Borehole plugging device for aircraft engines

Abstract

The present invention relates to a borehole probe plugging device for aircraft engines. The borehole probe plugging device includes a housing, a plug, a locking pin, an elastic member, a first self-locking ratchet, a second self-locking ratchet and a sealing assembly; wherein the housing includes a housing mounting keyway and a threaded hole arranged on the upper portion thereof; the plug includes an upper threaded portion, a plug mounting keyway, a sealing groove and a lower threaded portion; the locking pin includes a locking pin mounting key arranged on the upper portion thereof and a locking pin radial protrusion arranged below the locking pin mounting key; the first self-locking ratchet includes a ratchet mounting key arranged on the upper portion thereof, a ratchet radial protrusion arranged near the lower portion thereof and a first serration structure arranged on the lower portion thereof; the second self-locking ratchet includes a second serration structure arranged on the upper portion thereof; and the sealing assembly includes a metal C-shaped sealing ring. The present invention can achieve the following beneficial technical effects: simple structure, convenient disassembly and assembly; can avoid the decrease in efficiency caused by air leakage from high-pressure components of the engine.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, in particular to a borehole plugging device for an aeroengine. Background Art

[0002] The aircraft engine is the power part of the aircraft and also the heart of the aircraft. The performance of the engine will directly affect the entire aircraft. Therefore, it is very necessary to regularly check the surface damage of the internal structure of the aircraft engine. In addition, for high-pressure components, during the operation of the engine, the effective sealing of the borescope plug can avoid the loss of engine efficiency caused by leakage. At present, it is usually carried out through borescope inspection, that is, with the help of an endoscope, the internal structure of the engine is inspected to detect damage in time to evaluate the overall performance of the engine. The borescope inspection interface is usually arranged directly on the engine casing structure, and its position is convenient for maintenance without disassembling the engine hardware. Usually, the outside of the engine is full of external hardware, such as the gearbox, fuel main, air duct, etc., which makes borescope inspection complicated.

[0003] The current bore probe plug uses a lock wire, has a complex structure, and does not have a sealing function. This makes it inconvenient to operate during frequent disassembly; in addition, the lack of sealing measures can easily cause different degrees of secondary flow to enter the main channel, directly affecting the performance of the engine and causing a certain impact on the safety of the aircraft. Summary of the invention

[0004] An object of the present invention is to provide a bore plugging device for an aircraft engine, which can solve the problems existing in the prior art, has a simple structure and is convenient for disassembly and assembly; and can avoid the decrease in efficiency caused by air leakage from the high-pressure components of the engine.

[0005] The above objects of the present invention are achieved by a bore probe plugging device for an aircraft engine, the bore probe plugging device for an aircraft engine comprising a housing, a plug, a locking pin, an elastic member, a first self-locking ratchet, a second self-locking ratchet and a sealing assembly;

[0006] Wherein, the housing includes a housing mounting keyway and a threaded hole arranged on the upper portion thereof;

[0007] The plug includes an upper threaded portion, a plug mounting keyway, a sealing groove and a lower threaded portion, wherein the upper threaded portion is arranged at the upper portion of the plug and is used to engage with the threaded hole of the housing, the plug mounting keyway is opposite to the housing mounting keyway, the sealing groove is arranged near the middle portion of the plug and is used to accommodate the sealing assembly, and the lower threaded portion is arranged below the sealing groove and is used to engage with the engine casing of the aircraft engine;

[0008] The lock pin includes a lock pin installation key disposed on its upper portion and a lock pin radial protrusion disposed below the lock pin installation key, the lock pin installation key is used to be inserted into the housing installation key slot and the plug installation key slot, and the lower end surface of the lock pin radial protrusion is used to abut against the top of the elastic member;

[0009] The first self-locking ratchet comprises a ratchet installation key arranged on its upper part, a ratchet radial protrusion arranged near its lower part, and a first sawtooth structure arranged on its lower part, wherein the ratchet installation key is used to be inserted into the plug installation key slot, and the upper end surface of the ratchet radial protrusion is used to abut against the bottom of the elastic member;

[0010] Wherein, the second self-locking ratchet comprises a second sawtooth structure arranged on an upper portion thereof, and the second sawtooth structure is used to engage with the first sawtooth structure;

[0011] Wherein, the sealing assembly includes a metal C-shaped sealing ring.

