Adjustable lead sealing device for aero-engine

Abstract

The invention belongs to the field of aero-engines, relates to a test lead sealing design technology, and discloses an adjustable lead sealing device for an aero-engine, which comprises a lead seat and a pressing cap, one end of the lead seat is fixed on an engine casing, and the other end of the lead seat is connected with the pressing cap. And a test lead is sequentially led out of the engine from the inside of the engine through the engine case, the lead seat and the pressing cap. A cavity of the lead seat is internally provided with a pore plate structure, the pore plate structure comprises at least three pore plates which are stacked along the lead direction, each pore plate is provided with an eccentric lead hole, and the eccentric lead holes of all the pore plates define a lead channel through which the test lead passes. The adjustable lead sealing device has the advantages that the size of the lead channel is adjustable, the sealing performance is good, the adjustable lead sealing device can be installed and used without waiting, and the adjustable lead sealing device has a self-locking function.

Description

Technical Field

[0001] The invention belongs to the field of aeroengines, relates to a test lead seal design technology, and in particular to an adjustable lead seal device for an aeroengine. Background Art

[0002] An aircraft engine is a device that provides power for aircraft. It has the working characteristics of high temperature, high pressure and high speed, which requires a considerable level of technology to develop. Among them, testing technology is one of the most important technologies in the development of aircraft engines. Through testing, parameters such as gas pressure and temperature at different positions inside the aircraft engine can be obtained. When designing the test lead, it is necessary to make the lead structure minimize the impact on engine performance, thereby ensuring the accuracy of the test results.

[0003] In order to achieve the purpose of sealing the test lead, the traditional method is to use a structure of sol and orifice plate, and fill it with sealant while leading the test line out to achieve the purpose of sealing. However, the solution of using sol and orifice plate has the following disadvantages: 1) This solution is a fixed design. The size of the lead hole cannot change with the number of leads, which will affect the subsequent sealing process and further affect the sealing performance; 2) Bundling cannot be performed during the lead-in process, and the assembly process is more complicated. Summary of the invention

[0004] In order to solve the technical problems that the size of the lead hole cannot be adjusted due to the test lead sealing structure of the sol-gel plus perforated plate, the sealing performance is poor due to the influence of the sealing process, and the test leads cannot be bundled, resulting in a cumbersome assembly process, the present invention discloses an adjustable lead sealing device for an aircraft engine, the adjustable lead sealing device comprises a lead seat and a pressure cap, one end of the lead seat is fixed on the engine casing, and the other end is connected to the pressure cap, and 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 pressure cap in sequence.

[0005] Among them, a hole plate structure is provided in the cavity of the lead seat, and the hole plate structure includes at least 3 hole plates stacked along the lead direction, each of the hole plates is provided with an eccentric lead hole, and the eccentric lead holes of all the hole plates form a lead channel through which the test lead passes.

[0006] Furthermore, an opening communicating with the eccentric lead hole is formed on the edge of the orifice plate.

[0007] Furthermore, a boss is processed on one surface of the orifice plate, and a plurality of grooves are circumferentially processed on the other surface to match the boss on the adjacent orifice plate.

[0008] Furthermore, there are 1 to 3 bosses and 4 to 8 grooves on the orifice plate.

[0009] Furthermore, the eccentric lead-in hole comprises a first circular hole and a second circular hole which are concentric, the diameter of the first circular hole is smaller than the diameter of the second circular hole, and the second circular holes of all the eccentric lead-in holes form a labyrinth sealing structure.

[0010] 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.

[0011] Preferably, the elastic structure is a pre-compressed spring.

[0012] Furthermore, a sealing cover is provided at the outlet end of the lead-wire holder, an outer conical surface is provided at the edge of the outlet end of the lead-wire holder facing the engine casing, an inner conical surface matching the outer conical surface is provided at the outer periphery of the sealing cover, and a threading hole is provided on the sealing cover.

[0013] Preferably, a necking section is processed on the outer peripheral wall of the lead holder and located below the outer conical surface.

[0014] Furthermore, a seal is provided between the lead holder and the engine casing.

[0015] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects: 1. The present invention can timely adjust the size of the lead channel according to the number of test leads by designing the orifice plate structure, thereby reducing gas leakage and enhancing sealing performance.

[0016] 2. The present invention combines a variety of sealing methods such as sealing of sealing elements, sealing of labyrinth sealing structures, compression sealing of elastic structures, compression sealing of cone surfaces and sealing adhesive sealing, thereby minimizing gas leakage and improving sealing performance.

[0017] 3. The adjustable lead sealing device of the present invention does not require the use of sealant, which greatly saves the waiting time for the sealant to solidify and can quickly respond to emergency assembly tasks.

