Peep hole sealing structure, aero-engine combustion chamber and hole inspection method

Abstract

The application discloses a peeping hole sealing structure, an aero-engine combustion chamber and a hole-probing inspection method. The peeping hole sealing structure comprises a mounting assembly arranged on a casing of an aero-engine combustion chamber, a mounting hole formed in the mounting assembly, a peeping hole formed in the mounting assembly and arranged at intervals relative to the mounting hole for the extension of a hole-probing device, a valve assembly which is axially movable and can be arranged on the mounting hole in a circumferential rotating manner, a limiting assembly connected with the mounting assembly, an elastic element arranged between the valve assembly and the limiting assembly and located in the mounting hole for axially elastically limiting the valve assembly, and a sealing element arranged between the valve assembly and the mounting assembly and located in the mounting hole for elastic sealing. The movable end of the valve assembly extends out of the mounting hole, and the valve assembly is used for being axially moved and circumferentially rotated to open or close the peeping hole, so that the hole-probing inspection process is simple and convenient, and the parts are not lost and the thread structure is not failed.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine inspection technology, and in particular, to a peephole sealing structure. Furthermore, this invention also relates to an aircraft engine combustion chamber including the aforementioned peephole sealing structure. Additionally, this invention relates to a borescope inspection method employing the aforementioned peephole sealing structure. Background Technology

[0002] Aero engines operate in harsh environments characterized by high speed, high pressure, and high temperature. Furthermore, as performance requirements for aero engines continue to increase, the operating temperatures of hot-end components such as the combustion chamber exceed the limits of their materials. The presence of any abnormalities within these hot-end components is crucial to the safety of the entire aero engine and its continued operational capability. To inspect the internal condition of these components without disassembling the engine, aero engines are designed with inspection holes (commonly known as "sighting holes") that allow for observation of the internal components using specialized equipment, requiring only the removal of a few parts. Regular inspections of the internal condition of hot-end components through these sight holes and specialized equipment allow for the timely detection of internal anomalies (such as scratches, cracks, and crack propagation), preventing more serious malfunctions and ensuring the aero engine operates under controllable and safe conditions. During aero engine operation, the sight holes must be sealed to ensure normal operation.

[0003] For example, Chinese invention patent application CN115356112A discloses a plug structure and its assembly / disassembly method for an observation window of an aero-engine. The plug assembly consists of a plug rod, a plug cap, and a guide rivet. The lower end of the plug rod is the plug head. The plug cap is fitted onto the middle of the plug rod and can rotate around the axis of the plug rod. A retaining ring is provided between the inner surface of the plug cap and the outer cylindrical surface of the plug rod to restrict the axial position of the plug cap. The guide rivet passes through a transverse hole in the middle of the plug rod and is located below the plug cap. A guide head is provided at one end of the guide rivet, and a flared end is provided at the other end. The guide rivet is engaged with the transverse hole of the plug rod through the guide head and the flared end. An external thread is provided on the outer circumferential surface of the lower section of the plug cap for threaded connection with the outer casing of the low-pressure turbine guide vane. During assembly and disassembly, the plug rod, plug cap, and guide rivet are assembled as a single unit, enabling quick disassembly and effectively preventing any component from falling into the engine's internal flow channels and forming debris.

[0004] For example, Chinese invention patent application CN115788682A discloses a quick-release plug and an aero-engine, including a mounting base and a sealing device. The mounting base is connected to the inspection hole of the casing, and the mounting base has a sealing cavity for inserting the sealing device. The sealing device assembly includes a plug rod, a stop cover, and an elastic sealing assembly, which is positioned between the stop cover and the target sealing position. The mounting base has a limiting structure for restricting the axial position of the stop cover within the sealing cavity. The first end of the stop cover has a force-applying structure for moving the sealing device until the stop cover engages with or disengages from the limiting structure. The plug rod is inserted into the sealing cavity until the stop cover engages with the limiting structure, thereby compressing the elastic sealing assembly, with the first end of the elastic sealing assembly abutting against the stop cover and the second end abutting against the target sealing position. The sealing device of this quick-release plug is an integrated structure, which avoids the disassembly and assembly of a large number of parts, making it easy to operate, highly reliable, and stable.

