Aero-engine borescope plug assembly structure

Abstract

The embodiment of the invention provides an aero-engine borescope plug assembly structure, and relates to the field of aero-engines. The borescope plug assembly aims to solve the problems that a borescope plug assembly cannot overcome deformation and incoordination of an inner casing and an outer casing at the same time, and the high-temperature thermal cycle working condition exists. Comprising an inner plug, an outer plug, a check ring and a plugging piece, an inner plugging sealing part at the lower end of the inner plug is used for being connected with an inner-layer casing hole inspection hole mounting seat, and an inner plugging mounting part at the upper end of the inner plug is assembled in an outer-layer casing hole inspection hole mounting seat; an outer plug sealing part at the lower end of the outer plug is connected with the outer-layer casing hole inspection hole mounting seat; the check ring is arranged between the upper end inner plug mounting part and the upper end outer plug mounting part in a sleeving manner; and the plugging piece is connected with the upper end inner plug mounting part. By adopting a separated rigid structure and clearance fit, the problem of failure of the borescope plug assembly caused by failure after a plurality of high-temperature thermal cycle working conditions is avoided, and the defect that a rigid plug cannot adapt to the borescope plug assembly caused by inconsistent deformation of an inner casing and an outer casing is overcome.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically, to a structure for an aero-engine borehole probe plug assembly. Background Technology

[0002] Currently, in multi-stage axial compressors used in domestic and international aero engines, the compressor casings of the later stages typically employ a double-layer casing structure, which provides favorable conditions for radial clearance control. Because the inner and outer casings function separately—the outer layer primarily transmits loads while the inner layer forms the flow channel—large deformations of the outer casing caused by mechanical loads or thermal loads can be prevented from affecting the inner flow channel. Simultaneously, the larger diameter of the outer casing increases the longitudinal stiffness of the casing, contributing to reliable engine operation.

[0003] Due to the structural characteristics of the compressor's double-layer casing, when installing a borescope inspection port, the borescope plug structure must simultaneously cooperate with the mounting bases of both the inner and outer casings to ensure a tight seal and prevent air leakage. Conventional rigid borescope plug structures cannot accommodate the inconsistent deformation of the inner and outer casings. While borescope plug assemblies using compression springs solve the problem of inconsistent deformation between the inner and outer casings, the springs are prone to loss of elasticity after undergoing multiple high-temperature thermal cycles, significantly shortening the service life of the borescope plug assembly and increasing engine inspection and maintenance costs. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0005] The objectives of this invention include, for example, providing a structure for an aero-engine borehole plug assembly that can improve the problem that borehole plug assemblies cannot simultaneously overcome the incoordination of inner and outer casing deformation and high-temperature thermal cycling conditions.

[0006] The embodiments of the present invention can be implemented as follows:

[0007] This invention provides an aero-engine borehole plug assembly structure for mounting on an outer casing borehole mounting base and an inner casing borehole mounting base. The aero-engine borehole plug assembly structure includes an inner plug, an outer plug, a stop ring, and a sealing element. The inner plug has a lower inner plug sealing portion and an upper inner plug mounting portion positioned opposite each other. The lower inner plug sealing portion is used to connect to the inner casing borehole mounting base and plug the borehole of the compressor rectifier. The upper inner plug mounting portion is assembled inside the outer casing borehole mounting base. The outer plug has a central through-hole structure, and the outer plug has a positional... The device comprises a lower outer plug sealing part and an upper outer plug mounting part. The outer plug is used to fit around the outer periphery of the inner plug, and the lower outer plug sealing part is connected to the outer casing hole probe mounting seat. The stop ring is fitted between the upper inner plug mounting part and the upper outer plug mounting part. The inner periphery of the stop ring is clearance-fitted with the upper inner plug mounting part and circumferentially limited. The outer periphery of the stop ring is clearance-fitted with the upper outer plug mounting part and circumferentially limited. The sealing member is connected to the upper inner plug mounting part and seals the gap between the upper inner plug mounting part, the stop ring, and the upper outer plug mounting part.

