Adjustable lead seal device for aeroengine

Abstract

The present invention belongs to the field of aero-engines and relates to the technology of test lead seal design. It discloses an adjustable lead seal device for an aero-engine. The device includes a lead seat and a compression nut. One end of the lead seat is fixed on the engine casing, and the other end is connected to the compression nut. The test lead is led out from the inside of the engine to the outside of the engine through the engine casing, the lead seat, and the compression nut in sequence. A perforated plate structure is provided in the cavity of the lead seat. The perforated plate structure includes at least 3 perforated plates stacked along the lead direction. Each perforated plate is provided with an eccentric lead hole, and the eccentric lead holes of all the perforated plates enclose a lead channel through which the test lead passes. The adjustable lead seal device of the present invention has the advantages of adjustable lead channel size, good sealing performance, ready-to-use without waiting, and self-locking function, etc.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engines, relates to the design technology of test lead sealing, and particularly relates to an adjustable lead sealing device for an aero-engine. Background Art

[0002] An aero-engine is a device that provides power for an aircraft. Its working characteristics of high temperature, high pressure, and high rotational speed require a quite high technical level for development. Among them, the test technology is one of the most important technologies in the development of aero-engines. By testing, parameters such as gas pressure and temperature at different positions inside the aero-engine can be obtained. When designing the test leads, the lead structure should be minimized to affect the engine performance, thereby ensuring the accuracy of the test results.

[0003] To achieve the purpose of sealing the test leads, the traditional method is to adopt a structure of sol and orifice plate. While the test line is led out, sealant is used for filling to achieve the purpose of sealing. However, the solution of using the combination of sol and orifice plate has the following disadvantages:

[0004] 1) This solution is a fixed design, and the size of the hole for threading the leads cannot change with the change in the number of leads, which will affect the subsequent sealant application process and thus affect the sealing performance;

[0005] 2) The leads cannot be bundled during the lead process, and the assembly process is relatively cumbersome. Summary of the Invention

[0006] To solve the technical problems of the non-adjustable size of the lead hole caused by the test lead sealing structure of sol plus orifice plate, and thus the poor sealing performance caused by the influence on the sealant application process, and the cumbersome assembly process caused by the inability to bundle the test leads, the present invention discloses an adjustable lead sealing device for an aero-engine. The adjustable lead sealing device includes a lead seat and a compression cap. One end of the lead seat is fixed on the engine casing, and the other end is connected to the compression cap. The test leads are led out from the inside of the engine to the outside of the engine in sequence through the engine casing, the lead seat, and the compression cap.

[0007] Wherein, a orifice plate structure is arranged in the cavity of the lead seat. The orifice plate structure includes at least 3 orifice plates stacked along the lead direction. Each orifice plate is provided with an eccentric lead hole, and the eccentric lead holes of all the orifice plates enclose a lead channel through which the test leads pass.

[0008] Further, an opening communicating with the eccentric lead hole is formed at the edge of the orifice plate.

[0009] Further, a boss is machined on one surface of the orifice plate, and a plurality of grooves cooperating with the boss on the adjacent orifice plate are circumferentially machined on the other surface.

[0010] Furthermore, there are 1 to 3 bosses on the orifice plate, and 4 to 8 grooves.

[0011] Further, the eccentric lead hole includes a concentric first round hole and a second round hole, the diameter of the first round hole is smaller than that of the second round hole, and the second round holes of all the eccentric lead holes form a labyrinth seal structure.

[0012] Furthermore, an elastic structure is provided above the orifice plate structure, and a hole through which the test lead passes is provided on the elastic structure.

[0013] Preferably, the elastic structure is a pre-compressed spring.

[0014] Furthermore, a cover is provided at the outlet end of the lead seat, an outer conical surface facing the direction of the engine casing is provided at the edge of the outlet end of the lead seat, an inner conical surface matching the outer conical surface is provided on the outer periphery of the cover, and a wire passing hole is provided on the cover.

[0015] Preferably, a necking section is machined on the outer peripheral wall of the lead seat and below the outer conical surface.

[0016] Further, a seal is provided between the lead seat and the engine casing.

[0017] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of the present specification at least include:

[0018] 1. By designing the orifice plate structure, the present invention can adjust the size of the lead channel in a timely manner according to the number of test leads, thereby reducing gas leakage and enhancing the sealing performance.

[0019] 2. By combining multiple sealing methods such as sealant sealing, labyrinth seal structure sealing, elastic structure pressing sealing, conical surface pressing sealing and sealant sealing, the present invention minimizes gas leakage and improves the sealing performance.

