Plug quick-release structure of aero-engine borescope

Abstract

The invention belongs to the field of aero-engine borescope, and particularly relates to a plug quick-release structure of the aero-engine borescope. The structure comprises a plug, a spring, a mounting seat, a blanking cap and a rubber ring. According to the plug quick-release structure of the aero-engine borescope, the ball-cone centering matching structures are arranged on the plug and the blanking cap, so that slippage between the plug and the blanking cap or the mounting base after mounting is avoided, and meanwhile, self-sealing of a borescope channel is achieved through a rubber ring sealing structure; contact abrasion between the plug and the blanking cap or the mounting base is avoided, meanwhile, the problem that compressed air in the flow channel leaks through a hole exploration channel gap is solved, and the air compression efficiency loss is reduced.

Description

Technical Field

[0001] This application belongs to the field of aero-engine borescopes, and specifically relates to a quick-release structure for a borescope plug of an aero-engine. Background Technology

[0002] Throughout their service life, aero engines undergo periodic inspections of the surface condition of their flow passage components to prevent issues such as excessive cracking or chipping that could compromise engine safety. Inspection methods typically involve visual inspection or borescope checks. Components near the engine inlet and outlet (such as the intake casing support plate, the intake side of the first-stage fan rotor, or the exhaust side of the turbine rotor) can generally be inspected visually. Other flow passage components, such as those in the stator or combustion chamber, require inspection using borescopes. A borescope is a commonly used instrument in aero engines, allowing for internal probing and inspection without disassembling or damaging the engine structure. The casing is equipped with borescope inspection holes and plugs. When inspecting engine flow passage components, the borescope plug is quickly removed, and after inspection, it is reinstalled to seal the flow passage gases.

[0003] Existing borehole probe plugs primarily prevent ejection through the contact surface between the plug and the probe holder. However, with increasing engine usage time, the existing plugging structure lacks an effective centering and limiting mechanism due to alternating effects such as engine vibration and compressed gas pressure within the flow channel. This leads to repeated contact and friction between the plug and the cap or mounting base, causing fretting wear on the plug. Excessive wear on the plug surface results in metal shavings entering the rotating groove of the cap, making plug removal and installation difficult and hindering field support operations. Furthermore, the existing plugging structure lacks an effective sealing mechanism, allowing compressed gas to leak out through gaps between the borehole channels, resulting in reduced compression efficiency.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a quick-release structure for the plug of an aero-engine borescope, in order to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A quick-release structure for a borescope plug on an aircraft engine includes:

[0008] Mounting base, the mounting base is mounted on the casing, the outer ring surface of the mounting base is provided with external threads, and the interior is provided with a stepped cavity, the stepped cavity including an upper cavity and a lower cavity;

[0009] A plug, wherein the inner ring surface of the plug is provided with an internal thread that is compatible with the mounting base, the outer end face of the plug is provided with a strip-shaped opening, and an inner conical transition section of the plug is provided between the internal thread and the strip-shaped opening;

[0010] The plug includes an eccentric positioning section and a guide rod. The eccentric positioning section is provided with an eccentric spherical surface that matches the inner conical transition section of the plug. The end of the eccentric positioning section is provided with a square platform that matches the strip-shaped opening. The square platform is provided with an internal threaded hole that matches the plug disassembly and assembly tool of the borehole probe. The guide rod is provided with an annular groove.

[0011] A spring is installed in the upper cavity and coaxially sleeved on the guide rod. The preload of the spring is used to center and limit the transition section between the eccentric spherical surface and the inner conical surface of the plug.

[0012] A rubber ring is installed in the annular groove, and the rubber ring undergoes elastic compression deformation between the lower cavity and the annular groove to form a sealing pair.

[0013] In at least one embodiment of this application, the mounting base and the housing are connected as one unit by bolts.

[0014] In at least one embodiment of this application, the mounting base and the casing are connected as one unit by welding.

[0015] In at least one embodiment of this application, the mounting base and the plug are provided with mutually compatible locking screw holes, and the plug is locked to the mounting base to prevent loosening after installation.