[0008] In addition, the aero-engine borehole plug assembly structure provided in the embodiments of the present invention may also have the following additional technical features:

[0009] Optionally, the inner circumference of the stop ring is provided with an inner claw, and the outer circumference of the stop ring is provided with an outer claw; the outer circumference of the upper inner plug mounting portion of the inner plug is provided with an inner plug groove, and the inner circumference of the upper outer plug mounting portion of the outer plug is provided with an outer plug groove; the inner claw engages with the inner plug groove with a clearance fit, and the outer claw engages with the outer plug groove with a clearance fit, so as to circumferentially limit the inner plug and the outer plug.

[0010] Optionally, the edges of the inner plug groove are rounded, the edges of the outer plug groove are rounded, and the roots of both the inner and outer claws are rounded.

[0011] Optionally, the lower end of the inner plug includes a sealing boss, a threaded section of the inner plug, and a sealing edge of the inner plug connected in sequence; the sealing boss is used to seal the probe hole of the compressor rectifier, the threaded section of the inner plug is used to be threadedly connected to the inner casing probe hole mounting seat, and the sealing edge of the inner plug is used to seal and fit against the end face of the inner casing probe hole mounting seat.

[0012] Optionally, the end face of the upper inner plug mounting portion of the inner plug is provided with a threaded hole, which is used for threaded connection with the sealing member.

[0013] Optionally, the lower end of the outer plug includes an outer plug threaded section and an outer plug sealing edge connected in sequence; the outer plug threaded section is used to be threadedly connected to the outer casing hole probe mounting seat, and the outer plug sealing edge is used to seal and fit against the end face of the outer casing hole probe mounting seat.

[0014] Optionally, the outer periphery of the upper inner plug mounting portion of the outer plug is provided with an outer plug locking hole; the outer plug locking hole is used to connect with the housing to stop the circumferential rotation of the outer plug.

[0015] Optionally, the upper inner plug mounting portion of the inner plug is a regular prism structure for compatibility with a torque wrench tool; the upper inner plug mounting portion of the outer plug is a regular prism structure for compatibility with a torque wrench tool.

[0016] Optionally, the sealing component includes a sealing threaded section and a nut section arranged sequentially; the sealing threaded section is used to thread-connect with the upper inner plug mounting part of the inner plug head; the end face of the nut section is provided with a mounting groove, which is used to cooperate with a torque wrench tool; the outer periphery of the nut section is provided with a sealing locking hole, which is used to connect with the housing to stop the circumferential rotation of the sealing component.

[0017] The beneficial effects of the aero-engine borehole plug assembly structure of this invention include, for example:

[0018] The aero-engine borehole plug assembly includes an inner plug, an outer plug, a stop ring, and sealing components. The inner plug has a lower inner plug sealing portion and an upper inner plug mounting portion positioned opposite each other. The lower inner plug sealing portion is used to connect with the inner casing borehole mounting seat and plug the borehole of the compressor rectifier. The upper inner plug mounting portion is assembled inside the outer casing borehole mounting seat. The outer plug has a central through-hole structure and has a lower outer plug sealing portion and an upper outer plug mounting portion positioned opposite each other. The outer plug is fitted around the outer periphery of the inner plug, and the lower outer plug sealing part is connected to the outer casing hole probe mounting seat; the stop ring is fitted between the upper inner plug mounting part and the upper outer plug mounting part, the inner periphery of the stop ring is clearance-fitted with the upper inner plug mounting part and circumferentially limited, and the outer periphery of the stop ring is clearance-fitted with the upper outer plug mounting part and circumferentially limited; the sealing part is connected to the upper inner plug mounting part and seals the gap between the upper inner plug mounting part, the stop ring and the upper outer plug mounting part.