[0005] However, since the above structures all require the removal and installation of the plugs for borehole inspection, and the plugs are all fixed by threads, the following problems exist: 1) When performing borescope inspection, parts need to be removed, but the space inside the engine compartment is small, making operation difficult. After the parts such as plugs are removed, they are not easy to store and are easily lost. Loss will greatly affect the flight mission and progress of the aero engine. 2) To ensure the safe and reliable operation of aero engines, the number of borehole tests on aero engines is relatively high, which can easily lead to the failure of the threaded structure used to install plugs due to repeated disassembly and assembly. Summary of the Invention

[0006] This invention provides a borehole sealing structure, an aero-engine combustion chamber, and a borehole inspection method to solve the technical problems of existing borehole sealing structures requiring the removal of parts during borehole inspection, which makes the parts difficult to store and prone to loss, and the threaded structure used to install the plug is prone to failure when borehole inspection is performed many times.

[0007] According to one aspect of the present invention, a peephole sealing structure is provided, comprising a mounting assembly for being disposed on a casing of an aircraft engine combustion chamber, a mounting hole formed on the mounting assembly, peepholes formed on the mounting assembly and spaced apart from the mounting hole for insertion of a borescope, a valve assembly axially movable and circumferentially rotatable disposed on the mounting hole, a limiting assembly connected to the mounting assembly, an elastic member disposed between the valve assembly and the limiting assembly and located within the mounting hole for axially elastically limiting the valve assembly, and a sealing member disposed between the valve assembly and the mounting assembly and located within the mounting hole for elastic sealing, wherein the movable end of the valve assembly extends out of the mounting hole for opening or closing the peephole by axial movement and circumferential rotation.

[0008] As a further improvement to the above technical solution: Furthermore, the mounting assembly includes a mounting base with a mounting hole and a viewing hole, a limiting ring A formed by the outer edge of the mounting hole extending radially inward, and an annular boss formed by the inner edge of the mounting hole extending axially inward. The inner hole of the limiting ring A, the mounting hole, and the inner hole of the annular boss are sequentially connected to form a movable hole for the axial movement of the valve assembly. The seal is located between the limiting ring A and the valve assembly, and the annular boss is detachably connected to the limiting assembly.

[0009] Furthermore, the valve assembly includes an outer post for extending into the inner hole of the limiting ring A, an inner post arranged in the inner hole of the annular boss and the mounting hole, a receiving cylinder formed by extending radially outward and axially inward between the outer post and the inner post, and an opening and closing element arranged on the outer wall of the receiving cylinder for extending out of the mounting hole. The outer post is recessed with a mating groove for cooperating with the borehole tool to allow axial movement and circumferential rotation of the valve assembly. The sealing element is located between the receiving cylinder and the limiting ring A. The receiving cylinder and the inner post enclose a receiving cavity for accommodating the elastic element. The opening and closing element is used to open or close the peep hole by axial movement and axial rotation.

[0010] Furthermore, the opening and closing component includes a movable handle connected to the outer wall of the receiving cylinder, an opening and closing post disposed on the free end of the movable handle, and an opening and closing cone disposed on the opening and closing post for engaging with the conical surface of the peephole.

[0011] Furthermore, the annular boss is provided with a first sector groove for axial movement of the movable handle and a second sector groove connected to the first sector groove for circumferential rotation of the movable handle.

[0012] Furthermore, the axial height of the second sector groove is greater than the axial thickness of the movable handle by a preset value, which is 0.1mm-0.3mm.

[0013] Furthermore, the peephole includes a straight hole formed on the mounting base and a tapered hole formed on the mounting base and communicating with the straight hole, the tapered surface of which is used to engage with the opening and closing truncated cone.

[0014] Furthermore, the limiting assembly includes a limiting cylinder whose inner wall is threadedly connected to the outer wall of the annular boss, and a limiting ring B formed by the inner edge of the limiting cylinder extending radially inward. The inner hole of the limiting ring B communicates with the inner hole of the annular boss. An elastic element is arranged between the limiting ring B and the receiving cylinder. The axial outer edge of the limiting cylinder is used to axially abut and limit the opening and closing parts when they are away from or close to the viewing hole.

[0015] According to another aspect of the present invention, an aircraft engine combustion chamber is also provided, including a casing, a fuel nozzle passing through the casing, a flame tube communicating with the fuel nozzle, and a peephole sealing structure as described above.