[0018] 4. The inner wall of the pressure cap is provided with an internal thread that matches the external thread on the outer wall of the lead seat. Through the elastic deformation recovery force of the necking section of the lead seat, the threaded connection pair has a self-locking function, eliminating the locking wire process and making the installation process simple and convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 A schematic diagram of an adjustable lead sealing device for an aircraft engine disclosed in an embodiment of the present invention; Figure 2 A schematic diagram of a hole plate disclosed in an embodiment of the present invention; Figure 3 for Figure 2 AA direction cross-sectional view of the orifice plate shown in ; Figure 4 A schematic diagram of a lead channel formed by a hole plate structure disclosed in an embodiment of the present invention; Figure 5 A schematic diagram of a labyrinth sealing structure formed by a perforated plate structure disclosed in an embodiment of the present invention; Figure 6 A schematic diagram of a cover and a lead holder disclosed in an embodiment of the present invention; Among them, 1. engine casing; 2. lead holder; 21. outer cone; 22. neck section; 3. pressure cap; 4. orifice plate; 41. opening; 42. groove; 43. boss; 44. eccentric lead hole; 441. first circular hole; 442. second circular hole; 5. elastic structure; 6. cover; 61. inner cone; 62. threading hole; 7. seal; 8. test lead; 9. lead channel. DETAILED DESCRIPTION

[0021] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0022] The following describes the implementation methods of the present application through specific specific examples, and 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 methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0023] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the invention.

[0024] In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "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 "plurality" is two or more.

[0025] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure. The illustrations only show components related to the present disclosure rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0026] This embodiment discloses an adjustable lead wire sealing device for an aircraft engine, see Figure 1 As shown, the adjustable lead sealing device includes a lead holder 2 and a pressure cap 3, one end of the lead holder 2 is fixed on the engine casing 1, and the other end is connected to the pressure cap 3, and the test lead 8 is led out from the inside of the engine through the engine casing 1, the lead holder 2 and the pressure cap 3 in sequence to the outside of the engine.

[0027] Among them, see Figure 1 and Figure 2 As shown, a hole plate structure is provided in the cavity of the lead holder 2, and the hole plate structure includes at least three hole plates 4 stacked along the lead direction, each of the hole plates 4 is provided with an eccentric lead hole 44, and the eccentric lead holes 44 of all the hole plates 4 form a lead channel through which the test lead 8 passes. Figure 4As shown, by adjusting the position of each orifice plate 4, the eccentric lead holes 44 of all orifice plates 4 can be surrounded by a lead channel 9 of appropriate size according to the size parameters of the test lead 8, which can significantly reduce the gap between the test line and the lead hole, thereby reducing gas leakage and enhancing the sealing performance. At the same time, when the lead channel 9 is the largest, the hole centers of the eccentric lead holes 44 of all the orifice plates 4 coincide, and as the lead channel 9 gradually decreases, the hole centers of the eccentric lead holes 44 of all the orifice plates 4 do not coincide.

[0028] Further, see Figure 1 and Figure 2 As shown, an opening 41 communicating with the eccentric lead hole 44 is formed at the edge of the orifice plate 4 . The opening 41 is formed on the orifice plate 4 to facilitate installation of the test lead 8 into the eccentric lead hole 44 .

[0029] Further, see Figure 1 , Figure 2 and Figure 3 As shown, one surface of the orifice plate 4 is processed with a boss 43, and the other surface is circumferentially processed with a plurality of grooves 42 that match the boss 43 on the adjacent orifice plate 4. After the test lead 8 is inserted into the eccentric lead hole 44 of each orifice plate 4 and the circumferential angle of each orifice 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 orifice plate 4 is placed into the groove 42 of the upper orifice plate 4, so that the two orifice plates 4 can be limited to avoid relative movement between the two orifice plates 4 due to vibration during testing, which affects the change in the size of the lead channel 9.

[0030] Furthermore, there are 1 to 3 bosses 43 on the orifice plate 4, and 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 orifice plate 4 can be adjusted according to the size of the orifice plate 4. In specific implementation, the number of grooves 42 can be set according to the circumferential angle of the orifice plate 4 each time. The more the number of grooves 42 is set, the higher the size adjustment accuracy of the lead channel 9. However, in order to ensure the reliability of the orifice plate 4, the number of grooves 42 cannot be too many. Therefore, in the embodiment of the present invention, the number of grooves 42 is preferably set to 4 to 8. For example, see Figure 2 As shown, two bosses 43 and six grooves 42 may be evenly arranged on the orifice plate 4, so that the angle between two adjacent grooves 42 is 60°±2°.

[0031] Furthermore, the boss 43 and the groove 42 may be Figures 2 to 3 The square structure shown may also be in other shapes, which is not limited by the present invention.