[0019] The combination of inner plug, outer plug, stop ring, and sealing components enables the sealing of inner and outer probe holes in the double-layer casing structure of aero engines, especially high-pressure compressors. This separate rigid structure avoids the failure of the probe hole plug assembly caused by the failure of elastic elements after multiple high-temperature thermal cycles, significantly improving the service life of the parts and reducing engine inspection and maintenance costs. The stop ring has a small clearance fit with both the inner and outer plugs, achieving circumferential stopping connection between the inner and outer plugs while avoiding the defect of rigid plugs being unable to adapt to the inconsistent deformation of the inner and outer casings during engine operation. Attached Figure Description

[0020] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0021] Figure 1 This is a schematic diagram of the installation position of the aero-engine borehole probe plug assembly structure provided in an embodiment of the present invention;

[0022] Figure 2 An exploded view of the structure of the aero-engine borehole probe plug assembly provided in an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the inner plug in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0024] Figure 4 This is a cross-sectional view along AA of the inner plug in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0025] Figure 5 This is a schematic diagram of the outer plug in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0026] Figure 6 This is a cross-sectional view along BB of the outer plug in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0027] Figure 7 This is a schematic diagram of the stop ring in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0028] Figure 8 This is a cross-sectional view along CC of the stop ring in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0029] Figure 9 This is a schematic diagram of the sealing component in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0030] Figure 10 This is a cross-sectional view along DD of the sealing component in the aero-engine borehole plug assembly structure provided in an embodiment of the present invention;

[0031] Figure 11 This is a schematic diagram of the assembly of the inner plug of the aero-engine borehole probe plug assembly provided in an embodiment of the present invention;

[0032] Figure 12 This is a schematic diagram of the assembly of the inner and outer plugs of the aero-engine borehole probe plug assembly provided in an embodiment of the present invention;

[0033] Figure 13 This is a schematic diagram of the assembly of the inner plug, outer plug, and stop ring of the aero-engine borehole probe plug assembly provided in an embodiment of the present invention;

[0034] Figure 14 This is an assembly diagram of the inner plug, outer plug, stop ring, and sealing component of the aero-engine borehole probe plug assembly provided in an embodiment of the present invention.

[0035] Icons: Aircraft engine borehole probe plug assembly structure-1; Inner plug-2; Outer plug-3; Stop ring-4; Sealing component-5; Inner casing borehole probe mounting base-6; Outer casing borehole probe mounting base-7; Sealing boss-8; Inner plug threaded section-9; Inner plug sealing edge-10; Upper inner plug mounting part-11; Inner plug slot-12; Threaded hole-13; Outer plug threaded section-14; Outer plug sealing edge-15; Upper outer plug mounting part-16; Outer plug slot-17; Inner claw-18; Outer claw-19; Sealing threaded section-20; Nut section-21; Mounting groove-22. Detailed Implementation

[0036] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0037] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does 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 this invention.

[0038] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0039] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable 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, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] The following is combined Figures 1 to 14 The structure 1 of the aero-engine borehole probe plug assembly provided in this embodiment will be described in detail.

[0041] Please refer to Figure 1 , Figure 2 and Figure 14 This invention provides an aero-engine borehole plug assembly structure 1 for mounting on an outer casing borehole mounting base 7 and an inner casing borehole mounting base 6. The aero-engine borehole plug assembly structure 1 includes an inner plug 2, an outer plug 3, a stop ring 4, and a sealing element 5. The inner plug 2 has a lower inner plug sealing portion and an upper inner plug mounting portion 11 positioned opposite each other. The lower inner plug sealing portion is used to connect with the inner casing borehole mounting base 6 and block the borehole of the compressor rectifier. The upper inner plug mounting portion 11 is assembled inside the outer casing borehole mounting base 7. The outer plug 3 has a central through-hole structure. 3 has a lower outer plug sealing part and an upper outer plug mounting part 16 positioned opposite each other. The outer plug 3 is used to be sleeved on the outer periphery of the inner plug 2, and the lower outer plug sealing part is connected to the outer casing hole probe mounting seat 7. The stop ring 4 is sleeved between the upper inner plug mounting part 11 and the upper outer plug mounting part 16. The inner periphery of the stop ring 4 is clearance-fitted with the upper inner plug mounting part 11 and circumferentially limited. The outer periphery of the stop ring 4 is clearance-fitted with the upper outer plug mounting part 16 and circumferentially limited. The sealing member 5 is connected to the upper inner plug mounting part 11 and seals the gap between the upper inner plug mounting part 11, the stop ring 4 and the upper outer plug mounting part 16.