[0020] 3. The adjustable lead seal device of the present invention does not need to use sealant, greatly saves the waiting time for sealant solidification, and can quickly respond to emergency assembly tasks.

[0021] 4. The inner peripheral wall of the compression cap is provided with an internal thread that matches the external thread on the outer peripheral wall of the lead seat. Through the elastic deformation restoring force of the necking section of the lead seat, the threaded connection pair has a self-locking function, eliminating the process of locking wire, and the installation process is simple and convenient. Description of the Drawings

[0022] To more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

[0023] Figure 1 Schematic diagram of an adjustable lead seal device for an aeroengine disclosed in an embodiment of the present invention;

[0024] Figure 2 Schematic diagram of an orifice plate disclosed in an embodiment of the present invention;

[0025] Figure 3 For Figure 2 Cross-sectional view of the orifice plate shown in [Figure number] in the A-A direction;

[0026] Figure 4 Schematic diagram of a lead channel formed by the orifice plate structure disclosed in an embodiment of the present invention;

[0027] Figure 5 Schematic diagram of a labyrinth seal structure formed by the orifice plate structure disclosed in an embodiment of the present invention;

[0028] Figure 6 Schematic diagram of a cover and a lead seat disclosed in an embodiment of the present invention;

[0029] Wherein, 1, engine casing; 2, lead seat; 21, outer conical surface; 22, necking section; 3, compression cap; 4, orifice plate; 41, opening; 42, groove; 43, boss; 44, eccentric lead hole; 441, first round hole; 442, second round hole; 5, elastic structure; 6, cover; 61, inner conical surface; 62, wire passing hole; 7, seal; 8, test lead; 9, lead channel. Detailed implementation manners

[0030] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0031] The following describes the implementation manners of the present application through specific specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features of the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope protected by the present application.

[0032] In the description of this embodiment, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present invention.

[0033] In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0034] It should also be noted that the drawings provided in the following embodiments only schematically illustrate the basic concept of the present disclosure. The drawings only show the components related to the present disclosure, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in its actual implementation may be arbitrarily changed, and the component layout type may also be more complex.

[0035] This embodiment discloses an adjustable lead seal device for an aeroengine. Refer to Figure 1 As shown, the adjustable lead seal device includes a lead seat 2 and a compression nut 3. One end of the lead seat 2 is fixed on the engine casing 1, and the other end is connected to the compression nut 3. The test lead 8 is led out from the engine interior to the engine exterior in sequence through the engine casing 1, the lead seat 2, and the compression nut 3.

[0036] Among them, refer to Figure 1 and Figure 2As shown, a perforated plate structure is provided in the cavity of the lead seat 2. The perforated plate structure includes at least three perforated plates 4 stacked along the lead direction. Each perforated plate 4 is provided with an eccentric lead hole 44, and the eccentric lead holes 44 of all the perforated plates 4 enclose a lead channel through which the test lead 8 passes. For the adjustable lead sealing device of this embodiment, refer to Figure 4 As shown, by adjusting the position of each perforated plate 4, the eccentric lead holes 44 of all the perforated plates 4 can enclose a lead channel 9 of a suitable size according to the dimensional parameters of the test lead 8, which can significantly reduce the gap between the test lead and the lead hole. Therefore, gas leakage can be reduced and the sealing performance can be enhanced. At the same time, when the lead channel 9 is at its maximum, the centers of the eccentric lead holes 44 of all the perforated plates 4 coincide. As the lead channel 9 gradually decreases, the centers of the eccentric lead holes 44 of all the perforated plates 4 do not coincide.

[0037] Furthermore, refer to Figure 1 and Figure 2 As shown, an opening 41 communicating with the eccentric lead hole 44 is formed at the edge of the perforated plate 4. Forming the opening 41 on the perforated plate 4 can facilitate the installation of the test lead 8 into the eccentric lead hole 44.

[0038] Furthermore, refer to Figure 1 、 Figure 2 and Figure 3 As shown, a boss 43 is machined on one surface of the perforated plate 4, and a plurality of grooves 42 mating with the boss 43 on the adjacent perforated plate 4 are circumferentially machined on the other surface. After the test lead 8 is inserted into the eccentric lead hole 44 of each perforated plate 4 and the circumferential angle of each perforated plate 4 is adjusted according to the size of the test lead 8 to change the size of the lead channel 9, the boss 43 of the lower perforated plate 4 is placed into the groove 42 of the upper perforated plate 4, which can limit the two perforated plates 4 and prevent relative movement between the two perforated plates 4 due to vibration during testing, affecting the change of the size of the lead channel 9.