[0016] According to another aspect of the present invention, a borescope inspection method is also provided, employing the aforementioned aero-engine combustion chamber, comprising the following steps: S1: A borescope fixture is connected to a valve assembly, so that the borescope fixture drives the valve assembly to move axially, causing the movable end of the valve assembly to separate axially from the inspection hole, and then the borescope fixture drives the valve assembly to rotate circumferentially, so that the movable end of the valve assembly moves away from the inspection hole; S2: A borescope device is inserted into the inspection hole to perform a borescope inspection on the internal condition of the casing until the borescope inspection is completed; S3: The borescope fixture drives the valve assembly to rotate circumferentially, so that the movable end of the valve assembly approaches the inspection hole, and then, under the action of an elastic element, the valve assembly is driven to move axially until the movable end of the valve assembly seals the inspection hole.

[0017] The present invention has the following beneficial effects: The peephole sealing structure of this invention has an installation component mounted on the casing of an aero-engine combustion chamber, with a peephole provided. This allows a borehole inspection device to be inserted into the combustion chamber for inspection. A mounting hole is also provided to accommodate a valve assembly mounted on a limiting component. When borehole inspection is required, the axial movement and circumferential rotation of the valve assembly open the peephole for inspection. After inspection, the circumferential rotation and axial movement of the valve assembly close the peephole, preventing airflow leakage and ensuring combustion chamber performance. An elastic element provides axial elastic limiting of the valve assembly and ensures a tight fit between the valve assembly's moving end and the peephole, indirectly improving the sealing performance of the valve assembly's moving end. The structure is designed to be mounted on the valve assembly and the installation component. The seals between components provide an elastic seal to the mounting holes, ensuring reliable sealing. The elastic components, while axially limiting the valve assembly, also compress the seals, further enhancing their sealing performance. Compared to existing technologies, this solution eliminates the need to remove parts during borehole inspection, fundamentally preventing accidental loss and ensuring the smooth operation of the aero-engine. It also avoids repeated disassembly and reassembly of threaded structures, preventing maintenance delays due to thread failure. Furthermore, with mounting holes and inspection holes, the coordinated action of the elastic components and seals ensures reliable sealing of both holes. This makes borehole inspection simple, convenient, fast, and efficient, facilitating multiple borehole inspections of aero-engines. It is highly practical and suitable for widespread application.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the structure of an aero-engine combustion chamber according to a preferred embodiment of the present invention; Figure 2 yes Figure 1 An enlarged schematic diagram of part A of the combustion chamber of the aircraft engine shown; Figure 3 This is a cross-sectional schematic diagram of the peephole sealing structure in a sealed state according to a preferred embodiment of the present invention; Figure 4 This is a cross-sectional schematic diagram of the peephole sealing structure in the axially separated state according to a preferred embodiment of the present invention; Figure 5 This is a cross-sectional schematic diagram of the mounting components in the peephole sealing structure of a preferred embodiment of the present invention; Figure 6 This is a schematic diagram of the valve assembly in the peephole sealing structure of a preferred embodiment of the present invention; Figure 7 yes Figure 6 A schematic diagram of the AA cross-section of the valve assembly in the peephole sealing structure shown; Figure 8 This is a cross-sectional schematic diagram of the limiting component in the peephole sealing structure of a preferred embodiment of the present invention.

[0020] Legend: 110. Mounting assembly; 111. Mounting base; 112. Limiting ring A; 113. Annular boss; 114. First sector groove; 115. Second sector groove; 120. Mounting hole; 130. Inspection hole; 131. Straight hole; 132. Conical hole; 140. Valve assembly; 141. Outer post; 142. Inner post; 143. Receiving cylinder; 144. Mating groove; 145. Moving handle; 146. Opening / closing post; 147. Opening / closing cone; 148. Receiving cavity; 150. Limiting assembly; 151. Limiting cylinder; 152. Limiting ring B; 160. Elastic element; 170. Seal; 200. Casing; 300. Fuel nozzle; 400. Flame tube. Detailed Implementation

[0021] The following description provides specific application scenarios and requirements for this specification, intended to enable those skilled in the art to make and use the contents of this specification. Various partial modifications to the disclosed embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of this specification. Therefore, this specification is not limited to the embodiments shown, but rather to the widest scope consistent with the claims.

[0022] The terminology used herein is for the purpose of describing particular exemplary embodiments only and is not restrictive. For example, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” as used herein may also include the plural forms. When used in this specification, the terms “comprising,” “including,” and / or “containing” mean that the associated integers, steps, operations, elements, and / or components are present, but do not preclude the presence of one or more other features, integers, steps, operations, elements, components, and / or groups, or that other features, integers, steps, operations, elements, components, and / or groups may be added to the system / method.

