Hole exploration plug assembly, combustion chamber and aero-engine

Abstract

The utility model provides a borescope plug assembly, a combustion chamber and an aero-engine. The borescope plug assembly comprises a first seat body (1); the mounting piece (2) is inserted into the first seat body (1); the plug (3) is arranged on the mounting piece (2) and is used for being inserted into a probe hole (41) in the second seat body (4) for plugging; the self-locking mechanism (5) comprises a locking groove (51) and a locking piece (52), the locking groove (51) is formed in the inner wall of the first seat body (1), the locking piece (52) comprises a first elastic piece (54) and two locking blocks (53), the two locking blocks (53) are oppositely and movably arranged in the mounting piece (2), the first elastic piece (54) is arranged between the two locking blocks (53), and the first elastic piece (54) is arranged on the inner wall of the first seat body (1). And acting force is applied to the two locking blocks (53), so that the two locking blocks (53) extend out of the mounting piece (2) and are clamped with the locking grooves (51). In this way, the anti-loosening process can be simplified.

Description

Technical Field

[0001] The present application relates to the technical field of aeroengines, and particularly relates to a borescope plug assembly, a combustion chamber, and an aeroengine. Background Art

[0002] For on-line inspection, inspection holes are usually provided on components such as the combustion chamber of an aeroengine so that a borescope can extend into the holes for inspection. When inspection is not required, the inspection holes are usually blocked by plugs.

[0003] Traditional plugs are generally locked and loosened by lock wires or lock washers, but this anti-loosening method is relatively complex. Utility Model Content

[0004] The present application aims to provide a borescope plug assembly, a combustion chamber, and an aeroengine to simplify the anti-loosening process of the plug.

[0005] To achieve the above object, the borescope plug assembly provided by the present application includes:

[0006] A first seat body with an installation cavity formed inside;

[0007] An installation member inserted into the installation cavity;

[0008] A plug disposed on the installation member and used to be inserted into an inspection hole on a second seat body to block the inspection hole; and

[0009] A self-locking mechanism including a locking groove and a locking member. The locking groove is provided on the inner wall of the installation cavity. The locking member includes a first elastic member and two locking blocks. The two locking blocks are opposite to each other and movably disposed in the installation member. The first elastic member is disposed between the two locking blocks and applies a force to the two locking blocks to cause the two locking blocks to extend out of the installation member and engage with the locking groove.

[0010] In some embodiments, the locking block is configured as at least one of the following:

[0011] One end of the locking block facing the locking groove is provided with an inclined surface, and along the direction away from the plug, the inclined surface gradually inclines away from the locking groove;

[0012] The locking block is provided with a groove, and the first elastic member extends into the groove and abuts between the groove bottoms of the two locking blocks;

[0013] The locking block is cylindrical;

[0014] The locking block includes a first section and a second section. The first section and the second section are sequentially connected along the direction away from the first elastic member. The locking block engages with the locking groove through the second section, and the diameter of the first section is greater than that of the second section.

[0015] In some embodiments, the locking groove is an arc groove; and / or, the self-locking mechanism includes at least four locking grooves, and the at least four locking grooves are arranged along the circumferential direction of the installation cavity.

[0016] In some embodiments, the at least four locking grooves are arranged continuously along the circumferential direction of the installation cavity.

[0017] In some embodiments, a disassembly and assembly hole is provided in the installation part, and the disassembly and assembly hole is located on the side of the locking part away from the plug, for a disassembly and assembly tool to be inserted to disassemble and assemble the installation part.

[0018] In some embodiments, the disassembly and assembly hole is rectangular; and / or, a limiting table is provided in the installation part, and the limiting table is located between the disassembly and assembly hole and the locking part, for stopping and limiting the disassembly and assembly tool.

[0019] In some embodiments, a receiving cavity is provided in the installation part, and the plug extends into the receiving cavity, and the hole-probing plug assembly is configured as at least one of the following:

[0020] The inner wall of the receiving cavity has a first spherical surface, and one end of the plug located in the receiving cavity includes a first sphere, and the first sphere contacts the first spherical surface;

[0021] The hole-probing plug assembly includes a second elastic member, and the second elastic member is arranged in the receiving cavity and applies a force to the plug to move the plug away from the first seat body;

[0022] One end of the plug for inserting into the probing hole includes a second sphere, and the second sphere is used to contact the second spherical surface of the probing hole;

[0023] An air guiding groove is provided at one end of the plug for extending into the probing hole, so as to guide gas to flow through one end of the plug for extending into the probing hole to cool one end of the plug for extending into the probing hole.

[0024] In some embodiments, the hole-probing plug assembly includes a second seat body, the probing hole includes a guiding section and a contact section, the guiding section and the contact section are communicated in sequence along the direction away from the installation part, the contact section is used to contact the plug, and the guiding section gradually narrows along the direction away from the installation part to guide the plug into the contact section.

[0025] In some embodiments, the installation part includes a hole-probing sleeve and a hole-probing pipe, the hole-probing sleeve is sleeved outside the hole-probing pipe, the locking part is movably arranged in the hole-probing sleeve, and the plug extends into the hole-probing pipe; and / or, a sealing member is provided between the installation part and the first seat body.