[0032] Further, see Figure 3As shown, the eccentric lead hole 44 includes 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. The second circular holes 442 of all the eccentric lead holes 44 form a labyrinth sealing structure. The design of the labyrinth sealing structure can also increase the resistance of gas flowing through this place, greatly reduce the gas flow that finally flows through the orifice plate structure, and enhance the sealing performance. Specifically, when processing the eccentric lead hole 44, a first circular hole 441 can be processed on the orifice plate 4 first, and then a shallow groove is processed on the outer circle of the first circular hole 441 of the orifice plate 4 to form a 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 be formed as follows. Figure 5 The labyrinth seal structure shown in the figure. Through the design of the labyrinth seal structure, when the leaking gas flows through, due to the blocking effect of the labyrinth seal structure, the leaking gas flow rate will be reduced step by step, thereby improving the gas sealing performance.

[0033] Further, see Figure 1 As shown, an elastic structure 5 is provided above the orifice plate structure, and a hole is provided on the elastic structure 5 for the test lead 8 to pass through. Preferably, the elastic structure 5 is a pre-compression spring. The pre-compression spring can compress the orifice plate structure to ensure that there is no radial displacement between the orifice plates 4, thereby increasing the connection reliability.

[0034] Further, see Figure 1 and Figure 6 As shown, the outlet end of the lead base 2 is provided with a cover 6, the outlet end edge of the lead base 2 is provided with an outer cone 21 facing the engine casing 1, the outer periphery of the cover 6 is provided with an inner cone 61 matching with the outer cone 21, and the cover 6 is provided with a threading hole 62. By pressing the cover 6 onto the lead base 2, the gas leakage is further reduced through the precise matching between the inner cone 61 and the outer cone 21, and the sealing performance is enhanced.

[0035] Preferably, see Figure 1 and Figure 6 As shown, a necking section 22 is processed on the outer peripheral wall of the lead base 2 and below the outer cone surface 21. The necking section 22 has the characteristic of elastic deformation. When subjected to the pressing force of the pressure cap 3 and the cover 6, the necking section 22 can produce elastic deformation. During operation, this elastic force can continuously generate meshing force on the thread pair between the lead base 2 and the pressure cap 3, thereby preventing the pressure cap 3 from rotating, that is, it has a self-locking function.

[0036] Furthermore, the lead holder 2 and the pressure cap 3 can be connected via a threaded pair to improve the connection stability of the adjustable lead sealing device.

[0037] Further, see Figure 1As shown, a seal 7 is provided between the lead base 2 and the engine casing 1. In a specific implementation, the seal 7 can adopt a sealing ring structure, which can be used as a first sealing means to effectively reduce gas leakage between the lead base and the casing mounting surface.

[0038] When the adjustable lead sealing device of the present invention is used, first, the lead holder 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 installed 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 boss 43 of the adjacent orifice plate 4 is placed into the groove 42 to assemble and form 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 compressed and sealed using the cover 6; finally, the pressure cap 3 is connected to the lead holder.

[0039] The embodiments of the present invention achieve the following technical effects: 1. The present invention can timely adjust the size of the lead channel according to the number of test leads by designing the orifice plate structure, thereby reducing gas leakage and enhancing sealing performance.

[0040] 2. The present invention combines a variety of sealing methods such as sealing of sealing elements, sealing of labyrinth sealing structures, compression sealing of elastic structures, compression sealing of cone surfaces and sealing adhesive sealing, thereby minimizing gas leakage and improving sealing performance.

[0041] 3. The adjustable lead sealing device of the present invention does not require the use of sealant, which greatly saves the waiting time for the sealant to solidify and can quickly respond to emergency assembly tasks.

[0042] 4. The inner wall of the pressure cap is provided with an internal thread that matches the external thread on the outer wall of the lead seat. Through the elastic deformation recovery force of the necking section of the lead seat, the threaded connection pair has a self-locking function, eliminating the locking wire process and making the installation process simple and convenient.

[0043] Obviously, those skilled in the art should understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and changes. 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.

[0044] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes 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 of the perforated plates (4) being provided with an eccentric lead hole (44), and the eccentric lead holes (44) of all the perforated plates (4) forming a lead channel through which the test lead (8) passes.

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: One surface of the orifice plate (4) is processed with a boss (43), and the other surface is circumferentially processed with a plurality of grooves (42) that cooperate with the boss (43) on the adjacent orifice plate (4).

4. The adjustable lead wire sealing device for an aircraft engine according to claim 3, 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.

5. 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.

6. The adjustable lead wire sealing device for an aircraft engine according to any one of claims 1 to 5, 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).

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

8. The adjustable lead sealing device for an aircraft engine according to any one of claims 1 to 5, 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).

9. The adjustable lead wire sealing device for an aircraft engine according to claim 8, 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).

10. 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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