[0023] Considering the following description, these and other features of this specification, as well as the operation and function of the related components of the structure, and the economy of assembly and manufacture of the parts, can be significantly improved. All of these form part of this specification with reference to the accompanying drawings. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0024] like Figures 1-4 As shown, the peephole sealing structure of this embodiment includes a mounting assembly 110 for installation on the casing 200 of the combustion chamber of an aircraft engine, a mounting hole 120 opened on the mounting assembly 110, peepholes 130 for insertion of a borescope equipment opened on the mounting assembly 110 and spaced apart from the mounting hole 120, a valve assembly 140 axially movable and circumferentially rotatable on the mounting hole 120, a limiting assembly 150 connected to the mounting assembly 110, an elastic member 160 for axially elastically limiting the valve assembly 140, located between the valve assembly 140 and the limiting assembly 150 and within the mounting hole 120, and a sealing member 170 for elastic sealing, located between the valve assembly 140 and the mounting assembly 110 and within the mounting hole 120. The movable end of the valve assembly 140 extends out of the mounting hole 120 and is used to open or close the peephole 130 by axial movement and circumferential rotation.

[0025] like Figures 1-4As shown, specifically, in the inspection hole sealing structure of the present invention, the mounting assembly 110 is arranged on the casing 200 of the combustion chamber of the aircraft engine, and an inspection hole 130 is provided, so that the inspection equipment can be inserted into the combustion chamber of the aircraft engine through the inspection hole 130 for inspection. At the same time, a mounting hole 120 is provided to cooperate with the limiting assembly 150 to install the valve assembly 140, so that when inspection is required, the axial movement and circumferential rotation of the valve assembly 140 can open the inspection hole at the movable end of the valve assembly 140. 130, thus allowing for borehole inspection; after the borehole inspection is completed, the circumferential rotation and axial movement of the valve assembly 140 cause the movable end of the valve assembly 140 to close and seal the inspection hole 130, preventing airflow leakage in the combustion chamber and affecting combustion chamber performance; the elastic element 160 provides axial elastic limitation for the valve assembly 140, and drives the movable end of the valve assembly 140 to fit tightly against the inspection hole 130, indirectly improving the sealing performance of the movable end of the valve assembly 140 against the inspection hole 130; The sealing element 170, located between the valve assembly 140 and the mounting assembly 110, provides an elastic seal to the mounting hole 120, ensuring a reliable seal. Furthermore, the elastic element 160, while axially limiting the valve assembly 140, also compresses the sealing element 170, further enhancing the sealing performance of the sealing element 170 to the mounting hole 120. Compared to existing technologies, this solution eliminates the need to remove parts during borehole inspection, fundamentally eliminating the risk of accidental part loss and preventing disruption to the flight mission and schedule of the aero-engine. It also avoids the need for repeated disassembly and assembly of threaded structures, preventing maintenance delays due to thread failure. Moreover, with the mounting hole 120 and the inspection hole 130 provided, the elastic element 160 and the sealing element 170 work together to reliably seal both holes. This makes the borehole inspection process simple, convenient, fast, and efficient, facilitating multiple borehole inspections of the aero-engine. It is highly practical and suitable for widespread promotion and application.

[0026] It should be understood that in this embodiment, the radial and axial directions are based on the mounting hole 120 or the peep hole 130, and in this embodiment, the inner and outer directions are based on the casing 200.

[0027] It should be understood that the peephole 130 and the mounting hole 120 are arranged at intervals to maximize the moving distance of the movable end of the valve assembly 140 when the valve assembly 140 rotates, thereby facilitating the opening and closing of the peephole 130.

[0028] Optionally, the seal 170 is a C-ring. When the aero-engine is working, the pressure difference between the inside and outside of the combustion chamber gradually increases, and the pressure on the C-ring also increases, thereby enhancing the sealing effect of the seal 170.

[0029] Optionally, the elastic element 160 is a compression spring.