[0042] The aircraft engine borehole plug assembly structure 1 is used to plug the inner and outer boreholes of the double-layer casing structure in aircraft engines, especially high-pressure compressor structures. The outer casing borehole mounting seat 7 is fixed on the outer casing borehole, and the inner casing borehole mounting seat 6 is fixed on the inner casing borehole.

[0043] The borehole probe plug assembly includes an inner plug 2, an outer plug 3, a stop ring 4, and a sealing element 5. The inner plug 2 is installed to the borehole probe mounting base 6 of the inner casing, and the outer plug 3 is installed to the borehole probe mounting base 7 of the outer casing. The stop ring 4 is installed between the inner and outer plugs 3 to achieve a circumferential stop connection between the inner and outer plugs 3. The sealing element 5 is installed on the inner plug 2 to achieve a tight seal of the borehole probe plug assembly.

[0044] Specifically, the inner plug 2 is cylindrical, with its upper end being the upper inner plug mounting part 11 and its lower end being the lower inner plug sealing part. The inner plug 2 is simultaneously installed on both the outer casing hole probe mounting seat 7 and the inner casing hole probe mounting seat 6. The outer plug 3 has a central through-hole structure, and its inner surface can accommodate the inner plug 2. Its upper end is the upper outer plug mounting part 16, and its lower end is the lower outer plug sealing part. The inner circumference of the stop ring 4 is clearance-fitted with the inner plug 2, and the outer circumference of the stop ring 4 is clearance-fitted with the outer plug 3. This provides a certain clearance margin for the inconsistent deformation caused by uneven heating of the inner and outer plugs 3 during operation, solving the problem that rigid structures cannot adapt to the double-layer casing structure with inconsistent deformation.

[0045] Continuing from the above, the aero-engine borehole plug assembly structure 1 can seal the inner and outer boreholes in the double-layer casing structure. The aero-engine borehole plug assembly structure 1 includes an inner plug 2, an outer plug 3, a stop ring 4, and a sealing component 5. It adopts a separate rigid structure and uses a clearance fit, which can adapt to the inconsistent deformation of the inner and outer casings. At the same time, since the elastic element in the borehole plug assembly is eliminated, the failure of the borehole plug assembly caused by the failure of the elastic element after multiple high-temperature thermal cycles is fundamentally avoided, which significantly improves the service life of the parts and reduces the inspection and maintenance costs of the engine.

[0046] Reference Figure 2 , Figure 3 , Figure 5 , Figure 7 , Figure 8 and Figure 13 In this embodiment, the inner circumference of the stop ring 4 is provided with an inner claw 18, and the outer circumference of the stop ring 4 is provided with an outer claw 19; the outer circumference of the upper end inner plug mounting part 11 of the inner plug 2 is provided with an inner plug groove 12, and the inner circumference of the upper end outer plug mounting part 16 of the outer plug 3 is provided with an outer plug groove 17; the inner claw 18 engages with the inner plug groove 12 with a clearance fit, and the outer claw 19 engages with the outer plug groove 17 with a clearance fit, so as to circumferentially limit the inner plug 2 and the outer plug 3.

[0047] The stop ring 4 is an annular structure with outer claws 19 distributed on its outer surface, which mate with the outer plug groove 17. Its inner surface has inner claws 18 distributed on its inner surface, which mate with the inner plug groove 12, achieving a circumferential stop connection between the inner and outer plugs 3. The outer surface diameter of the stop ring 4 should be slightly smaller than the inner surface diameter of the outer plug 3, and the inner surface diameter should be slightly larger than the outer diameter of the upper inner plug mounting part 11 of the inner plug 2. The inner and outer claws 19 and the inner and outer plug grooves 17 are all in a small clearance fit, providing a certain clearance margin for the inconsistent deformation of the inner and outer plugs 3 due to uneven heating during operation. This solves the difficulty of a rigid structure being unable to adapt to a double-layer casing structure with inconsistent deformation. There is at least one inner claw 18 and at least one outer claw 19, with the positions of the inner claws 18 and outer claws 19 offset circumferentially along the stop ring 4.