[0026] In addition, the combustion chamber provided by the present application includes a casing and a flame tube, and further includes the hole-probing plug assembly of any one of the embodiments, the first seat body is arranged on the casing, and the second seat body is arranged on the flame tube

[0027] In addition, the aeroengine provided by the present application includes the hole-probing plug assembly of any one of the embodiments.

[0028] The provided self-locking mechanism has two locking blocks that can extend under the action of the first elastic member and cooperate with the locking grooves on the inner wall of the first seat body to achieve self-locking and anti-loosening. This self-locking and anti-loosening method is simpler and more convenient compared with the traditional wire-locking or washer-locking anti-loosening methods.

[0029] The following provides a detailed description of exemplary embodiments of the present application with reference to the accompanying drawings, and other features and advantages of the present application will become clear. Description of the Drawings

[0030] To more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following briefly introduces the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0031] Figure 1 It is a schematic structural diagram of the aero-engine in this embodiment.

[0032] Figure 2 It is a schematic structural diagram of the combustion chamber in this embodiment.

[0033] Figure 3 It is an assembly schematic diagram of the borescope plug assembly in this embodiment.

[0034] Figure 4 It is a schematic structural diagram of the first seat body in this embodiment.

[0035] Figure 5 It is a schematic structural diagram of the locking block in this embodiment.

[0036] Figure 6 It is a schematic diagram of the state when the locking block is engaged with the locking groove in this embodiment.

[0037] Figure 7 It is a three-dimensional schematic diagram of the borescope sleeve in this embodiment.

[0038] Figure 8 It is a sectional view of the borescope sleeve in this embodiment.

[0039] Figure 9 It is a sectional view of the borescope tube in this embodiment.

[0040] Figure 10 It is a schematic structural diagram of the plug in this embodiment.

[0041] Figure 11 It is an assembly schematic diagram of the second seat body in this embodiment.

[0042] Figure 12It is a schematic diagram of the state when the plug floats axially in this embodiment.

[0043] Figure 13 It is a schematic diagram of the state when the plug floats radially in this embodiment.

[0044] Description of the reference numerals in the drawings:

[0045] 100, aeroengine; 10, fan; 20, compressor; 30, combustion chamber; 40, turbine; 50, flame tube; 60, fuel nozzle; 70, casing; 80, diffuser; 90, borescope plug assembly;

[0046] 1, the first seat body; 11, installation cavity; 12, sealing table; 13, corrugated teeth;

[0047] 2, installation part; 21, borescope sleeve; 22, borescope tube; 23, disassembly and assembly hole; 24, slider hole; 25, limiting table; 26, external thread; 27, internal thread; 28, accommodating cavity; 29, first spherical surface;

[0048] 3, plug; 31, first sphere; 32, second sphere; 33, first cylinder; 34, second cylinder; 35, air extraction groove;

[0049] 4, the second seat body; 41, inspection hole; 42, guiding section; 43, contact section; 44, second spherical surface;

[0050] 5, self-locking mechanism; 51, locking groove; 52, locking part; 53, locking block; 54, first elastic part; 55, first section; 56, second section; 57, inclined surface; 58, groove; 59, first spring;

[0051] 6, second elastic part; 61, second spring;

[0052] 7, sealing part; 71, sealing ring. Detailed implementation manners

[0053] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and in no way restrictive of the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present application.

[0054] For technologies, methods, and devices known to those of ordinary skill in the relevant art, they may not be discussed in detail, but where appropriate, the said technologies, methods, and devices should be regarded as part of the specification.

[0055] In the description of the present application, it should be understood that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Without additional statements, the above terms have no special meanings, and thus should not be construed as limiting the protection scope of the present application.

[0056] In addition, the technical features involved in different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0057] For safe operation, it is usually necessary to regularly conduct on-line inspections of the structural components of an aeroengine. To avoid disassembly and assembly, inspection holes are usually provided on the structural components that need on-line inspection, and a borescope is used to extend into the holes for inspection. At the same time, to prevent problems such as gas leakage through the inspection holes, a plug is usually provided for the inspection holes to block the inspection holes after the inspection is completed.

[0058] Traditional plugs are locked by lock wires or lock washers to prevent loosening. However, this anti-loosening method is relatively complex and needs to be improved.

[0059] In view of the above situation, the present application provides a borescope plug assembly, a combustion chamber and an aeroengine.

[0060] Figures 1 - 13 Exemplarily, the structures of the aeroengine, the combustion chamber and the borescope plug assembly in the present application are shown.

[0061] See Figures 1 - 13 , in the present application, the borescope plug assembly 90 includes a first seat body 1, a mounting member 2, a plug 3 and a self-locking mechanism 5. Among them, an installation cavity 11 is provided inside the first seat body 1. The mounting member 2 is inserted into the installation cavity 11. The plug 3 is arranged on the mounting member 2 and is used to be inserted into the inspection hole 41 on the second seat body 4 to block the inspection hole 41. The self-locking mechanism 5 includes a locking groove 51 and a locking member 52. The locking groove 51 is arranged on the inner wall of the installation cavity 11. The locking member 52 includes a first elastic member 54 and two locking blocks 53. The two locking blocks 53 are opposite to each other and are movably arranged in the mounting member 2. The first elastic member 54 is arranged between the two locking blocks 53 and applies a force to the two locking blocks 53 to make the two locking blocks 53 extend out of the mounting member 2 and engage with the locking groove 51.