[0030] like Figure 5 As shown, in this embodiment, the mounting assembly 110 includes a mounting base 111 with a mounting hole 120 and a viewing hole 130, a limiting ring A112 formed by the outer edge of the mounting hole 120 extending radially inward, and an annular boss 113 formed by the inner edge of the mounting hole 120 extending axially inward. The inner hole of the limiting ring A112, the mounting hole 120 and the inner hole of the annular boss 113 are sequentially connected to form an active hole for the axial movement of the valve assembly 140. The sealing member 170 is located between the limiting ring A112 and the valve assembly 140. The annular boss 113 is detachably connected to the limiting assembly 150.

[0031] like Figure 5 As shown, specifically, the mounting base 111 is disposed on the casing 200 of the aircraft engine combustion chamber, with a mounting hole 120 and an inspection hole 130 provided on the mounting base 111. Both the mounting hole 120 and the inspection hole 130 communicate with the inner cavity of the combustion chamber. A limiting ring A is formed by extending radially inward from the outer edge of the mounting hole 120. 112, through the cooperation of the limiting ring A112 and the limiting component 150, axially limits the valve assembly 140 and the seal 170. An annular boss 113 is formed by extending axially inward from the inner edge of the mounting hole 120. The inner hole of the limiting ring A112, the mounting hole 120 and the inner hole of the annular boss 113 are sequentially connected to form an axially movable hole for the valve assembly 140. The movable hole increases the axial movement space of the valve assembly 140 and makes part of the valve assembly 140 located in the annular boss 113. This allows the movable end of the valve assembly 140 to extend out of the mounting hole 120 to move in the combustion chamber cavity, avoiding interference between components, thereby opening or closing the inspection hole 130.

[0032] like Figure 6 and Figure 7 As shown, in this embodiment, the valve assembly 140 includes an outer post 141 for extending into the inner hole of the limiting ring A112, an inner post 142 arranged in the inner hole of the annular boss 113 and the mounting hole 120, a receiving cylinder 143 extending radially outward and axially inward between the outer post 141 and the inner post 142, and an opening and closing member arranged on the outer wall of the receiving cylinder 143 for extending out of the mounting hole 120. The outer post 141 is recessed with a mating groove 144 for cooperating with the borehole tool to perform axial movement and circumferential rotation of the valve assembly 140. The sealing member 170 is located between the receiving cylinder 143 and the limiting ring A112. The receiving cylinder 143 and the inner post 142 enclose a receiving cavity 148 for accommodating the elastic member 160. The opening and closing member is used to open or close the peep hole 130 by axial movement and axial rotation.

[0033] like Figure 6 and Figure 7As shown, specifically, part of the outer column 141 is located in the mounting hole 120, and part extends into the inner hole of the limiting ring A112. After a mating groove 144 is opened on the outer side wall of the outer column 141, it is convenient to cooperate with the borehole tool through the mating groove 144 to allow for axial movement and circumferential rotation of the valve assembly 140. Part of the inner column 142 is located in the mounting hole 120, and part extends into the inner hole of the annular boss 113. The limiting ring A112 radially limits the outer column 141. The receiving cylinder 143 and the inner column 142 enclose and form a receiving cavity 148 to receive the elastic element 160. The elastic element 160 abuts against the receiving cylinder 143 to achieve axial elastic limiting of the valve assembly 140. The opening and closing element is connected to the outer wall of the receiving cylinder 143 and extends out of the mounting hole 120. The axial movement and axial rotation of the valve assembly 140 open or close the peep hole 130.

[0034] Optionally, the outer wall of the receiving cylinder 143 and the inner wall of the mounting hole 120 are fitted together to achieve radial limiting and axial guidance of the valve assembly 140, and to avoid interference when the outer post 141 extends into the hole of the limiting ring A112.

[0035] like Figure 6 and Figure 7 As shown, in this embodiment, the opening and closing component includes a movable handle 145 connected to the outer wall of the receiving cylinder 143, an opening and closing post 146 disposed on the free end of the movable handle 145, and an opening and closing cone 147 disposed on the opening and closing post 146 for engaging with the conical surface of the peephole 130. Specifically, the radial distance is increased by the movable handle 145, and the opening and closing cone 147 is installed by the opening and closing column 146. When the valve assembly 140 rotates, the movable handle 145 can drive the opening and closing cone 147 to move closer to or away from the peephole 130, thereby opening or closing the peephole 130. When the opening and closing cone 147 closes the peephole 130, the conical surface of the opening and closing cone 147 and the peephole 130 are in concave-convex fit. When the aero-engine is working, the pressure difference between the inside and outside of the combustion chamber gradually increases, and the conical surface fit will increase with the pressure, improving the sealing effect, that is, improving the sealing effect of the opening and closing cone 147 on the peephole 130, and achieving a reliable seal on the peephole 130.