[0048] The inner plug groove 12 is located on the upper end face of the upper inner plug mounting part 11, providing mounting space for the inner claw 18 of the stop ring 4. The number of inner plug grooves 12 can be set to be the same as the number of edges of the upper inner plug mounting part 11, and its shape can be set as a cuboid groove located at the center of each edge, which optimizes the stress distribution of the part while facilitating processing. For example, if the upper inner plug mounting part 11 is a hexagonal prism, then one inner plug groove 12 is provided for each edge.

[0049] The outer plug groove 17 is located on the upper end face of the upper outer plug mounting part 16 and on the inner diameter surface of the hollow structure of the outer plug 3, providing installation space for the outer claw 19 of the stop ring 4. The number of outer plug grooves 17 can be different from the number of inner plug grooves 12. The number of inner and outer plug grooves 17 should preferably be a combination of two adjacent grooves with no common factor to increase the probability that the groove positions of the inner and outer plugs 3 will match the claws of the stop ring 4 after they are tightened. The shape of the outer plug groove 17 can also be set as a cuboid groove and evenly distributed on the inner diameter surface of the outer plug 3, with its bottom surface flush with the bottom surface of the inner plug groove 12.

[0050] In this embodiment, the height of the stop ring 4 can be set to be the same as the height of the outer plug groove 17. Since its height is higher than that of the inner plug groove 12, its inner claw 18 can be directly grabbed during disassembly, which is convenient for disassembly.

[0051] In this embodiment, the edges of the inner plug groove 12 are rounded, the edges of the outer plug groove 17 are rounded, and the roots of the inner claw 18 and the outer claw 19 are both rounded.

[0052] The edges of the inner plug groove 12 are rounded to avoid local stress concentration. The edges of the outer plug groove 17 are also rounded to avoid local stress concentration. An inner rounded structure is also provided at the root of the claw to prevent the stop ring 4 from scratching or abrading the inner and outer plugs 3 during assembly and operation. It also provides a certain clearance margin for the inner and outer plugs 3 to deform unevenly due to inconsistent heating during operation, thus solving the problem that rigid structures cannot adapt to the double-layer casing structure with inconsistent deformation.

[0053] Reference Figure 3 , Figure 4 and Figure 11 In this embodiment, the lower end of the inner plug 2 includes a sealing boss 8, an inner plug threaded section 9, and an inner plug sealing edge 10 connected in sequence; the sealing boss 8 is used to seal the test hole of the compressor rectifier, the inner plug threaded section 9 is used to be threadedly connected to the inner casing test hole mounting seat 6, and the inner plug sealing edge 10 is used to seal and fit against the end face of the inner casing test hole mounting seat 6.

[0054] The sealing boss 8, the threaded section 9, and the sealing edge 10 at the lower end of the inner plug 2 cooperate with the rectifier's probe hole and the inner casing's probe hole mounting seat to achieve the sealing of the inner casing's probe hole.

[0055] Specifically, the bottom of the sealing boss 8 is machined with an arc surface and is assembled into the rectifier's probe hole. The threaded section 9 of the inner plug mates with the threaded section of the inner casing probe hole mounting base 6. After the threads are tightened, the sealing edge 10 of the inner plug is completely fitted with the end face of the inner casing probe hole mounting base 6.

[0056] Reference Figure 3 , Figure 4 and Figure 14 In this embodiment, the end face of the upper inner plug mounting portion 11 of the inner plug head 2 is provided with a threaded hole 13, which is used for threaded connection with the sealing member 5. The threaded hole 13 is located on the center line of the upper inner plug mounting portion 11, providing installation space for the sealing member 5.