[0012] According to the above technical scheme, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: simple structure and convenient disassembly and assembly; and can avoid the decrease in efficiency caused by air leakage from the high-pressure components of the engine.

[0013] Specifically, the present invention proposes a boresight plugging device for an aircraft engine. At the threaded connection between the boresight plugging device and the engine casing (such as a casing), the sealing effect of the metal C-type sealing ring is used to ensure the sealing of the boresight plugging device during engine operation, thereby avoiding a decrease in efficiency due to air leakage from the engine's high-pressure components. The boresight plugging device is composed of a plug, a shell, a locking pin, an elastic member, a self-locking ratchet and a metal C-type sealing ring. The self-locking ratchet, the elastic member and the locking pin are inserted into the plug structure from the upper end, and then the shell is connected to the structure by threads to complete the assembly, thereby ensuring a simple assembly structure. A serrated structure is designed in the self-locking ratchet structure of the boresight plugging device to cooperate and achieve a self-locking function.

[0014] Preferably, the sealing assembly further comprises a metal gasket arranged radially inwardly of the metal C-shaped sealing ring, and the cross section of the metal gasket is a straight line.

[0015] According to the above technical scheme, the borehole probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: the combination of the metal C-shaped sealing ring and the metal I-shaped gasket can make the sealing effect of the sealing assembly better, and after the borehole probe plug device is removed from the aircraft engine, the sealing assembly can naturally remain in the plug sealing groove, avoiding subsequent falling and loss and saving subsequent assembly steps.

[0016] Preferably, the ratio of the outer diameter of the metal gasket to the outer diameter of the metal C-shaped sealing ring is in the range of 0.91-0.93.

[0017] According to the above technical scheme, the borehole probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the appropriate gasket / sealing ring outer diameter ratio range, the sealing effect of the sealing assembly can be better, and after the borehole probe plug device is removed from the aircraft engine, the sealing assembly can remain more naturally in the plug sealing groove, avoiding subsequent falling and loss and saving subsequent assembly steps.

[0018] Preferably, the plug further comprises a mounting groove disposed on the top thereof for engaging with a corresponding mounting tool.

[0019] According to the above technical solution, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: it is convenient to use conventional installation tools for disassembly and assembly.

[0020] Preferably, the locking pin further includes an annular portion disposed below the radial protrusion of the locking pin.

[0021] According to the above technical solution, the bore probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: the annular portion can be combined with the shell to better define the space for accommodating the elastic member.

[0022] Preferably, the first self-locking ratchet further comprises a cylindrical portion arranged on an upper portion thereof, and the ratchet mounting key is arranged on a radially inner side of the cylindrical portion.

[0023] According to the above technical scheme, the bore plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the cylindrical portion can be combined with the shell to better define the space for accommodating the elastic member, and the ratchet mounting key can be firmly set on the first self-locking ratchet.

[0024] Preferably, the second self-locking ratchet further includes an anti-rotation structure disposed at a lower portion thereof.

[0025] According to the above technical scheme, the borehole probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the anti-rotation structure can prevent the borehole probe plugging device from rotating relative to the engine casing, thereby better achieving the sealing effect.

[0026] Preferably, the anti-rotation structure is a recess for engaging with a corresponding boss provided on the engine housing.

[0027] According to the above technical solution, the boresight plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the recess / boss type anti-rotation structure, the boresight plug device can be better prevented from rotating relative to the engine casing.

[0028] Preferably, the housing further comprises a cylindrical extension portion disposed at a lower portion thereof.