[0062] In the above arrangement, the two locking blocks 53 can expand and contract under the action of the first elastic member 54 and engage with the locking groove 51 on the first seat body 1 to achieve self-locking and prevent loosening. This enables the borescope plug assembly 90 to have a self-locking and anti-loosening function. Compared with the traditional situation of locking and anti-loosening with lock wires or lock washers, it can effectively simplify the anti-loosening process and improve the anti-loosening efficiency.

[0063] Meanwhile, under the action of the first elastic member 54, the two locking blocks 53 are engaged with the locking grooves 51 on the first seat body 1 to perform self-locking and anti-loosening, and the anti-loosening reliability is relatively high, and the service life is also relatively long. Therefore, it is beneficial to more reliably prevent the plug from loosening.

[0064] In addition, the form of using the locking block 53 in cooperation with the locking groove 51 for self-locking and anti-loosening does not require welding and is not affected by the welding quality.

[0065] It can be seen that the provided self-locking mechanism 5 uses the form of the locking block 53 in cooperation with the locking groove 51 for self-locking and anti-loosening, and can realize a simple, efficient and reliable anti-loosening process.

[0066] See Figure 3 and Figures 5 - 6 , in some embodiments, one end of the locking block 53 facing the locking groove 51 is provided with an inclined surface 57, and along the direction away from the plug 3, the inclined surface 57 gradually inclines away from the locking groove 51. Based on this, see Figure 3 , after the locking block 53 is engaged with the locking groove 51, along the inclination direction of the inclined surface 57, a gap gradually generates between the locking block 53 and the inner wall of the installation cavity 11, and the gap gradually becomes larger. In this way, the locking block 53 can be pushed through the corresponding gap, so that the locking block 53 is away from the locking groove 51 and is no longer engaged with the locking groove 51, and the locking is released. It can be seen that the provided inclined surface 57 facilitates the release of the self-locking and anti-loosening function.

[0067] In addition, see Figure 3 , in some embodiments, the locking block 53 is provided with a groove 58, and the first elastic member 54 extends into the groove 58 and abuts between the bottoms of the grooves 58 of the two locking blocks 53. In this way, the two grooves 58 can limit and guide the first elastic member 54, which can not only prevent the first elastic member 54 from disengaging and enhance the reliability, but also guide the first elastic member 54 to deform along the telescopic direction of the locking block 53 to prevent the first elastic member 54 from deflecting and affecting the smooth realization of the self-locking function.

[0068] See Figure 5 , in some embodiments, the locking block 53 includes a first section 55 and a second section 56, the first section 55 and the second section 56 are sequentially connected along the direction away from the first elastic member 54, the locking block 53 is engaged with the locking groove 51 through the second section 56, and the diameter of the first section 55 is larger than that of the second section 56. In this case, since the diameter of the first section 55 is larger, it is beneficial to increase the contact area between the locking block 53 and the first elastic member 54, and improve the structural reliability and the self-locking and anti-loosening reliability.

[0069] In the foregoing embodiments, the shape of the locking groove 51 can be diverse. For example, it can be triangular, rectangular, or arc-shaped. Among them, when the locking groove 51 is arc-shaped, the locking groove 51 is an arc groove. In this case, the locking groove 51 is not only more beautiful and convenient to process, but also convenient to cooperate with the locking block 53 to achieve a better self-locking and anti-loosening effect.

[0070] In addition, in the foregoing embodiments, the number of the locking grooves 51 is not limited and can be a pair, two pairs, or multiple pairs (that is, at least three pairs). When the number of the locking grooves 51 is at least two pairs, the self-locking mechanism 5 includes at least four locking grooves 51. These at least four locking grooves 51 can be arranged along the circumferential direction of the installation cavity 11. In this way, the two locking blocks 53 can be engaged with the pairs of locking grooves 51 at different circumferential positions to achieve self-locking and anti-loosening at different circumferential positions, and a more flexible anti-loosening process can be realized.

[0071] Among them, when at least four locking grooves 51 are arranged along the circumferential direction of the installation cavity 11, these at least four locking grooves 51 can be arranged at intervals or continuously along the circumferential direction of the installation cavity 11. When these at least four locking grooves 51 are continuously arranged along the circumferential direction of the installation cavity 11, a corrugated tooth 13 can be formed. In this case, no matter what angular position the two locking blocks 53 are in, there is a corresponding locking groove 51 engaged with it. Therefore, the position requirement for the angle of the installation part 2 can be reduced. During the assembly process, only by putting the installation part 2 into the installation cavity 11, self-locking and anti-loosening can be achieved, and the position of the installation part 2 does not need to be specially adjusted. Therefore, the anti-loosening difficulty can be further reduced, and a more convenient and efficient anti-loosening process can be realized.

[0072] See Figure 7 and Figure 8 , in some embodiments, a disassembly and assembly hole 23 is provided in the installation part 2. The disassembly and assembly hole 23 is located on the side of the locking part 52 away from the plug 3 and is used for inserting a disassembly and assembly tool to disassemble and assemble the installation part 2. In this way, the disassembly and assembly tool can be inserted into the installation part 2 through the disassembly and assembly hole 23 to disassemble and assemble the installation part 2, which is simple and convenient. Among them, in some embodiments, the disassembly and assembly hole 23 is rectangular, so that it is convenient to realize the non-rotatable connection between the disassembly and assembly tool and the installation part 2, and it is more convenient for the disassembly and assembly tool to drive the installation part 2 to rotate together for smooth disassembly and assembly.