[0057] Reference Figure 3 and Figure 4 In this embodiment, the upper end of the inner plug 2, the inner plug mounting part 11, is a regular prism structure to be compatible with torque wrench tools. Specifically, it is a regular hexagonal prism structure.

[0058] The upper inner plug mounting part 11 has a regular prism structure, providing a tightening feature for the inner plug 2, which can be tightened using tools such as torque wrenches. Besides being a regular hexagon, the upper inner plug mounting part 11 can also be configured with other shapes suitable for tightening wrenches and other tools. The edges of the upper inner plug mounting part 11 are rounded to prevent damage from collisions with the retaining ring 4.

[0059] Reference Figure 5 , Figure 6 and Figure 12 In this embodiment, the lower end of the outer plug 3 includes an outer plug thread section 14 and an outer plug sealing edge 15 connected in sequence; the outer plug thread section 14 is used to be threadedly connected to the outer casing hole probe mounting seat 7, and the outer plug sealing edge 15 is used to seal and fit with the end face of the outer casing hole probe mounting seat 7.

[0060] The threaded section 14 and sealing edge 15 of the outer plug mate with the outer casing outer hole probe mounting base to seal the outer casing probe hole. Specifically, the threaded section 14 of the outer plug mates with the outer casing probe hole mounting base 7, and after the threads are tightened, the sealing edge 15 of the outer plug is completely flush with the end face of the outer casing probe hole mounting base 7.

[0061] Reference Figure 5 In this embodiment, the upper inner plug mounting part 11 of the outer plug 3 is a regular prism structure to be compatible with torque wrench tools. Specifically, it is a regular hexagonal prism structure.

[0062] The upper inner plug mounting part 11 adopts a regular prism structure, providing a tightening feature for the outer plug 3, and the inner plug 2 can be tightened using tools such as torque wrenches. In addition to being set as a regular hexagon, the upper inner plug mounting part 11 can also be set as other shapes that are compatible with tools such as tightening wrenches.

[0063] Reference Figure 5 In this embodiment, the outer periphery of the inner plug mounting part 11 at the upper end of the outer plug 3 is provided with a locking hole for the outer plug 3; the locking hole for the outer plug 3 is used to connect with the casing to stop the circumferential rotation of the outer plug 3.

[0064] The upper inner plug mounting part 11 is designed with a locking screw hole structure for the outer plug 3, which facilitates subsequent locking with a locking screw. After the stop ring 4 is assembled, its inner and outer claws 19 cooperate with the inner and outer plug grooves 17 respectively to achieve circumferential locking connection between the inner and outer plugs 3. After locking the outer plug 3 with a locking screw, the inner plug 2 can be locked at the same time, preventing the inner plug 2 from loosening during operation.

[0065] Reference Figure 9 , Figure 10 and 14 In this embodiment, the sealing component 5 includes a sealing threaded section 20 and a nut section 21 arranged sequentially. The sealing threaded section 20 is used to be threadedly connected to the upper end of the inner plug mounting part 11 of the inner plug head 2. The end face of the nut section 21 is provided with a mounting groove 22, which is used to cooperate with a torque wrench tool. The outer periphery of the nut section 21 is provided with a sealing locking hole, which is used to connect with the casing to stop the circumferential rotation of the sealing component 5.

[0066] The sealing thread section 20 of the sealing component 5 is installed into the threaded hole 13 of the inner plug 2, achieving a seal for the borehole probe plug assembly itself. The nut section 21 of the sealing component 5 is provided with an installation groove 22, facilitating the tightening of the connecting bolts using tools such as torque wrenches. The nut section 21 may be provided with a locking screw hole feature, allowing the sealing component 5 to be locked in place using a locking screw. Specifically, the sealing component 5 is a connecting bolt structure. After the sealing component 5 is screwed onto the inner plug 2, it simultaneously seals the connection between the inner plug 2 and the stop ring 4, and between the stop ring 4 and the outer plug 3.