[0029] According to the above technical solution, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the cylindrical extension portion can better define the space for accommodating the elastic member.

[0030] Preferably, the ratio of the height of the housing mounting keyway to the total height of the housing is in the range of 0.15-0.25.

[0031] According to the above technical scheme, the borehole plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the appropriate shell installation keyway height / shell total height ratio range, the borehole plugging device can be assembled more conveniently. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic cross-sectional view of a bore probe plugging device for an aircraft engine according to an embodiment of the present invention.

[0033] Figure 2 It is a schematic stereoscopic diagram of a shell in a borehole plugging device for an aircraft engine according to an embodiment of the present invention.

[0034] Figure 3 It is a schematic stereoscopic diagram of a plug in a borehole plugging device for an aircraft engine according to an embodiment of the present invention.

[0035] Figure 4 It is a schematic stereoscopic diagram of a locking pin in a borehole plugging device for an aircraft engine according to an embodiment of the present invention.

[0036] Figure 5 It is a schematic stereoscopic diagram of a first self-locking ratchet in a bore probe plugging device for an aircraft engine according to an embodiment of the present invention.

[0037] Figure 6 It is a schematic stereoscopic diagram of a second self-locking ratchet in a bore probe plugging device for an aircraft engine according to an embodiment of the present invention.

[0038] Figure 7 It is a schematic stereoscopic diagram of a sealing assembly in a borehole plugging device for an aircraft engine according to an embodiment of the present invention.

[0039] Figure 8 The present invention is a schematic assembly diagram of a bore probe plugging device for an aircraft engine according to an embodiment of the present invention.

[0040] Reference numerals list

[0041] 1. Shell;

[0042] 2. Plug;

[0043] 3. Lock pin;

[0044] 4. Spring;

[0045] 5. The first self-locking ratchet;

[0046] 6. Second self-locking ratchet;

[0047] 7. Sealing components;

[0048] 101, housing mounting keyway;

[0049] 102. Threaded hole;

[0050] 103, cylindrical extension;

[0051] 201, upper threaded portion;

[0052] 202, plug installation keyway;

[0053] 203, sealing groove;

[0054] 204, lower threaded portion;

[0055] 205, mounting slot;

[0056] 301, radial protrusion of the lock pin;

[0057] 302, lock pin installation key;

[0058] 303, annular part;

[0059] 501, ratchet mounting key;

[0060] 502, radial protrusion of ratchet;

[0061] 503, first sawtooth structure;

[0062] 504. Cylindrical part;

[0063] 601, second sawtooth structure;

[0064] 602, anti-rotation structure;

[0065] 701, metal C-type sealing ring;

[0066] 702, metal washers;

[0067] 801, sealing surface;

[0068] 802. Engine casing. DETAILED DESCRIPTION

[0069] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to be concise and clear, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means, and should not be understood as insufficient content of this disclosure.

[0070] Unless otherwise defined, the technical or scientific terms used in the claims and the specification shall have the usual meaning understood by persons with ordinary skills in the technical field to which the invention belongs. The words "first", "second" and similar words used in the patent application specification and the claims of the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "One" or "one" and other similar words do not indicate a quantitative limitation, but indicate the existence of at least one. "Include" or "comprises" and other similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalent elements, and do not exclude other elements or objects. "Connected" or "connected" and other similar words are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0071] As the name suggests, the term "borescope plugging device" refers to a device that is frequently disassembled and assembled during the borescope inspection of aircraft engines to play a plugging role.