[0073] Continue to see Figure 7 and Figure 8 , in some embodiments, not only a disassembly and assembly hole 23 is provided in the installation part 2, but also a limiting platform 25 is provided. The limiting platform 25 is located between the disassembly and assembly hole 23 and the locking part 52 and is used for stopping and limiting the disassembly and assembly tool. In this way, during the disassembly and assembly process, the interference between the disassembly and assembly tool and the locking part 52 can be prevented, which is beneficial to realizing a more efficient disassembly and assembly process and is also beneficial to reducing the risk of damage to the locking part 52 during the disassembly and assembly process.

[0074] In addition, referring to Figure 3 , in some embodiments, a receiving cavity 28 is provided in the mounting member 2, the plug 3 extends into the receiving cavity 28, and the borescope plug assembly 90 includes a second elastic member 6. The second elastic member 6 is disposed in the receiving cavity 28 and applies a force to the plug 3 to move the plug 3 away from the first seat body 1. Based on this, under the action of the second elastic member 6, the plug 3 can achieve floating in the radial direction of the aero-engine. Thus, referring to Figure 13 , when the components where the first seat body 1 and the second seat body 4 are located have radial position deviation or creep due to reasons such as structural defects or inconsistent radial deformation, the plug 3 can move radially by compressing or releasing the second elastic member 6, so as to adapt to the corresponding radial position deviation or creep, and prevent the plug 3 from protruding excessively from the inspection hole 41 due to the corresponding radial position deviation or creep, resulting in damages such as high-temperature ablation. Since the inside of the flame tube 50 of the combustion chamber 30 is a high-temperature environment, the flame tube 50 is greatly deformed by the high temperature, while the casing 70 of the combustion chamber 30 has a small deformation amount, and the difference in the radial deformation amount between the two is large, and the problem of inconsistent deformation is more prominent. The plug 3 is more likely to extend into the flame tube 50 due to the inconsistent radial deformation amounts of the flame tube 50 and the casing 70, resulting in ablation. Therefore, the corresponding solution for radially floating the plug 3 is particularly applicable to the case where the borescope plug assembly 90 is provided on the flame tube 50.

[0075] In addition, continuing to refer to Figure 3 , in the case where the aforementioned receiving cavity 28 is provided in the mounting member 2, in some embodiments, the inner wall of the receiving cavity 28 has a first spherical surface 29, and one end of the plug 3 located in the receiving cavity 28 includes a first spherical body 31. The first spherical body 31 contacts the first spherical surface 29. In this way, on the one hand, the contact between the first spherical body 31 and the first spherical surface 29 can achieve a tight seal and effectively prevent gas leakage. On the other hand, referring to Figure 12 , it is convenient to realize the floating of the plug 3 in the axial and circumferential directions of the aero-engine by rotating the first spherical body 31, so as to prevent the plug 3 from being damaged due to stuck force caused by inconsistent deformation of the first seat body 1 and the second seat body 4, which is beneficial to extending the service life of the plug 3.

[0076] In addition, referring to Figure 3 , in some embodiments, one end of the plug 3 for inserting into the inspection hole 41 includes a second spherical body 32, and the second spherical body 32 is used to contact the second spherical surface 44 of the inspection hole 41. In this case, on the one hand, the contact between the second spherical body 32 and the second spherical surface 44 can achieve a tight seal and effectively prevent gas leakage. On the other hand, referring to Figure 12 , it is convenient to realize the floating of the plug 3 in the axial and circumferential directions of the aero-engine by rotating the second spherical body 32, so as to prevent the plug 3 from being damaged due to stuck force caused by inconsistent deformation of the positions where the first seat body 1 and the second seat body 4 are located, which is beneficial to extending the service life of the plug 3.

[0077] In particular, when the plug 3 includes both the first sphere 31 and the second sphere 32 at the same time, the plug 3 forms a double-ball-head structure, which can rotate more smoothly, change its position in the axial and circumferential directions, and flexibly adapt to the circumferential and axial position deviations caused by the inconsistent deformation of the positions of the first seat body 1 and the second seat body 4, thereby preventing jamming.

[0078] Since the inside of the flame tube 50 of the combustion chamber 30 is a high-temperature environment, the flame tube 50 is greatly deformed under the influence of high temperature, while the casing 70 has a small deformation amount. The difference in the circumferential and axial deformation amounts between the two is large, and the problem of inconsistent deformation is more prominent. The plug 3 is more likely to be jammed and damaged due to the inconsistent circumferential or axial deformation amounts of the flame tube 50 and the casing 70. Therefore, the aforementioned scheme that enables the plug 3 to float axially and circumferentially is particularly applicable to the case where the borescope plug assembly 90 is provided on the flame tube 50.