[0067] Specifically, after the sealing component 5 is threaded through the mounting groove 22, the end face of the nut section 21 is completely fitted with the upper end face of the inner plug 2. After the assembly is completed, the sealing component 5 can be locked by using the locking screw through the sealing locking screw hole of the sealing component 5.

[0068] Among them, the high-pressure compressor of the aero-engine includes an outer casing hole probe mounting base 7, an inner casing hole probe mounting base 6, and an aero-engine hole probe plug assembly structure 1.

[0069] According to the embodiment of this invention, the working principle of the aero-engine borehole plug assembly structure 1 includes: sealing the inner and outer boreholes of the double-layer casing structure in the aero-engine, especially the high-pressure compressor structure.

[0070] The assembly sequence includes:

[0071] The inner plug 2 is assembled until the sealing edge 10 of the inner plug is completely in contact with the end face of the inner casing hole probe mounting seat 6, and the tightening torque of the inner plug 2 meets the design requirements;

[0072] The outer plug 3 is assembled until the sealing edge 15 of the outer plug is completely in contact with the end face of the outer casing hole probe mounting seat 7. The tightening torque of the outer plug 3 meets the design requirements. At the same time, the inner plug groove 12 of the inner plug 2 and the outer plug groove 17 of the outer plug 3 are kept in the corresponding positions.

[0073] The stop ring 4 is inserted into the borehole plug assembly through the hollow section of the outer plug 3. Its inner claw 18 cooperates with the inner plug groove 12 of the inner plug 2, and its outer claw 19 cooperates with the outer plug groove 17 of the outer plug 3 to achieve circumferential stop connection between the inner and outer plugs 3.

[0074] Assemble the connecting bolt into the threaded hole 13 of the inner plug 2, and tighten the connecting bolt until the end face of its nut section 21 is completely in contact with the upper end face of the inner plug 2. The tightening torque of the connecting bolt meets the design requirements.

[0075] The probe plug is locked by using locking screws through the connecting bolt, the outer plug 3, and the locking screw hole on the casing.

[0076] When disassembling the borehole probe plug assembly, the entire assembly can be removed from the housing directly using the fastening nut head of the outer plug 3. The borehole probe plug assembly can then be disassembled into individual parts for inspection. Subsequent assembly can be performed following the assembly sequence described above.

[0077] The aero-engine borehole plug assembly structure 1 provided in this embodiment has at least the following advantages:

[0078] The aero-engine borehole probe plug assembly structure 1 includes an inner plug 2, an outer plug 3, a stop ring 4, and a sealing element 5. The inner plug 2, outer plug 3, stop ring 4, and sealing element 5 work together to seal the inner and outer boreholes of the double-layer casing structure in aero-engines, especially high-pressure compressors, forming a separate rigid structure. The stop ring 4 has a small clearance fit with both the inner plug 2 and the outer plug 3, achieving circumferential stopping connection between the inner and outer plugs 3 while avoiding the defect of a rigid plug being unable to adapt to the inconsistent deformation of the inner and outer casings during engine operation. Furthermore, it eliminates the need for elastic elements, fundamentally eliminating the disadvantage of elastic elements losing elasticity after multiple high-temperature thermal cycles during operation, which can cause the borehole probe plug assembly to fail. This significantly improves the service life of the borehole probe plug assembly and reduces engine inspection and maintenance costs.

[0079] The inner claw 18 of the stop ring 4 and the inner plug groove 12 of the inner plug 2, as well as the outer claw 19 and the outer plug groove 17 of the outer plug 3, are all fitted with a small clearance. The diameter of the inner surface of the ring is slightly larger than the outer diameter of the upper inner plug mounting part 11 of the inner plug 2, and the diameter of the outer surface of the ring is slightly smaller than the inner diameter of the hollow surface of the outer plug 3. This avoids possible component deformation and failure due to inconsistent thermal deformation of each layer of the casing when the engine is running.