[0072] Figure 1 It is a schematic cross-sectional view of a bore probe plugging device for an aircraft engine according to an embodiment of the present invention. Figure 2 It is a schematic stereoscopic diagram of a shell in a borehole plugging device for an aircraft engine according to an embodiment of the present invention. Figure 3 It is a schematic stereoscopic diagram of a plug in a borehole plugging device for an aircraft engine according to an embodiment of the present invention. Figure 4 It is a schematic stereoscopic diagram of a locking pin in a borehole plugging device for an aircraft engine according to an embodiment of the present invention. Figure 5 It is a schematic stereoscopic diagram of a first self-locking ratchet in a bore probe plugging device for an aircraft engine according to an embodiment of the present invention. Figure 6It is a schematic stereoscopic diagram of a second self-locking ratchet in a bore probe plugging device for an aircraft engine according to an embodiment of the present invention. Figure 7 It is a schematic stereoscopic diagram of a sealing assembly in a borehole plugging device for an aircraft engine according to an embodiment of the present invention. Figure 8 The present invention is a schematic assembly diagram of a bore probe plugging device for an aircraft engine according to an embodiment of the present invention.

[0073] like Figure 1 — Figure 8 As shown, according to one embodiment of the present invention, a bore probe plug device for an aircraft engine comprises a housing 1, a plug 2, a locking pin 3, an elastic member (such as a spring 4), a first self-locking ratchet 5, a second self-locking ratchet 6 and a sealing assembly 7;

[0074] The housing 1 includes a housing mounting keyway 101 and a threaded hole 102 disposed on the upper portion thereof;

[0075] The plug 2 includes an upper threaded portion 201, a plug mounting keyway 202, a sealing groove 203 and a lower threaded portion 204. The upper threaded portion 201 is arranged at the upper portion of the plug 2 and is used to engage with the threaded hole 102 of the housing 1. The plug mounting keyway 202 is opposite to the housing mounting keyway 101. The sealing groove 203 is arranged near the middle of the plug 2 and is used to accommodate the sealing assembly 7. The lower threaded portion 204 is arranged below the sealing groove 203 and is used to engage with the engine casing 802 of the aircraft engine.

[0076] The lock pin 3 includes a lock pin installation key 302 disposed on the upper portion thereof and a lock pin radial protrusion 301 disposed below the lock pin installation key 302. The lock pin installation key 302 is used to be inserted into the housing installation key slot 101 and the plug installation key slot 202. The lower end surface of the lock pin radial protrusion 301 is used to abut against the top of the elastic member.

[0077] The first self-locking ratchet 5 includes a ratchet installation key 501 disposed on the upper portion thereof, a ratchet radial protrusion 502 disposed near the lower portion thereof, and a first serration structure 503 disposed on the lower portion thereof. The ratchet installation key 501 is used to be inserted into the plug installation key slot 202, and the upper end surface of the ratchet radial protrusion 502 is used to abut against the bottom of the elastic member.

[0078] The second self-locking ratchet 6 includes a second sawtooth structure 601 disposed on the upper portion thereof, and the second sawtooth structure 601 is used to mesh with the first sawtooth structure 503;

[0079] The sealing assembly 7 includes a metal C-shaped sealing ring 701 .

[0080] According to the above technical scheme, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: simple structure and convenient disassembly and assembly; and can avoid the decrease in efficiency caused by air leakage from the high-pressure components of the engine.

[0081] Specifically, the present invention proposes a boresight plugging device for an aircraft engine. At the threaded connection between the boresight plugging device and the engine casing (such as a casing), the sealing effect of the metal C-type sealing ring is used to ensure the sealing of the boresight plugging device during engine operation, thereby avoiding a decrease in efficiency due to air leakage from the engine's high-pressure components. The boresight plugging device is composed of a plug, a shell, a locking pin, an elastic member, a self-locking ratchet and a metal C-type sealing ring. The self-locking ratchet, the elastic member and the locking pin are inserted into the plug structure from the upper end, and then the shell is connected to the structure by threads to complete the assembly, thereby ensuring a simple assembly structure. A serrated structure is designed in the self-locking ratchet structure of the boresight plugging device to cooperate and achieve a self-locking function.

