casing and a nozzle, comprising:

[0027] A casing connection ring 1, the outer wall of the front end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the rear end of the casing 2 through bolt fasteners; the outer wall of the rear end of the casing connection ring 1 has an annular step, and there is an annular protrusion on the outside of the annular step, and the cross-section of the annular protrusion is semi-circular;

[0028] A nozzle connection ring 3, the outer wall of the rear end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the front end of the nozzle 4 through bolt fasteners; the outer wall of the front end of the nozzle connection ring 3 has an outward annular flange, the outward annular flange covers the annular step and has a small clearance fit with the annular protrusion; there is a gap between the front end of the nozzle connection ring 3 and the rear end of the casing connection ring 1;

[0029] The W-shaped sealing ring 5 is sleeved on the outer periphery of the casing connecting ring 1 and is axially sealed between the annular step and the annular flange;

[0030] The quick-release ring 6 has a two-half butt-jointed structure and has inward annular flanges at both ends; the annular step and the outward annular flange are located between the two inward annular flanges.

[0031] For the connection structure between the aero-engine casing and the nozzle disclosed in the above embodiment, in specific applications, the casing connecting ring 1 and the casing 2 can be assembled first, the nozzle connecting ring 3 and the nozzle 4 can be assembled, and then the W-shaped sealing ring 5 can be assembled in cooperation. Subsequently, the quick-release ring 6 is used for limiting to realize the connection between the casing 2 and the nozzle 4, which is convenient and fast. When assembling in sections on the aircraft, only the casing connecting ring 1, the nozzle connecting ring 3, the W-shaped sealing ring 5, and the quick-release ring 6 are required, and the operation is convenient.

[0032] For the connection structure between the aero-engine casing and the nozzle disclosed in the above embodiment, those skilled in the art can understand that the small clearance fit between the annular protrusion on the outer wall of the rear end of the casing connecting ring 1 and the outward annular flange on the outer wall of the front end of the nozzle connecting ring 3 can play a role in radial adjustment structure compensation during assembly, and can release the stress generated by the inconsistent deformation in a high-temperature environment. In addition, there is a gap between the front end of the nozzle connecting ring 3 and the rear end of the casing connecting ring 1, and the W-shaped sealing ring 5 with deformation ability is used for sealing between the annular step and the outward annular flange, and the quick-release ring 6 is used for restraint, which can compensate for the high-temperature deformation, release the stress generated by the inconsistent deformation, and protect the components from damage on the basis of ensuring the sealing performance and force transmission ability.

[0033] In some alternative embodiments, in the above connection structure between the aero-engine casing and the nozzle, the small clearance fit between the quick-release ring 6 and the annular step and the outward annular flange can provide a deformation margin for the inconsistent deformation in a high-temperature environment, avoid generating large stress, and protect the components from damage.

[0034] In some alternative embodiments, in the above connection structure between the aero-engine casing and the nozzle, the ends of the two inward annular flanges are bent inward and are in small clearance fit with the annular step and the outward annular flange respectively.

[0035] In some alternative embodiments, in the above connection structure between the aero-engine casing and the nozzle, the two half quick-release rings 6 are connected by bolts and fasteners through the mounting edges, which is convenient for realizing rapid and reliable assembly.

[0036] So far, the technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principle of this 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 all fall within the protection scope of this application.

Claims

1. A connecting structure between an aeroengine casing and a nozzle, characterized in that, Comprising: A casing connection ring (1), the outer wall of the front end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the rear end of the casing (2) through bolt fasteners; the outer wall of the rear end of the casing connection ring (1) has an annular step, and there is an annular protrusion on the outside of the annular step, and the cross-section of the annular protrusion is semi-circular; A nozzle connection ring (3), the outer wall of the rear end has an annular connection edge, and this annular connection edge is connected to the annular connection edge at the front end of the nozzle (4) through bolt fasteners; the outer wall of the front end of the nozzle connection ring (3) has an outward annular flange, and the outward annular flange covers the annular step and has a small clearance fit with the annular protrusion; there is a gap between the front end of the nozzle connection ring (3) and the rear end of the casing connection ring (1); A W-shaped sealing ring (5), sleeved on the outer periphery of the casing connection ring (1), and sealed axially between the annular step and the annular flange; A quick-release ring (6), which is a two-half docking structure, and has inward annular flanges at both ends; The annular step and the outward annular flange are located between the two inward annular flanges.

2. The connection structure between the casing and the nozzle of an aeroengine according to claim 1, characterized in that The quick-release ring (6) has a small clearance fit with the annular step and the outward annular flange.

3. The connection structure between the casing and the nozzle of an aeroengine according to claim 1, characterized in that The ends of the two inward annular flanges are bent inward and respectively have a small clearance fit with the annular step and the outward annular flange.

4. The connection structure between the casing and the nozzle of an aeroengine according to claim 1, characterized in that The two half quick-release rings (6) are connected through mounting edges with bolt fasteners.

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