[0080] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A borehole probe plug assembly structure for an aircraft engine, used for mounting on an outer casing borehole probe mounting base and an inner casing borehole probe mounting base, characterized in that, The structure of the aero-engine borehole plug assembly includes: The inner plug has a lower inner plug sealing part and an upper inner plug mounting part that are positioned opposite each other. The lower inner plug sealing part is used to connect with the inner casing hole probe mounting seat and block the hole probe of the compressor rectifier. The upper inner plug mounting part is assembled in the outer casing hole probe mounting seat. The outer plug has a central through hole structure and has a lower outer plug sealing part and an upper outer plug mounting part that are positioned opposite each other. The outer plug is used to be sleeved on the outer periphery of the inner plug, and the lower outer plug sealing part is connected to the outer casing hole probe mounting seat. A stop ring is sleeved between the upper inner plug mounting part and the upper outer plug mounting part. The inner circumference of the stop ring is clearance-fitted with the upper inner plug mounting part and circumferentially limited. The outer circumference of the stop ring is clearance-fitted with the upper outer plug mounting part and circumferentially limited. And a sealing component, which is connected to the upper inner plug mounting part and seals the gap between the upper inner plug mounting part, the stop ring and the upper outer plug mounting part.

2. The structure of the aero-engine borehole probe plug assembly according to claim 1, characterized in that: The inner circumference of the stop ring is provided with an inner pawl, and the outer circumference of the stop ring is provided with an outer pawl. The upper end of the inner plug mounting portion of the inner plug is provided with an inner plug groove on its outer periphery, and the upper end of the outer plug mounting portion of the outer plug is provided with an outer plug groove on its inner periphery; the inner claw engages with the inner plug groove with a clearance fit, and the outer claw engages with the outer plug groove with a clearance fit, so as to circumferentially limit the inner plug and the outer plug.

3. The structure of the aero-engine borehole probe plug assembly according to claim 2, characterized in that: The edges of the inner plug groove are rounded, the edges of the outer plug groove are rounded, and the roots of both the inner and outer claws are rounded.

4. The structure of the aero-engine borehole probe plug assembly according to any one of claims 1 to 3, characterized in that: The lower end of the inner plug includes a sealing boss, a threaded section of the inner plug, and a sealing edge of the inner plug connected in sequence. The sealing boss is used to seal the probe hole of the compressor rectifier. The threaded section of the inner plug is used to be threadedly connected to the inner casing probe hole mounting seat. The sealing edge of the inner plug is used to seal and fit against the end face of the inner casing probe hole mounting seat.

5. The structure of the aero-engine borehole probe plug assembly according to claim 4, characterized in that: The end face of the upper inner plug mounting part of the inner plug is provided with a threaded hole, which is used for threaded connection with the sealing member.

6. The structure of the aero-engine borehole plug assembly according to any one of claims 1 to 3, characterized in that: The lower end of the outer plug includes an outer plug threaded section and an outer plug sealing edge connected in sequence; the outer plug threaded section is used to be threadedly connected to the outer casing hole probe mounting seat, and the outer plug sealing edge is used to seal and fit against the end face of the outer casing hole probe mounting seat.

7. The structure of the aero-engine borehole probe plug assembly according to claim 6, characterized in that: The outer periphery of the upper inner plug mounting part of the outer plug is provided with an outer plug locking screw hole; the outer plug locking screw hole is used to connect with the casing to stop the circumferential rotation of the outer plug.

8. The structure of the aero-engine borehole probe plug assembly according to any one of claims 1 to 3, characterized in that: The upper inner plug mounting portion of the inner plug is a regular prism structure for compatibility with torque wrench tools; the upper inner plug mounting portion of the outer plug is a regular prism structure for compatibility with torque wrench tools.

9. The structure of the aero-engine borehole probe plug assembly according to claim 1, characterized in that: The sealing component includes a sealing threaded section and a nut section arranged sequentially; the sealing threaded section is used to thread into the upper inner plug mounting part of the inner plug head; the end face of the nut section is provided with a mounting groove, which is used to cooperate with a torque wrench tool; the outer periphery of the nut section is provided with a sealing locking hole, which is used to connect with the housing to stop the circumferential rotation of the sealing component.

Images