[0036] like Figure 5As shown, in this embodiment, the annular boss 113 is provided with a first sector-shaped groove 114 for axial movement of the movable handle 145 and a second sector-shaped groove 115 communicating with the first sector-shaped groove 114 for circumferential rotation of the movable handle 145. Specifically, the first sector-shaped groove 114 provides axial movement space for the movable handle 145, so that the opening and closing cone 147 can open or close the inspection hole 130 through the axial movement of the movable handle 145. The second sector-shaped groove 115 provides circumferential movement space for the movable handle 145, so that the opening and closing cone 147 can move closer to or away from the inspection hole 130 through the circumferential movement of the movable handle 145. This avoids interference or obstruction of the opening and closing cone 147 to the insertion of the borehole inspection equipment during borehole inspection.

[0037] In this embodiment, the axial height of the first sector groove 114 is greater than the axial height of the second sector groove 115, and the angle of the first sector groove 114 is less than the angle of the second sector groove 115.

[0038] In this embodiment, the axial height of the second sector groove 115 is greater than the axial thickness of the movable handle 145 by a preset value, which is 0.1mm-0.3mm. Specifically, when the preset value is between 0.1mm and 0.3mm, the movable handle 145 rotates smoothly and avoids the annular boss 113 extending too far into the combustion chamber cavity, thus affecting airflow and combustion chamber performance; when the preset value is less than 0.1mm, the movable handle 145 is prone to jamming during rotation; when the preset value is greater than 0.3mm, the annular boss 113 extends too far into the combustion chamber cavity, thus affecting airflow.

[0039] like Figure 5 As shown, in this embodiment, the inspection hole 130 includes a straight hole 131 formed on the mounting base 111, and a tapered hole 132 formed on the mounting base 111 and communicating with the straight hole 131. The tapered surface of the tapered hole 132 is used for a concave-convex fit with the opening and closing cone 147. Specifically, the straight hole 131 facilitates the insertion of the borehole inspection equipment, and the concave-convex fit between the tapered surface of the tapered hole 132 and the opening and closing cone 147 improves the sealing performance.

[0040] like Figure 8As shown, in this embodiment, the limiting component 150 includes a limiting cylinder 151 whose inner wall is threadedly connected to the outer wall of the annular boss 113, and a limiting ring B152 formed by the inner edge of the limiting cylinder 151 extending radially inward. The inner hole of the limiting ring B152 communicates with the inner hole of the annular boss 113. An elastic element 160 is arranged between the limiting ring B152 and the receiving cylinder 143. The axial outer edge of the limiting cylinder 151 is used to axially abut and limit the opening and closing member when it is away from or close to the viewing hole 130. Specifically, during borehole inspection, the valve assembly 140 drives the opening and closing element to separate from the inspection hole 130 along the axial direction until it is axially abutted and limited. At this time, the valve assembly 140 can drive the opening and closing element to rotate circumferentially to move away from the inspection hole 130. That is, the limiting cylinder 151 ensures that the opening and closing element moves axially into place during borehole inspection, while the limiting ring B152 provides radial limitation for the valve assembly 140 and axial limitation for the elastic element 160.

[0041] like Figure 1 As shown, the combustion chamber of the aero-engine in this embodiment includes a casing 200, a fuel nozzle 300 passing through the casing 200, a flame tube 400 communicating with the fuel nozzle 300, and a peephole sealing structure as described above. Specifically, by providing a peephole sealing structure on the casing 200, borehole inspection can be performed during the disassembly and assembly of parts, fundamentally eliminating the risk of accidental loss of parts, avoiding impact on the flight mission and schedule of the aero-engine, and eliminating the need for repeated disassembly and assembly of threaded structures, thus avoiding the need for time-consuming maintenance due to threaded structure failure. Furthermore, with the mounting hole 120 and the peephole 130 provided, the elastic element 160 and the sealing element 170 work together to achieve a reliable seal for the two holes, while making the borehole inspection process simple, convenient, fast, and efficient. It facilitates multiple borehole inspections of the aero-engine combustion chamber, is highly practical, and suitable for widespread promotion and application.