[0082] More specifically, a metal C-shaped sealing ring structure is used at the corresponding plug sealing surface. Through the elastic deformation of the metal C-shaped sealing ring structure, during the compression process, the metal C-shaped sealing ring and the sealing surface are tightly combined in a line sealing manner, thereby ensuring the sealing of the borehole probe plug during engine operation and avoiding efficiency loss due to air leakage from the engine's high-pressure components. The borehole probe plug device itself has a simple structure, is easy to assemble, and can achieve a self-locking effect, thereby shortening the time for frequent disassembly and assembly of the borehole probe plug on the route and reducing the cost of regular inspections.

[0083] In some embodiments, Figure 1 — Figure 3 As shown, the shell mounting keyway 101 extends along the longitudinal direction of the shell 1 (i.e., the longitudinal direction of the borehole probe plug device); the plug mounting keyway 202 extends along the longitudinal direction of the plug 2 (i.e., the longitudinal direction of the borehole probe plug device); and the sealing groove 203 extends along the transverse direction of the plug 2 (i.e., the transverse direction of the borehole probe plug device).

[0084] In some embodiments, Figure 4 As shown, the locking pin installation key 302 extends along the longitudinal direction of the locking pin 3 (ie, the longitudinal direction of the bore probe plug device); Figure 5 As shown, the ratchet installation key 501 extends along the longitudinal direction of the first self-locking ratchet 5 (i.e., the longitudinal direction of the bore probe plug device);

[0085] In some embodiments, Figure 7 As shown, the sealing assembly 7 further includes a metal gasket 702 disposed radially inwardly of the metal C-shaped sealing ring 701 , and the cross section of the metal gasket 702 is a straight line shape.

[0086] According to the above technical scheme, the borehole probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: the combination of the metal C-shaped sealing ring 701 and the metal I-shaped gasket can make the sealing effect of the sealing component 7 better, and after the borehole probe plug device is removed from the aircraft engine, the sealing component 7 can naturally remain in the plug sealing groove 203, avoiding subsequent falling and loss and saving subsequent assembly steps.

[0087] In some embodiments, Figure 7 As shown, the ratio of the outer diameter of the metal gasket 702 to the outer diameter of the metal C-shaped sealing ring 701 is in the range of 0.91-0.93.

[0088] According to the above technical scheme, the borehole probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the appropriate gasket / sealing ring outer diameter ratio range, the sealing effect of the sealing component 7 can be better, and after the borehole probe plug device is removed from the aircraft engine, the sealing component 7 can be more naturally retained in the plug sealing groove 203, avoiding subsequent falling and loss and saving subsequent assembly steps.

[0089] In some embodiments, Figure 3 As shown, the plug 2 also includes a mounting groove 205 disposed on the top thereof for engaging with a corresponding mounting tool.

[0090] According to the above technical solution, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: it is convenient to use conventional installation tools for disassembly and assembly.

[0091] In some embodiments, Figure 3 As shown, the cross section of the mounting groove 205 is square.

[0092] Of course, the above-mentioned mounting groove cross-sectional shape is only a preferred form adopted by the borehole plugging device for aircraft engines in this application. Those skilled in the art can understand, based on the disclosure of this application, that other suitable mounting groove cross-sectional shapes (for example, hexagonal, octagonal, etc.) can also be adopted without departing from the scope of protection of the claims of this application.

[0093] In some embodiments, Figure 3 As shown, the mounting groove 205 extends along the longitudinal direction of the plug 2 (ie, the longitudinal direction of the borescope plug device).

[0094] In some embodiments, Figure 4 As shown, the locking pin 3 further includes an annular portion 303 disposed below the locking pin radial protrusion 301 .

[0095] According to the above technical solution, the bore probe plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: the annular portion 303 can be combined with the shell 1 to better define the space for accommodating the elastic member.

[0096] In some embodiments, Figure 5 As shown, the first self-locking ratchet 5 further includes a cylindrical portion 504 arranged on the upper portion thereof, and the ratchet mounting key 501 is arranged on the radial inner side of the cylindrical portion 504 .