[0079] As a further improvement to the foregoing embodiments, refer to Figure 10 , an air guide groove 35 is provided at one end of the plug 3 for extending into the inspection hole 41 to guide the gas to flow through one end of the plug 3 for extending into the inspection hole 41, so as to cool one end of the plug 3 for extending into the inspection hole 41. In this way, overheating of one end of the plug 3 for extending into the inspection hole 41 can be prevented, the structural reliability of the plug 3 can be improved, and the service life of the plug 3 can be extended. Since one end of the plug 3 for extending into the inspection hole 41 is more likely to overheat when the borescope plug assembly 90 is installed on the combustion chamber 30, the scheme of providing the air guide groove 35 is particularly applicable to the case where the borescope plug assembly 90 is installed on the combustion chamber 30. Wherein, when one end of the plug 3 for extending into the inspection hole 41 includes the second sphere 32, the air guide groove 35 can be provided on the second sphere 32 to achieve cooling of the corresponding second sphere 32.

[0080] In some embodiments, the borescope plug assembly 90 includes the second seat body 4, the inspection hole 41 includes a guiding section 42 and a contact section 43, the guiding section 42 and the contact section 43 are sequentially communicated along the direction away from the mounting member 2, the contact section 43 is used for contacting the plug 3, and the guiding section 42 gradually narrows along the direction away from the mounting member 2 to guide the plug 3 into the contact section 43. In this way, under the guiding action of the guiding section 42, the plug 3 can more conveniently extend into the contact section 43, contact the contact section 43, and perform plugging and sealing.

[0081] In the foregoing embodiments, the mounting member 2 can be of an integral structure or a split structure. For example, refer to Figure 3 and Figures 7 - 9, in some embodiments, the mounting member 2 includes a borescope sleeve 21 and a borescope tube 22. The borescope sleeve 21 is sleeved outside the borescope tube 22. The locking member 52 is disposed inside the borescope sleeve 21, and the plug 3 extends into the borescope tube 22. With this structural form, the assembly is more convenient. In particular, when the borescope plug assembly 90 includes the aforementioned locking member 52 and the second elastic member 6 at the same time, the locking member 52 and the second elastic member 6 can be conveniently installed into the borescope sleeve 21 and the borescope tube 22 respectively, realizing the installation of the locking member 52 and the second elastic member 6 inside the mounting member 2.

[0082] In addition, as a further improvement to the foregoing embodiments, refer to Figure 3 , a sealing member 7 is provided between the mounting member 2 and the first seat body 1. In this way, a seal can be formed between the mounting member 2 and the first seat body 1, effectively preventing gas from leaking from the corresponding position, so as to avoid affecting flight safety due to gas leakage.

[0083] The borescope plug assemblies 90 of the foregoing embodiments can be applied to various parts of the aeroengine 100 that need to be inspected by borescope, such as the parts on the rotor where the blades need to be inspected by borescope, or the flame tube 50 of the combustion chamber 30. Among them, it can be particularly applied to the flame tube 50 where the environment is very harsh. When applied to the flame tube 50, the first seat body 1 and the second seat body 4 can be respectively disposed on the casing 70 and the flame tube 50.

[0084] Next, in combination with the Figures 1 - 13 illustrated embodiment, the present application will be further introduced.

[0085] Figure 1 shows the structure of the aeroengine 100 in this embodiment. As Figure 1 shown, in this embodiment, the aeroengine 100 includes a fan 10, a compressor 20, a combustion chamber 30, and a turbine 40. The fan 10, the compressor 20, the combustion chamber 30, and the turbine 40 are arranged in sequence along the direction in which the gas flows into the aeroengine 100 ( Figure 1 the left-right direction in

[0086] which is also the axial direction of the aeroengine 100). During operation, the compressor 20 compresses air, which is burned in the combustion chamber 30 to do work on the turbine 40, converting the chemical energy of the fuel into the mechanical energy of the turbine 40. The turbine 40 discharges the combustion gas and drives the fan 10 to generate thrust. Figure 2 shows the structure of the combustion chamber 30. As Figure 2As shown, in this embodiment, the combustion chamber 30 includes a flame tube 50, a fuel nozzle 60, a casing 70, a diffuser 80, and a borescope plug assembly 90. During operation, the air flow compressed by the compressor 20 enters the flame tube 50 after deceleration and pressure increase through the diffuser 80, and mixes with the fuel ejected from the fuel nozzle 60, thereby achieving combustion. The environments where the flame tube 50 and the fuel nozzle 60 are located are extremely harsh, and regular in-flight borescope inspections are required. Therefore, as Figure 2 shown, in this embodiment, a borescope plug assembly 90 is provided on the flame tube 50 to block the inspection holes 41 on the flame tube 50.

[0087] Figures 3 - 13 The structure of the borescope plug assembly 90 is further shown.