[0039] Furthermore, there are 1 - 3 bosses 43 on the perforated plate 4, and at the same time, the opening 41 can be located in the middle of two adjacent grooves 42. At the same time, it should be noted that the number of grooves 42 on the perforated plate 4 can be adjusted according to the size of the perforated plate 4. In specific implementation, the number of grooves 42 can be set according to the circumferential angle of each adjustment of the perforated plate 4. The more the number of grooves 42 is set, the higher the adjustment accuracy of the size of the lead channel 9, but in order to ensure the reliability of the perforated plate 4, the number of grooves 42 cannot be too many. Therefore, in the embodiment of the present invention, it is preferably selected to set the number of grooves 42 to 4 - 8. For example, refer to Figure 2 As shown, 2 bosses 43 and 6 grooves 42 can be evenly arranged on the perforated plate 4, so that the angle between two adjacent grooves 42 is 60° ± 2°.

[0040] Furthermore, the boss 43 and the groove 42 can be Figures 2 to 3 the square structure shown, or can be other shapes, and the present invention does not limit them.

[0041] Further, referring to Figure 3 shown, the eccentric lead hole 44 includes concentric first circular hole 441 and second circular hole 442, the diameter of the first circular hole 441 is smaller than the diameter of the second circular hole 442, and the second circular holes 442 of all the eccentric lead holes 44 form a labyrinth seal structure. Through the design of the labyrinth seal structure, the resistance of the gas flowing through here can be increased, the gas flow rate finally flowing through the orifice plate structure can be greatly reduced, and the sealing performance can be enhanced. Specifically, when machining the eccentric lead hole 44, a first circular hole 441 can be machined on the orifice plate 4 first, and then a shallow groove is machined on the outer circle of the first circular hole 441 of the orifice plate 4 to form the second circular hole 442. After all the orifice plates 4 are stacked and the size of the lead channel 9 is adjusted according to the test lead 8, the second circular holes 442 of all the orifice plates 4 can form a labyrinth seal structure as Figure 5 shown. Through the design of the labyrinth seal structure, when the leakage gas flows through, due to the blocking effect of the labyrinth seal structure, the leakage gas flow rate will gradually decrease, improving the gas sealing performance.

[0042] Furthermore, referring to Figure 1 shown, an elastic structure 5 is provided above the orifice plate structure, and a hole through which the test lead 8 passes is provided on the elastic structure 5. Preferably, the elastic structure 5 is a pre-compressed spring. The pre-compressed spring can press the orifice plate structure to ensure that there is no radial displacement between the orifice plates 4, increasing the connection reliability.

[0043] Furthermore, referring to Figure 1 and Figure 6 shown, a cover 6 is provided at the outlet end of the lead seat 2. An outer conical surface 21 facing the direction of the engine casing 1 is provided at the edge of the outlet end of the lead seat 2. An inner conical surface 61 matching the outer conical surface 21 is provided on the outer circumference of the cover 6, and a wire passing hole 62 is provided on the cover 6. By pressing the cover 6 on the lead seat 2, the precise fit between the inner conical surface 61 and the outer conical surface 21 further reduces gas leakage and enhances the sealing performance.

[0044] Preferably, referring to Figure 1 and Figure 6 shown, a necking section 22 is machined on the outer peripheral wall of the lead seat 2 and below the outer conical surface 21. The necking section 22 has the characteristic of elastic deformation. When subjected to the pressing force of the compression cap 3 and the cover 6, the necking section 22 can produce elastic deformation. During operation, this elastic force can continuously generate a meshing force on the thread pair between the lead seat 2 and the compression cap 3, thereby preventing the compression cap 3 from rotating, that is, having a self-locking function.

[0045] Further, the lead seat 2 and the compression cap 3 can be connected by a thread pair to improve the connection stability of the adjustable lead seal device.

[0046] Further, as shown in Figure 1 a seal 7 is provided between the lead seat 2 and the engine casing 1. Specifically, the seal 7 can adopt a sealing ring structure, which can be used as the first sealing means and can effectively reduce the gas leakage between the lead seat and the casing mounting surface.