[0097] According to the above technical scheme, the bore plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the cylindrical portion 504 can be combined with the shell 1 to better define the space for accommodating the elastic member, and the ratchet mounting key 501 can be firmly set on the first self-locking ratchet 5.

[0098] In some embodiments, Figure 6 As shown, the second self-locking ratchet 6 also includes an anti-rotation structure 602 disposed at the lower portion thereof.

[0099] According to the above technical solution, the borehole plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the anti-rotation structure 602 can prevent the borehole plugging device from rotating relative to the engine casing 802, thereby better achieving the sealing effect.

[0100] In some embodiments, Figure 6 As shown, the anti-rotation structure 602 is a recess for engaging with a corresponding boss provided on the engine housing 802 .

[0101] According to the above technical solution, the boresight plug device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the recess / boss type anti-rotation structure 602, the boresight plug device can be better prevented from rotating relative to the engine casing 802.

[0102] In some embodiments, Figure 1 — Figure 2 As shown, the housing 1 further includes a cylindrical extension portion 103 disposed at a lower portion thereof.

[0103] According to the above technical solution, the bore probe plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: the cylindrical extension portion 103 can better define the space for accommodating the elastic member.

[0104] In some embodiments, Figure 1 — Figure 2 As shown, the ratio of the height of the housing mounting keyway 101 to the total height of the housing 1 (ie, the height of the housing mounting keyway 101 plus the height of the cylindrical extension 103 ) is in the range of 0.15-0.25.

[0105] According to the above technical scheme, the borehole plugging device for aircraft engines of the present invention can achieve the following beneficial technical effects: through the appropriate shell installation keyway height / shell total height ratio range, the borehole plugging device can be assembled more conveniently.

[0106] In some embodiments, Figure 2 — Figure 5 As shown, the number of the housing mounting keyways 101 is four; the number of the plug mounting keyways 202 is also four; the number of the locking pin mounting keys 302 is also four; and the number of the ratchet mounting keys 501 is also four.

[0107] Of course, the number of keyways / keys mentioned above is merely a preferred form of the borehole plugging device used in the present application for aircraft engines. Those skilled in the art can understand, based on the disclosure of the present application, that other suitable numbers of keyways / keys (for example, three, five, six, etc.) may also be used without departing from the scope of protection of the claims of the present application.

[0108] In some embodiments, Figure 2 — Figure 5 As shown, four housing mounting keyways 101, four plug mounting keyways 202, four lock pin mounting keys 302, and four ratchet mounting keys 501 are evenly distributed along the circumferential direction.

[0109] like Figure 1 — Figure 8 As shown, according to one embodiment of the present invention, the assembly process of the bore probe plugging device for an aircraft engine is as follows:

[0110] First, the sealing assembly 7 is rotated and installed in the sealing groove 203 on the plug 2 through the lower threaded portion 204 on the plug 2. Secondly, the second self-locking ratchet 6 is inserted into the plug 2 from above, and the ratchet installation key 501 of the first self-locking ratchet 5 is inserted into the plug 2 through the plug installation keyway 202 of the plug 2, ensuring that the first serration structure 503 of the first self-locking ratchet 5 is engaged with the second serration structure 601 of the second self-locking ratchet 6. Thirdly, the spring 4 is inserted from above, and the bottom of the spring 4 abuts against the upper end surface of the ratchet radial protrusion 502 of the first self-locking ratchet 5. Then, the lock pin 3 is inserted into the plug 2 through the plug installation keyway 202 of the plug 2, and the lower end surface of the lock pin radial protrusion 301 of the lock pin 3 abuts against the top of the spring 4. Finally, the spring 4 is pressed down through the lock pin installation key 302 of the lock pin 3, and then the shell 1 is connected to the upper threaded portion 201 of the plug 2 through the threaded hole 102 from above. The lock pin 3 is acted upon by the elastic force of the spring 4, and the lock pin installation key 302 of the lock pin 3 is matched with the installation key slot 101 of the shell 1 to complete the entire assembly process.