[0088] Among them, Figure 3 a schematic assembly diagram of the borescope plug assembly 90 is shown. As Figure 3 shown, in this embodiment, the borescope plug assembly 90 includes a first seat body 1, a mounting member 2, a plug 3, a second seat body 4, a self-locking mechanism 5, a second spring 61, and a sealing ring 71. The first seat body 1 and the second seat body 4 are respectively welded to the casing 70 and the flame tube 50, and become integral with the casing 70 and the flame tube 50. The mounting member 2 is disposed on the first seat body 1 and is connected to the inner wall of the first seat body 1, and includes a borescope sleeve 21 and a borescope tube 22. The plug 3 is disposed on the mounting member 2, specifically disposed in the borescope tube 22, and is used to block the inspection hole 41 on the second seat body 4. The self-locking mechanism 5 includes a corrugated tooth 13 and a locking member 52. The corrugated tooth 13 is disposed on the inner wall of the first seat body 1, and includes a plurality of locking grooves 51 that surround the inner wall of the first seat body 1 for one full circle and are continuously arranged in the circumferential direction of the inner wall of the first seat body 1. The locking member 52 is disposed inside the mounting member 2, and includes a first spring 59 and two locking blocks 53. The two locking blocks 53 are installed on the borescope sleeve 21 and are telescopically moved through the first spring 59 serving as a first elastic member 54, and cooperate with the corrugated tooth 13 on the inner wall of the first seat body 1 to generate damping to achieve anti-loosening. The second spring 61 is disposed in the borescope tube 22 and abuts against the plug 3, so that the plug 3 can radially float. In this way, when the flame tube 50 moves in the radial direction ( Figure 1 and Figure 3 the up and down direction) of the aeroengine 100, the second spring 61 expands and contracts, and the plug 3 can achieve floating, keeping the plug 3 in contact with the second seat body 4 without leakage. Both ends of the plug 3 are spherical head structures. The upper spherical head structure is a first sphere 31, which cooperates with the borescope tube 22, and the lower spherical structure is a second sphere 32, which cooperates with the second seat body 4. By rotating the spherical head structures at both ends, the plug 3 can move in the axial direction ( Figure 1 and Figure 3 the left and right direction) or the circumferential direction ( Figure 1 and Figure 3float in the inner and outer directions to prevent the plug 3 from getting stuck and damaged. The sealing ring 71 serves as the seal 7 and is arranged between the first seat body 1 and the mounting member 2 for sealing to prevent gas leakage. In this embodiment, the sealing ring 71 is a C-shaped sealing ring.

[0089] Figure 4 Further shows the structure of the first seat body 1. As Figure 4 shown, in this embodiment, the first seat body 1 is generally cylindrical, its axis is along the radial direction of the aeroengine 100, and its interior is provided with a mounting cavity 11. On the inner wall of the mounting cavity 11, there are successively arranged corrugated teeth 13, internal threads 27 and a sealing platform 12 from top to bottom (that is, from the outer side to the inner side of the radial direction of the aeroengine 100). The corrugated teeth 13 are used to cooperate with the locking block 53 to achieve the self-locking and anti-loosening function. It surrounds the inner wall of the mounting cavity 11 for one week and includes a plurality of locking grooves 51. These plurality of locking grooves 51 are continuously arranged without intervals between each other, and these plurality of locking grooves 51 are all arc-shaped, being arc-shaped grooves. The internal threads 27 below the corrugated teeth 13 are used to cooperate with the external threads 26 on the borescope sleeve 21 to achieve the threaded connection between the borescope sleeve 21 and the first seat body 1, so that the mounting member 2 is detachably mounted on the first seat body 1. The sealing platform 12 is used to mount the sealing ring 71.

[0090] Figure 5 Further shows the structure of the locking block 53. As Figure 5 shown, in this embodiment, the locking block 53 is cylindrical and includes a first section 55 and a second section 56. The diameter of the first section 55 is larger than that of the second section 56 and is connected to the end close to the first spring 59 for abutting against the first spring 59 to drive the second section 56 to expand and contract under the action of the first spring 59. From Figure 3 and Figure 6 it can be seen that in this embodiment, a groove 58 is provided at the end of the first section 55 away from the second section 56. The first spring 59 extends into the grooves 58 of two relatively arranged locking blocks 53 to apply an elastic force to the two locking blocks 53, so that the two locking blocks 53 can move in the mounting member 2 to achieve expansion and contraction. The second section 56 is connected to the end of the first section 55 close to the corrugated teeth 13 and cooperates with the corrugated teeth 13 on the first seat body 1 to achieve damping anti-loosening, as Figure 6 shown. Refer to Figure 5 , and combined with Figure 3 it can be seen that in this embodiment, the end face of the second section 56 is configured as an inclined surface 57. The inclined surface 57 gradually inclines towards the direction close to the first section 55 along the direction away from the plug 3 (which is also the direction from the inner side to the outer side of the radial direction of the aeroengine). In other words, in the radial direction of the aeroengine 100, the outer end of the inclined surface 57 is closer to the first section 55 than the inner end. Thus, as Figure 3As shown, when the locking block 53 is engaged with the corrugated tooth 13, the gap between the locking block 53 and the corrugated tooth 13 increases from zero to one along the direction from the radial inside to the outside of the aircraft engine, and gradually increases. This makes it convenient to push the locking block 53 and the corrugated tooth 13 to disengage through the corresponding gap to release the self-locking, so as to meet other needs such as disassembly.

