An aeroengine nozzle seal clamp and method of use thereof

Abstract

The application provides an aero-engine nozzle sealing clamp and a use method thereof. The clamp comprises a body, a supporting block and a supporting base. The body is a cylindrical structure with an open end. A sealing element is arranged in the body at the other end. An extension is formed by extending the open end of the body radially outward. A sealing assembly is arranged on the extension to seal a second nozzle. The supporting block is an L-shaped structure. One end of the supporting block is connected with the extension of the body, and the other end is provided with the sealing assembly to seal a first nozzle. The supporting base is installed on a part through a connecting piece. The supporting base is provided with a sealing unit to seal a first nozzle hole and a second nozzle hole respectively. The sealing clamp is divided into the body and the supporting base. The nozzles are sealed by the sealing assembly and the sealing unit. The weight and the operation complexity of the sealing clamp are reduced. The supporting block is connected with the body and can move within a certain range in the circumference to meet the use requirements of different parts.

Description

Technical Field

[0001] This invention belongs to the field of sealing fixture technology, and relates to an aero-engine nozzle sealing fixture and its usage method. Background Technology

[0002] During operation, aero-engines require nozzles to spray lubricating oil to cool and lubricate the bearings and other components of the nozzle mounting base. Some aero-engine models have numerous nozzle spray points that are spatially distributed. During assembly, the nozzles need to be inspected for sealing, which requires the use of clamps to seal them. Current technology uses integral sealing clamps, which are complex in structure and inconvenient to operate. Using multi-structure sealing methods is time-consuming and labor-intensive to install. Summary of the Invention

[0003] The purpose of this invention is to solve the problem that the sealing fixtures used in the prior art have relatively complex structures and are inconvenient to operate when assembling aero-engine nozzles, and to provide an aero-engine nozzle sealing fixture and its usage method.

[0004] To achieve the above objectives, the present invention employs the following technical solution: An aero-engine nozzle sealing fixture includes a body, a support block, and a base. The body is a cylindrical structure with one open end and a sealing element inside the other end. It is mounted on an aero-engine nozzle mounting base via a connector. The open end of the body extends radially outward to form an extension portion, on which a sealing component is provided to seal a second nozzle. The support block is an L-shaped structure, with one end engaging with the extension portion of the body and the other end mounted with a sealing component to seal a first nozzle. The base is mounted on the aero-engine nozzle mounting base via a connector and has a sealing unit that seals both the first and second nozzle orifices.

[0005] A further improvement of the present invention is that: A rubber ring is provided on the inner side of one opening end of the main body.

[0006] The connector between the body and the aircraft engine nozzle mounting base includes two second screws.

[0007] A sealing assembly is provided on the extension, the sealing assembly including a first screw and a second sealing gasket, the second sealing gasket being bonded to the end face of the first screw.

[0008] The sealing assembly on the support block includes a sixth screw and a sealing gasket, the sealing gasket being bonded to the end face of the sixth screw.

[0009] The sealing unit on the support includes a fourth screw, a fifth screw, and a pressure block. The fourth screw and the pressure block are rotatably connected to seal the first nozzle hole; the fifth screw and the pressure block are rotatably connected to seal the second nozzle hole.

[0010] The fourth and fifth screws are connected to the pressure block using an articulated structure.

[0011] The support block is connected to the extension of the body by a first screw.

[0012] A method of using an aircraft engine nozzle sealing clamp, employing the aircraft engine nozzle sealing clamp as described in any of the preceding items, specifically includes the following steps: First, a rubber ring is installed at one end of the opening of the main body, and a first sealing gasket is installed at the other end. The main body is installed on the aircraft engine nozzle mounting base through a connector. A sealing assembly is installed on the extension of the main body to seal the second nozzle. Then, a support block is installed on the extension of the main body, and a sealing assembly is installed at the other end of the support block to seal the first nozzle. Finally, the support is installed on the aircraft engine nozzle mounting base through a connector, and a sealing unit is installed on the support. The sealing unit seals the first nozzle hole and the second nozzle hole respectively.

[0013] The body and the support are respectively mounted on the aircraft engine nozzle mounting base by screws.