[0047] When the adjustable lead seal device of the present invention is in use, first, the lead seat 2 is fixed on the engine casing 1, and the test lead 8 is passed through the engine casing 1; secondly, the test lead 8 is sequentially inserted into the eccentric lead hole 44 from the opening 41 of each orifice plate 4, and the size of the lead channel 9 is adjusted by adjusting the circumferential angle of each orifice plate 4, and then the bosses 43 of adjacent orifice plates 4 are placed into the grooves 42 to assemble into an orifice plate structure; then, the test lead 8 is passed through the elastic structure 5, and the elastic structure 5 and the orifice plate structure are tightly sealed by using the cover 6; finally, the compression cap 3 is connected to the lead seat.

[0048] The embodiments of the present invention achieve the following technical effects:

[0049] 1. By designing the orifice plate structure, the present invention can adjust the size of the lead channel in a timely manner according to the number of test leads, thereby reducing gas leakage and enhancing the sealing performance.

[0050] 2. By combining multiple sealing methods such as sealant sealing, labyrinth sealing structure sealing, elastic structure pressing sealing, conical surface pressing sealing, and sealant sealing, the present invention minimizes gas leakage and improves the sealing performance.

[0051] 3. The adjustable lead seal device of the present invention does not require the use of sealant, greatly saving the waiting time for sealant to solidify and enabling a quick response to emergency assembly tasks.

[0052] 4. The inner peripheral wall of the compression cap is provided with an internal thread that mates with the external thread on the outer peripheral wall of the lead seat. Through the elastic deformation restoring force of the necking section of the lead seat, the thread connection pair has a self-locking function, eliminating the need for the wire locking process and making the installation process simple and convenient.

[0053] Obviously, those skilled in the art should understand that the above description is only a preferred embodiment of the present invention and is not used to limit the present invention. For those skilled in the art, various changes and modifications can be made to the embodiments of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0054] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An adjustable lead sealing device for an aircraft engine, comprising a lead seat (2) and a pressure cap (3), wherein one end of the lead seat (2) is fixed to an engine casing (1), and the other end is connected to the pressure cap (3), and a test lead (8) is led out from the inside of the engine through the engine casing (1), the lead seat (2) and the pressure cap (3) in sequence to the outside of the engine, characterized in that: A perforated plate structure is provided in the cavity of the lead base (2), the perforated plate structure comprising at least three perforated plates (4) stacked along the lead direction, each perforated plate (4) being provided with an eccentric lead hole (44), and the position of each perforated plate (4) being adjusted so that the eccentric lead holes (44) of all the perforated plates (4) form a lead channel through which the test lead (8) passes according to the size parameters of the test lead (8); a boss (43) is machined on one surface of the perforated plate (4), and a plurality of grooves (42) are circumferentially machined on the other surface to match the boss (43) on the adjacent perforated plate (4).

2. The adjustable lead wire sealing device for an aircraft engine according to claim 1, characterized in that: An opening (41) communicating with the eccentric lead-in hole (44) is provided on the edge of the orifice plate (4).

3. The adjustable lead wire sealing device for an aircraft engine according to claim 1, characterized in that: The number of the bosses (43) on the orifice plate (4) is 1 to 3, and the number of the grooves (42) is 4 to 8.

4. The adjustable lead wire sealing device for an aircraft engine according to claim 1, characterized in that: The eccentric lead-in hole (44) comprises a concentric first circular hole (441) and a second circular hole (442); the diameter of the first circular hole (441) is smaller than the diameter of the second circular hole (442); and the second circular holes (442) of all the eccentric lead-in holes (44) form a labyrinth sealing structure.

5. The adjustable lead sealing device for an aircraft engine according to any one of claims 1 to 4, characterized in that: An elastic structure (5) is provided above the orifice plate structure, and a hole through which the test lead (8) passes is provided on the elastic structure (5).

6. The adjustable lead wire sealing device for an aircraft engine according to claim 5, characterized in that: The elastic structure (5) is a pre-compression spring.

7. The adjustable lead wire sealing device for an aircraft engine according to any one of claims 1 to 4, characterized in that: The outlet end of the lead-wire holder (2) is provided with a cover (6); the outlet end edge of the lead-wire holder (2) is provided with an outer conical surface (21) facing the engine casing (1); the outer periphery of the cover (6) is provided with an inner conical surface (61) matching the outer conical surface (21); and the cover (6) is provided with a threading hole (62).

8. The adjustable lead wire sealing device for an aircraft engine according to claim 7, characterized in that: A necking section (22) is machined on the outer peripheral wall of the lead seat (2) and located below the outer conical surface (21).

9. The adjustable lead wire sealing device for an aircraft engine according to claim 1, characterized in that: A sealing member (7) is provided between the lead base (2) and the engine casing (1).

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