[0091] Figure 7 and Figure 8 The structure of the bore probe sleeve 21 is shown. Figure 7 and Figure 8 As shown, in this embodiment, the bore probe sleeve 21 is cylindrical, and is coaxially arranged with the first seat body 1 in the mounting cavity 11 of the first seat body 1, and has a disassembly hole 23, a stopper 25, a slider hole 24, an external thread 26 and an internal thread 27. Among them, the disassembly hole 23 is arranged inside the bore probe sleeve 21 and is located at the end of the bore probe sleeve 21 away from the plug 3. It is rectangular, and its depth direction is along the axial direction of the bore probe sleeve 21 (also the radial direction of the aircraft engine 100), and is used for inserting a disassembly tool for disassembly. The slider hole 24 is used to assemble the locking block 53, and its axial direction is along the radial direction of the bore probe sleeve 21, parallel to the axial direction of the aircraft engine 100, and adapted to the locking block 53 including the first section 55 and the second section 56. The slider hole 24 includes two hole sections with different diameters, which are respectively adapted to the first section 55 and the second section 56. At the same time, corresponding to the locking member 52 including two locking blocks 53, two slider holes 24 opposite to each other are provided on the bore probe sleeve 21 to accommodate the two locking blocks 53 and make the two locking blocks 53 opposite to each other. The limit platform 25 is located between the slider hole 24 and the disassembly hole 23, and is used to stop the disassembly tool to prevent the disassembly tool from interfering with the first spring 59 and the locking block 53, causing damage to the first spring 59 and the locking block 53. The external thread 26 on the bore probe sleeve 21 is arranged on the outer wall of the lower end (i.e., the end close to the plug 3) of the bore probe sleeve 21, and is used to cooperate with the internal thread 27 on the first seat body 1 to achieve the threaded connection between the bore probe sleeve 21 and the first seat body 1. The internal thread 27 on the bore probe sleeve 21 is arranged on the inner wall of the lower end of the bore probe sleeve 21, and is used to cooperate with the external thread 26 on the bore probe tube 22 to achieve the threaded connection between the bore probe tube 22 and the bore probe sleeve 21.

[0092] Figure 9 The structure of the hole probe tube 22 is shown. Figure 9 As shown, in this embodiment, the bore probe tube 22 is roughly cylindrical, with its axial direction along the radial direction of the aircraft engine 100, and the upper end is connected to the bore probe sleeve 21 through an external thread 26, and the lower end is configured to be a spherical end, and the inner surface of the corresponding spherical end constitutes a first spherical surface 29, which is used to cooperate with the first sphere 31 of the plug 3 to realize the rotation of the plug 3.

[0093] Figure 10 The structure of the plug 3 is further shown. Figure 10As shown, in this embodiment, the plug 3 includes a first cylinder 33, a first sphere 31, a second cylinder 34, and a second sphere 32 that are connected in sequence. The first cylinder 33 is cylindrical and is used for the second spring 61 to be sleeved thereon. The second spring 61 is sleeved on the first cylinder 33 and abuts against the first sphere 31, so as to telescopically expand and contract along the radial direction of the aeroengine 100 under the guidance of the first cylinder 33, apply an elastic force to the first sphere 31, and enable the plug 3 to perform radial floating. The first sphere 31 is hemispherical and protrudes radially of the plug 3 relative to the first cylinder 33 and the second cylinder 34, and cooperates with the first spherical surface 29 on the borescope 22 to realize the floating of the plug 3 in the circumferential and axial directions of the aeroengine 100. The second cylinder 34 is cylindrical and is connected between the first sphere 31 and the second sphere 32. The second sphere 32 is almost a complete sphere and protrudes radially of the plug 3 relative to the second cylinder 34, and is used to cooperate with the probe hole 41 on the second seat body 4 to realize the floating in the circumferential and axial directions of the aeroengine 100. As can be seen from Figure 10 it that, in this embodiment, a plurality of air bleeding grooves 35 are provided on the outer surface of the second sphere 32. These a plurality of air bleeding grooves 35 are evenly arranged along the circumferential direction of the second sphere 32, and each air bleeding groove 35 extends from one end of the second sphere 32 close to the second cylinder 34 to the end far from the second cylinder 34, so that the cooling air can flow through the second sphere 32 along the air bleeding grooves 35 to realize the cooling of the second sphere 32.

[0094] Figure 11 is the assembly schematic diagram of the second seat body 4. As Figure 11 shown, the second seat body 4 is welded to the flame tube 50 and includes a guiding section 42 and a contact section 43. Along the direction from the radial outer side to the radial inner side of the aeroengine 100, the guiding section 42 and the contact section 43 are communicated in sequence, and the guiding section 42 is in a tapered shape that gradually shrinks, and the contact section 43 includes a second spherical surface 44 adjacent to the guiding section 42. In this way, the guiding section 42 can guide the plug 3 to quickly reach the contact section 43 and contact the second spherical surface 44 to realize sealing and the rotation of the plug 3.

[0095] Based on the foregoing structural settings, in this embodiment, the cooperation of the two locking blocks 53, the first spring 59, and the corrugated teeth 13 can effectively prevent the plug 3 from loosening during operation and disengaging from the first seat body 1, and enhance the setting reliability of the plug 3. The corresponding self-locking anti-loosening structure is simple, convenient, effective, and reliable. At the same time, the corresponding self-locking anti-loosening structure can be visibly marked and observed the position after fastening, which is convenient to confirm whether it is loose.

[0096] In addition, the plug 3 is fitted with the first spherical surface 29 and the second spherical surface 44 through double ball heads, and can float in the circumferential and axial directions of the aeroengine 100, effectively solving the problem of inconsistent deformation between the combustion chamber 50 and the casing 70 during operation, and preventing the plug 3 from being damaged due to forced jamming. Among them, the state of the plug during axial floating is as shown in Figure 12 shown.

[0097] Meanwhile, under the action of the second spring 61, the plug 3 can float in the radial direction of the aeroengine 100 as shown in Figure 13 shown, effectively solving the problems of welding collapse of the combustion chamber 50 and radial position deviation and creep of the combustion chamber 50 and the casing 70 caused by mismatched radial deformation between the combustion chamber 50 and the casing 70, which may lead to the plug 3 extending into the inner wall of the combustion chamber 50 and being ablated. The service life of the plug 3 can be extended, and the flight safety can be improved.