[0014] Compared with the prior art, the present invention has the following beneficial effects: This invention proposes an aero-engine nozzle sealing fixture. By dividing the sealing fixture into two parts, the body and the support, the nozzle is sealed by various sealing components and sealing units, which reduces the weight and operation complexity of the sealing fixture. At the same time, the support block is connected to the body and can move within a certain range in the circumferential direction, which can meet the usage requirements of different aero-engine nozzle mounting bases. The overall structure of the sealing fixture is simple and easy to operate. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the aero-engine nozzle sealing fixture structure of the present invention; Figure 2 This is a partial structural diagram of the aero-engine nozzle sealing fixture of the present invention.

[0017] Wherein: 1. Body; 2. Support block; 3. Support base; 4. Pressure block; 5. First sealing gasket; 6. Second sealing gasket; 7. First screw; 8. Second screw; 10. Third screw; 11. Fourth screw; 12. Fifth screw; 13. Sixth screw; 14. Front nozzle; C. First nozzle; P. Second nozzle; Y. Third nozzle; N. First nozzle hole; S. Second nozzle hole. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0019] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0020] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0021] In the description of the embodiments of the present invention, it should be noted that if terms such as "upper," "lower," "horizontal," or "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of the invention is in use, they are only for the convenience of describing the present invention 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, and therefore should not be construed as a limitation of the present invention. Furthermore, terms such as "first" and "second" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0022] Furthermore, the use of the term "horizontal" does not imply that the component must be absolutely horizontal, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0023] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0024] The present invention will now be described in further detail with reference to the accompanying drawings: See Figure 1 This is a schematic diagram of the sealing fixture structure for an aero-engine nozzle in this invention. The sealing fixture includes a body 1, a support block 2, and a support 3. The body 1 is a cylindrical structure with one open end, and a rubber ring 10 is provided inside the opening. A sealing element is provided inside the other end, and it is installed on the aero-engine nozzle mounting base through a connector. The open end of the body 1 extends radially outward to form an extension. A first sealing assembly is provided on the extension to seal the second nozzle P. The first sealing assembly includes a first screw 7 and a second sealing gasket 6. The second sealing gasket 6 is bonded to the end face of the first screw 7. The support block 2 has an L-shaped structure. One end of the support block 2 is connected to the extension of the body 1, and the other end... A second sealing assembly is installed at the end to seal the first nozzle C. The second sealing assembly includes a sixth screw 13 and a sealing gasket, the sealing gasket being adhered to the end face of the sixth screw 13. A sealing unit is provided on the support 3 to seal the first nozzle hole N and the second nozzle hole S respectively. The sealing unit on the support 3 includes a fourth screw 11, a fifth screw 12, and a pressure block 4. The fourth screw 11 and the pressure block 4 are rotatably connected to seal the first nozzle hole N. The fifth screw 12 and the pressure block 4 are rotatably connected to seal the second nozzle hole S. The fourth screw 11 and the fifth screw 12 are connected to the pressure block 4 using an articulated structure.

[0025] See Figure 2 The diagram shows a partial structure of the aero-engine nozzle sealing fixture in this invention. The support block 2 is connected to the extension of the body 1 by the first screw 7.

[0026] An embodiment of the present invention provides a method for using an aero-engine nozzle sealing fixture, which employs the aero-engine nozzle sealing fixture as described above, specifically including: The main body 1 has a cap-like structure. It is connected to the aircraft engine nozzle mounting base via a second screw 8. A first sealing gasket 5 is installed between the end faces of the main body 1 and the aircraft engine nozzle mounting base for sealing. A first screw 7 is installed on the main body 1, and a second sealing gasket 6 is adhered to the end face of the first screw 7 to seal the end face, preventing damage to the aircraft engine nozzle mounting base and saving the installation process of the sealing gasket. A support block 2 is fixed to the mounting edge of the main body 1. The support block 2 and the main body 1 are movable within a certain circumferential range. A sixth screw 13 is installed on the side of the support block 2, and a sealing gasket is adhered to the end face of the sixth screw 13 for sealing the side. The support 3 is fixed to the aircraft engine nozzle mounting base by screws. A fourth screw 11 and a fifth screw 12 are installed on the side of the support 3. Pressure blocks 4 are respectively installed on the screw heads. The fourth screw 11 and the fifth screw 12 are connected to the pressure blocks 4 using a joint structure.