[0042] The borescope inspection method of this embodiment uses the aforementioned aero-engine combustion chamber and includes the following steps: S1: A borescope fixture is connected to the valve assembly 140 so that the valve assembly 140 is axially moved by the borescope fixture, so that the movable end of the valve assembly 140 is separated from the inspection hole 130 along the axial direction. Then, the borescope fixture drives the valve assembly 140 to rotate circumferentially so that the movable end of the valve assembly 140 moves away from the inspection hole 130. S2: The borescope device is inserted into the inspection hole 130 to perform borescope inspection on the internal condition of the casing 200 until the borescope inspection is completed. S3: The borescope fixture drives the valve assembly 140 to rotate circumferentially so that the movable end of the valve assembly 140 approaches the inspection hole 130. Then, under the action of the elastic member 160, the valve assembly 140 is axially moved until the movable end of the valve assembly 140 seals the inspection hole 130. Specifically, the borehole inspection is completed through the above steps. Compared with existing technologies, the borehole inspection process is simple and convenient, and there will be no loss of parts or failure of threaded structures. It is applicable to the combustion chamber of aero-engines, has strong practicality, and is suitable for widespread promotion and application.

[0043] Optionally, the borehole probe tool is a screwdriver, and the mating groove 144 is a slotted groove.

[0044] Optionally, the borehole probe is a borehole instrument, which includes an endoscope.

[0045] The foregoing has described specific embodiments of this specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in a different order than that shown in the embodiments and may still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require a specific or sequential order to achieve the desired result. In some embodiments, multitasking and parallel processing are possible or may be advantageous.

[0046] In summary, after reading the detailed disclosure of this specification, those skilled in the art will understand that the foregoing detailed disclosure is presented by way of example only and is not restrictive. Although not explicitly stated herein, those skilled in the art will understand that this specification requires various reasonable changes, improvements, and modifications to the embodiments. These changes, improvements, and modifications are intended to be made by this specification and are within the spirit and scope of the exemplary embodiments described herein.

[0047] Furthermore, certain terms in this specification have been used to describe embodiments of this specification. For example, "an embodiment," "an embodiment," and / or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with that embodiment may be included in at least one embodiment of this specification. Therefore, it is to be emphasized and understood that two or more references to "an embodiment" or "an embodiment" or "alternative embodiment" in various parts of this specification do not necessarily refer to the same embodiment. Moreover, specific features, structures, or characteristics may be suitably combined in one or more embodiments of this specification.

[0048] It should be understood that in the foregoing description of the embodiments in this specification, various features are combined in a single embodiment, drawing, or description for the purpose of simplifying the description and aiding in the understanding of a feature. However, this does not mean that the combination of these features is necessary, and those skilled in the art may readily identify some of the devices as separate embodiments when reading this specification. That is, the embodiments in this specification can also be understood as an integration of multiple secondary embodiments. It is also valid when each secondary embodiment contains fewer than all the features of a single foregoing disclosed embodiment.

[0049] Each patent, patent application, publication of the patent application, and other materials such as articles, books, specifications, publications, documents, articles, etc., cited herein may be incorporated by reference. The entire contents used for all purposes, except for any history of prosecution documents associated with it, that may be inconsistent with or conflict with this document, or that may have a limiting effect on the widest extent of the claims, are now or hereafter associated with this document. For example, in the event of any inconsistency or conflict between the description, definition, and / or use of terms associated with any of the included materials and the terms, description, definition, and / or used in connection with this document, the terms used herein shall prevail.

[0050] Finally, it should be understood that the embodiments disclosed herein are illustrative of the principles of the embodiments described in this specification. Other modified embodiments are also within the scope of this specification. Therefore, the embodiments disclosed in this specification are merely examples and not limitations. Those skilled in the art can implement the applications described in this specification using alternative configurations based on the embodiments in this specification. Therefore, the embodiments in this specification are not limited to the embodiments precisely described in the applications.