[0098] The foregoing are only exemplary embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included within the protection scope of the present application.

Claims

1. A borescope plug component (90), characterized in that, Comprising: A first body (1) with an installation cavity (11) provided inside; An installation member (2) inserted into the installation cavity (11); A plug (3) provided on the installation member (2) and used for inserting into a probe hole (41) on a second body (4) to block the probe hole (41); And A self-locking mechanism (5) including a locking groove (51) and a locking member (52). The locking groove (51) is provided on the inner wall of the installation cavity (11). The locking member (52) includes a first elastic member (54) and two locking blocks (53). The two locking blocks (53) are arranged opposite to each other and movably disposed in the installation member (2). The first elastic member (54) is disposed between the two locking blocks (53) and applies a force to the two locking blocks (53) to make the two locking blocks (53) extend out of the installation member (2) and engage with the locking groove (51).

2. The borescope plugging head assembly (90) according to claim 1, wherein, The locking block (53) is configured as at least one of the following: One end of the locking block (53) facing the locking groove (51) is provided with an inclined surface (57). Along the direction away from the plug (3), the inclined surface (57) gradually inclines away from the locking groove (51); The locking block (53) is provided with a groove (58). The first elastic member (54) extends into the groove (58) and abuts between the bottoms of the grooves (58) of the two locking blocks (53); The locking block (53) is cylindrical; The locking block (53) includes a first section (55) and a second section (56). The first section (55) and the second section (56) are sequentially connected along the direction away from the first elastic member (54). The locking block (53) engages with the locking groove (51) through the second section (56), and the diameter of the first section (55) is larger than that of the second section (56).

3. The borescope plugging head assembly (90) according to claim 1, characterized in that, The locking groove (51) is an arc-shaped groove; and / or, the self-locking mechanism (5) includes at least four locking grooves (51), and the at least four locking grooves (51) are arranged along the circumferential direction of the installation cavity (11).

4. The borescope plugging head assembly (90) according to claim 3, characterized in that, The at least four locking grooves (51) are arranged continuously along the circumferential direction of the installation cavity (11).

5. The borescope plugging head assembly (90) according to claim 1, characterized in that, An assembly and disassembly hole (23) is provided inside the installation member (2). The assembly and disassembly hole (23) is located on the side of the locking member (52) away from the plug (3) and is used for inserting a disassembly and assembly tool to assemble and disassemble the installation member (2).

6. The borescope plugging head assembly (90) according to claim 5, characterized in that, The assembly and disassembly hole (23) is rectangular; and / or, a limiting platform (25) is provided inside the installation member (2). The limiting platform (25) is located between the assembly and disassembly hole (23) and the locking member (52) and is used for stopping and limiting the disassembly and assembly tool.

7. The borescope plugging head assembly (90) according to any one of claims 1-6, characterized in that, A receiving cavity (28) is provided inside the installation member (2). The plug (3) extends into the receiving cavity (28). And the hole probe plug assembly (90) is configured as at least one of the following: The inner wall of the accommodation cavity (28) has a first spherical surface (29). One end of the plug (3) located in the accommodation cavity (28) includes a first spherical body (31), and the first spherical body (31) is in contact with the first spherical surface (29). The hole-probing plug assembly (90) includes a second elastic member (6). The second elastic member (6) is arranged in the accommodation cavity (28) and applies a force to the plug (3) to move the plug (3) away from the first seat body (1). One end of the plug (3) for inserting into the probing hole (41) includes a second spherical body (32), and the second spherical body (32) is used for contacting the second spherical surface (44) of the probing hole (41). An air guiding groove (35) is provided at one end of the plug (3) for extending into the probing hole (41) to guide gas to flow through one end of the plug (3) for extending into the probing hole (41) and cool one end of the plug (3) for extending into the probing hole (41).

8. The borescope plugging head assembly (90) according to any one of claims 1-6, characterized in that, The hole-probing plug assembly (90) includes the second seat body (4). The probing hole (41) includes a guiding section (42) and a contact section (43). The guiding section (42) and the contact section (43) are sequentially communicated along the direction away from the mounting member (2). The contact section (43) is used for contacting the plug (3), and the guiding section (42) gradually narrows along the direction away from the mounting member (2) to guide the plug (3) into the contact section (43).

9. The borescope plugging head assembly (90) according to any one of claims 1-6, characterized in that, The mounting member (2) includes a hole-probing sleeve (21) and a hole-probing pipe (22). The hole-probing sleeve (21) is sleeved outside the hole-probing pipe (22). The locking member (52) is movably arranged in the hole-probing sleeve (21), and the plug (3) extends into the hole-probing pipe (22); and / or, a sealing member (7) is provided between the mounting member (2) and the first seat body (1).

10. A combustion chamber (30) comprising a casing (70) and a flame tube (50), characterized in that, Including the hole-probing plug assembly (90) according to any one of claims 1-9, the first seat body (1) is arranged on the engine casing (70), and the second seat body (4) is arranged on the combustion chamber liner (50).

11. An aeroengine (100), characterized in that, Including the hole-probing plug assembly (90) according to any one of claims 1-9.

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