[0016] In at least one embodiment of this application, positioning lines are provided on both sides of the strip-shaped opening of the plug.

[0017] In at least one embodiment of this application, positioning lines are provided on the square platform of the eccentric positioning segment.

[0018] In at least one embodiment of this application, the guide rod is clearance-fitted with the lower cavity of the mounting base.

[0019] The invention has at least the following beneficial technical effects:

[0020] The quick-release structure for the plug of the aero-engine borescope in this application prevents slippage between the plug and the plug or mounting base after installation by setting a ball-cone centering fit structure on the plug and the plug cover. At the same time, it uses a rubber ring sealing structure to achieve self-sealing of the borescope channel, avoids contact wear between the plug and the plug cover or mounting base, and solves the problem of compressed gas leakage through the gaps in the borescope channel, thereby reducing the loss of compression efficiency. Attached Figure Description

[0021] Figure 1 This is an overall schematic diagram of the quick-release structure of the plug of an aero-engine borescope according to one embodiment of this application;

[0022] Figure 2 This is a schematic diagram of the plug according to one embodiment of this application;

[0023] Figure 3 This is a top view of a plug according to one embodiment of this application;

[0024] Figure 4 This is a top view of the quick-release structure of the plug of an aero-engine borescope according to one embodiment of this application.

[0025] in:

[0026] 1-Plug; 11-Eccentric spherical surface; 12-Annular groove; 13-Square platform; 14-Internal threaded hole; 2-Spring; 3-Mounting base; 4-Plug; 5-Rubber ring. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0028] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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. Therefore, they should not be construed as limiting the scope of protection of this application.

[0029] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0030] This application provides a quick-release structure for a borescope plug for an aircraft engine, including: a plug 1, a spring 2, a mounting base 3, a plug cover 4, and a rubber ring 5.

[0031] Specifically, such as Figure 1 As shown, the mounting base 3 includes a base plate and a plug mounting cylinder. The mounting base 3 is connected to the casing via the base plate. Preferably, the base plate and the casing are connected as one unit by bolts or welding. The outer ring surface of the plug mounting cylinder is provided with external threads for installing the plug cap 4. The interior of the plug mounting cylinder is provided with a through stepped cavity, which includes an upper cavity and a lower cavity.

[0032] The inner ring surface of the plug 4 is provided with an internal thread that matches the mounting base 3. The plug 4 and the mounting base 3 are connected by a threaded connection. The outer end face of the plug 4 is provided with a strip-shaped opening, which can serve as a channel for disassembling and assembling the plug 1. Preferably, positioning lines are provided on both sides of the strip-shaped opening of the plug 4. A tapered transition section is provided between the internal thread of the plug 4 and the strip-shaped opening. In the preferred embodiment of this application, the mounting base 3 and the plug 4 are provided with matching locking screw holes, and the plug 4 is locked to the mounting base 3 after installation to prevent loosening.

[0033] like Figure 2 As shown, the plug 1 includes an eccentric positioning section and a guide rod. The eccentric positioning section has an eccentric spherical surface 11 that matches the inner conical transition section of the plug cap. After installation, the plug 1 achieves self-alignment with the plug cap 4 through the cooperation of the eccentric spherical surface 11 and the inner conical transition section of the plug cap 4. The end of the eccentric positioning section has a square platform 13 that matches the strip opening. The square platform 13 can be positioned with the strip opening on the plug cap 4, and the width of the square platform 13 is slightly smaller than the width of the strip opening. Preferably, two positioning lines are provided on the surface of the square platform 13 in the direction of the eccentric spherical surface 11, such as... Figure 3 As shown; the square platform 13 is provided with an internal threaded hole 14 that is compatible with the hole probe plug removal and installation tool. Part of the guide rod is located in the upper cavity of the mounting base 3, and the other part is located in the lower cavity of the mounting base 3. The guide rod located in the lower cavity is provided with an annular groove 12, and the guide rod is clearance-fitted with the lower cavity of the mounting base 3.

[0034] Spring 2 is installed in the upper cavity and coaxially sleeved on the guide rod. The preload of spring 2 is used to center and limit the eccentric spherical surface 11 and the transition section of the inner conical surface of the plug.