Claims

1. A peephole sealing structure, characterized in that, Includes a mounting assembly (110) for mounting on a casing (200) of an aircraft engine combustion chamber, a mounting hole (120) on the mounting assembly (110), inspection holes (130) on the mounting assembly (110) and spaced apart from the mounting hole (120) for insertion of borehole equipment, a valve assembly (140) axially movable and circumferentially rotatable on the mounting hole (120), a limiting assembly (150) connected to the mounting assembly (110), and a valve assembly. An elastic element (160) for axial elastic limiting of the valve assembly (140) is located between the valve assembly (140) and the limiting component (150) and within the mounting hole (120), and a sealing element (170) for elastic sealing is arranged between the valve assembly (140) and the mounting component (110) and within the mounting hole (120). The movable end of the valve assembly (140) extends out of the mounting hole (120) and is used to open or close the peep hole (130) by axial movement and circumferential rotation. The mounting assembly (110) includes a mounting base (111) with a mounting hole (120) and a viewing hole (130), a limiting ring A (112) formed by the outer edge of the mounting hole (120) extending radially inward, and an annular boss (113) formed by the inner edge of the mounting hole (120) extending axially inward. The inner hole of the limiting ring A (112), the mounting hole (120) and the inner hole of the annular boss (113) are connected in sequence to form an active hole for the axial movement of the valve assembly (140). The seal (170) is located between the limiting ring A (112) and the valve assembly (140). The annular boss (113) is detachably connected to the limiting assembly (150). The valve assembly (140) includes an outer post (141) for extending into the inner hole of the limiting ring A (112), an inner post (142) disposed in the inner hole of the annular boss (113) and the mounting hole (120), a receiving cylinder (143) extending radially outward and axially inward between the outer post (141) and the inner post (142), and an opening and closing element disposed on the outer wall of the receiving cylinder (143) for extending out of the mounting hole (120). 141) The upper recess is provided with a mating groove (144) for cooperating with the borehole tool to allow axial movement and circumferential rotation of the valve assembly (140). The sealing element (170) is located between the receiving cylinder (143) and the limiting ring A (112). The receiving cylinder (143) and the inner column (142) enclose to form a receiving cavity (148) for receiving the elastic element (160). The opening and closing element is used to open or close the peep hole (130) by axial movement and axial rotation. The opening and closing components include a movable handle (145) connected to the outer wall of the receiving cylinder (143), an opening and closing post (146) disposed on the free end of the movable handle (145), and an opening and closing cone (147) disposed on the opening and closing post (146) for engaging with the conical surface of the peephole (130). The annular boss (113) is provided with a first sector groove (114) for the axial movement of the movable handle (145) and a second sector groove (115) connected to the first sector groove (114) for the circumferential rotation of the movable handle (145).

2. The peephole sealing structure according to claim 1, characterized in that, The axial height of the second sector groove (115) is 0.1mm-0.3mm greater than the axial thickness of the movable handle (145).

3. The peephole sealing structure according to claim 1, characterized in that, The peephole (130) includes a straight hole (131) opened on the mounting base (111) and a tapered hole (132) opened on the mounting base (111) and communicating with the straight hole (131). The tapered surface of the tapered hole (132) is used to engage with the opening and closing cone (147).

4. The peephole sealing structure according to claim 1, characterized in that, The limiting assembly (150) includes a limiting cylinder (151) whose inner wall is threaded to the outer wall of the annular boss (113), and a limiting ring B (152) formed by the inner edge of the limiting cylinder (151) extending radially inward. The inner hole of the limiting ring B (152) communicates with the inner hole of the annular boss (113). An elastic element (160) is arranged between the limiting ring B (152) and the receiving cylinder (143). The axial outer edge of the limiting cylinder (151) is used to axially abut and limit the opening and closing member when it is away from or close to the viewing hole (130).

5. An aircraft engine combustion chamber, characterized in that, It includes a housing (200), a fuel nozzle (300) passing through the housing (200), a flame tube (400) communicating with the fuel nozzle (300), and a peephole sealing structure as described in any one of claims 1-4.

6. A borescope inspection method, characterized in that, The use of the aircraft engine combustion chamber according to claim 5 includes the following steps: S1: A borescope tool is connected to the valve assembly (140) so that the valve assembly (140) can be moved axially through the borescope tool, so that the moving end of the valve assembly (140) can be separated from the peep hole (130) along the axial direction. Then, the borescope tool can be used to drive the valve assembly (140) to rotate circumferentially so that the moving end of the valve assembly (140) can be moved away from the peep hole (130). S2: The borescope is inserted into the inspection hole (130) to inspect the inside of the casing (200) until the borescope inspection is completed; S3: The valve assembly (140) is rotated circumferentially by the borehole tool so that the movable end of the valve assembly (140) is close to the peep hole (130). Then, under the action of the elastic element (160), the valve assembly (140) is moved axially until the movable end of the valve assembly (140) seals the peep hole (130).

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