[0027] First, install a rubber ring 10 at one end of the opening of the main body 1 and a first sealing gasket 5 at the other end. The main body 1 is installed on the aircraft engine nozzle mounting base through a connector. A sealing assembly is installed on the extension of the main body 1 to seal the second nozzle P. Then, the support block 2 is installed on the extension of the main body 1, and a sealing assembly is installed on the other end of the support block 2 to seal the first nozzle C. Finally, the support 3 is installed on the aircraft engine nozzle mounting base through a connector, and a sealing unit is installed on the support 3 to seal the first nozzle hole N and the second nozzle hole S respectively.

[0028] The sealing clamp of this invention employs a two-part structural design, reducing its weight and facilitating installation. The support block is connected to the main body and can move within a certain circumferential range, meeting the requirements of various aero-engine nozzle mounting substrates. The screw and pressure block are connected using a joint-type structure for easy installation; a sealing gasket is adhered to the screw end face to prevent damage to the aero-engine nozzle mounting substrate and to save on the gasket installation process. The structure is compact, easy to use, simple to maintain, and has low manufacturing costs.

[0029] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft engine nozzle sealing clamp, characterized in that, The system includes a body (1), a support block (2), and a support (3). The body (1) is a cylindrical structure with one open end. A rubber ring (10) is provided on the inner side of the open end of the body (1), and a first sealing gasket (5) is provided on the other end for forming a seal with the outer wall of the aircraft engine nozzle mounting base. The body (1) is mounted on the aircraft engine nozzle mounting base through a connector. The open end of the body (1) extends radially outward to form an extension. A first sealing component is provided on the extension for sealing the second nozzle (P) located on the side of the body (1). The support block (2) has an L-shaped structure. One end of the support block (2) is connected to the extension of the body (1), and the other end is equipped with a second sealing component to seal the first nozzle (C) located in front of the body (1). The support (3) is installed on the aircraft engine nozzle mounting base through a connector. The support (3) is provided with a sealing unit, which seals the first nozzle hole (N) and the second nozzle hole (S) on the aircraft engine nozzle mounting base respectively.

2. The aircraft engine nozzle sealing clamp as described in claim 1, characterized in that, The connector between the body (1) and the aircraft engine nozzle mounting base includes two second screws (8).

3. The aircraft engine nozzle sealing clamp as described in claim 1, characterized in that, The first sealing assembly includes a first screw (7) and a second sealing gasket (6). The second sealing gasket (6) is bonded to the end face of the first screw (7) and is used to form a contact seal with the sealed orifice when the first screw (7) is tightened.

4. The aircraft engine nozzle sealing clamp as described in claim 1, characterized in that, The second sealing assembly includes a sixth screw (13) and a sealing gasket, the sealing gasket being bonded to the end face of the sixth screw (13) for forming a contact seal with the sealed orifice when the sixth screw (13) is tightened.

5. The aircraft engine nozzle sealing fixture as described in claim 1, characterized in that, The sealing unit on the support (3) includes a fourth screw (11), a fifth screw (12) and a pressure block (4). The fourth screw (11) and the pressure block (4) are connected by a joint structure. By rotating the pressure block (4), it is pressed against the end face of the first nozzle hole (N) to achieve a seal. The fifth screw (12) and the pressure block (4) are connected by a joint structure. By rotating the pressure block (4), it is pressed against the end face of the second nozzle hole (S) to achieve a seal.

6. A method of using an aircraft engine nozzle sealing clamp, characterized in that, The use of the aircraft engine nozzle sealing fixture as described in any one of claims 1-5 specifically includes the following steps: First, install a rubber ring (10) at one end of the opening of the main body (1) and a first sealing gasket (5) at the other end. The main body (1) is installed on the aircraft engine nozzle mounting base through a connector. A sealing assembly is installed on the extension of the main body (1) to seal the second nozzle (P). Then, install the support block (2) on the extension of the main body (1). A sealing assembly is installed on the other end of the support block (2) to seal the first nozzle (C). Finally, install the support (3) on the aircraft engine nozzle mounting base through a connector. Install the sealing unit on the support (3) to seal the first nozzle hole (N) and the second nozzle hole (S) respectively through the sealing unit.

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