[0111] like Figure 1 — Figure 8As shown, according to one embodiment of the present invention, the working principle of the bore probe plugging device for an aircraft engine is as follows:

[0112] Use conventional installation tools to connect the bore probe plug device to the engine housing 802 through the lower threaded portion 204 of the plug 2 through the installation groove 205 of the plug 2. After the second self-locking ratchet 6 contacts the engine housing 802, the anti-rotation structure 602 on the second self-locking ratchet 6 cooperates with the engine housing 802 to achieve the anti-rotation function, and the first serration structure 503 of the first self-locking ratchet 5 meshes with the second serration structure 601 of the second self-locking ratchet 6 to achieve the self-locking function. Continue to tighten the bore probe plug device downward, and finally form a sealing surface 801 with the engine housing 802 through the sealing component 7 (especially the metal C-shaped sealing ring 701) to achieve the sealing function.

[0113] The above describes the specific embodiments of the present invention, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation of the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. A bore probe plugging device for an aircraft engine, characterized in that: The borehole plugging device for an aircraft engine comprises a housing, a plug, a locking pin, an elastic member, a first self-locking ratchet, a second self-locking ratchet and a sealing assembly; Wherein, the housing includes a housing mounting keyway and a threaded hole arranged on the upper portion thereof; The plug includes an upper threaded portion, a plug mounting keyway, a sealing groove and a lower threaded portion, wherein the upper threaded portion is arranged at the upper portion of the plug and is used to engage with the threaded hole of the housing, the plug mounting keyway is opposite to the housing mounting keyway, the sealing groove is arranged near the middle portion of the plug and is used to accommodate the sealing assembly, and the lower threaded portion is arranged below the sealing groove and is used to engage with the engine casing of the aircraft engine; The lock pin includes a lock pin installation key disposed on its upper portion and a lock pin radial protrusion disposed below the lock pin installation key, the lock pin installation key is used to be inserted into the housing installation key slot and the plug installation key slot, and the lower end surface of the lock pin radial protrusion is used to abut against the top of the elastic member; The first self-locking ratchet comprises a ratchet installation key arranged on its upper part, a ratchet radial protrusion arranged near its lower part, and a first sawtooth structure arranged on its lower part, wherein the ratchet installation key is used to be inserted into the plug installation key slot, and the upper end surface of the ratchet radial protrusion is used to abut against the bottom of the elastic member; Wherein, the second self-locking ratchet comprises a second sawtooth structure arranged on an upper portion thereof, and the second sawtooth structure is used to engage with the first sawtooth structure; Wherein, the sealing assembly includes a metal C-shaped sealing ring.

2. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The sealing assembly also includes a metal gasket arranged radially inward of the metal C-shaped sealing ring, and the cross section of the metal gasket is a straight line.

3. The bore probe plugging device for an aircraft engine according to claim 2, characterized in that: The ratio of the outer diameter of the metal gasket to the outer diameter of the metal C-shaped sealing ring is in the range of 0.91-0.

93.

4. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The plug also includes a mounting groove arranged on the top thereof for engaging with a corresponding mounting tool.

5. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The locking pin further includes an annular portion disposed below the radial protrusion of the locking pin.

6. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The first self-locking ratchet also includes a cylindrical portion arranged on an upper portion thereof, and the ratchet mounting key is arranged on the radial inner side of the cylindrical portion.

7. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The second self-locking ratchet also includes an anti-rotation structure arranged at a lower portion thereof.

8. The bore probe plugging device for an aircraft engine according to claim 7, characterized in that: The anti-rotation structure is a recess for engaging with a corresponding boss arranged on the engine housing.

9. The bore probe plugging device for an aircraft engine according to claim 1, characterized in that: The housing further comprises a cylindrical extension portion arranged at a lower portion thereof.

10. The bore probe plugging device for an aircraft engine according to claim 9, characterized in that: The ratio of the height of the housing mounting keyway to the total height of the housing is in the range of 0.15-0.25.

Images