[0035] The rubber ring 5 is installed in the annular groove 12 of the plug 1 to form an integral structure. The rubber ring 5 undergoes elastic compression deformation between the lower cavity and the annular groove 12 to form a sealing pair.

[0036] The quick-release structure for the plug of the aero-engine borescope in this application, such as Figure 4As shown, during installation, the plug removal tool is screwed into the internal threaded hole 14 of plug 1 using a borehole probe. After aligning the square platform 13 of plug 1 with the strip opening of mounting base 3, the integrated structure of plug 1 and rubber ring 5 is placed into the stepped cavity of mounting base 3. Pressing spring 2 rotates it 90 degrees, and the positioning lines on the surface of the square platform 13 of plug 1 become parallel to the positioning lines on both sides of the strip opening of plug 4. Releasing the removal tool, the eccentric spherical surface 11 of the eccentric positioning section of plug 1 and the transition section of the inner conical surface of plug 4 achieve centering and limiting under the preload force of spring 2. Rubber ring 5 undergoes elastic compression deformation between the lower cavity of mounting base 3 and the annular groove 12 of plug 1, forming a sealing pair. During disassembly, the plug removal tool is screwed into the internal threaded hole 14 of plug 1 using a borehole probe, and spring 2 is pressed to rotate it 90 degrees to remove plug 1 and rubber ring 5.

[0037] The quick-release structure for the borescope plug of the aircraft engine disclosed in this application, through the ball-cone centering sealing structure between the borescope plug, the plug cover, and the mounting base, can avoid contact wear between the plug and the plug cover or the mounting base, and at the same time solve the problem of compressed gas leakage through the gap of the borescope channel in the flow channel, reduce the loss of compressed gas efficiency, and thus improve the reliability of engine operation.

[0038] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A quick-release structure for a borescope plug on an aero-engine, characterized in that, include: Mounting seat (3), the mounting seat (3) is mounted on the casing, the outer ring surface of the mounting seat (3) is provided with external threads, and the interior is provided with a stepped cavity, the stepped cavity including an upper cavity and a lower cavity; The plug (4) has an internal thread on its inner ring surface that is compatible with the mounting base (3), and a strip opening on its outer end face. A transition section of the inner conical surface of the plug is provided between the internal thread and the strip opening. The plug (1) includes an eccentric positioning section and a guide rod. The eccentric positioning section is provided with an eccentric spherical surface (11) that is compatible with the inner conical transition section of the plug. The end of the eccentric positioning section is provided with a square platform (13) that is compatible with the strip opening. The square platform (13) is provided with an internal threaded hole (14) that is compatible with the plug disassembly and assembly tool of the borehole probe. The guide rod is provided with an annular groove (12). Spring (2), the spring (2) is installed in the upper cavity and coaxially sleeved on the guide rod, the preload of the spring (2) is used to center and limit the eccentric spherical surface (11) and the transition section of the inner conical surface of the plug; A rubber ring (5) is installed in the annular groove (12). The rubber ring (5) undergoes elastic compression deformation between the lower cavity and the annular groove (12) to form a sealing pair.

2. The quick-release structure for the plug of an aero-engine borescope according to claim 1, characterized in that, The mounting base (3) is connected to the casing by bolts.

3. The quick-release structure for the plug of an aero-engine borescope according to claim 1, characterized in that, The mounting base (3) is connected to the casing by welding.

4. The quick-release structure for the plug of an aero-engine borescope according to claim 1, characterized in that, The mounting base (3) and the plug (4) are provided with matching locking holes. After the plug (4) is installed, it is locked to the mounting base (3) to prevent loosening.

5. The quick-release structure for the plug of an aero-engine borescope according to claim 4, characterized in that, The plug (4) has positioning markings on both sides of its strip-shaped opening.

6. The quick-release structure for the plug of an aero-engine borescope according to claim 5, characterized in that, The eccentric positioning section has positioning lines on its square platform (13).

7. The quick-release structure for the plug of an aero-engine borescope according to claim 6, characterized in that, The guide rod is clearance-fitted with the lower cavity of the mounting base (3).

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