Front fulcrum sealing test structure of aero-engine core engine

Abstract

The embodiment of the invention provides an aero-engine core engine front fulcrum sealing test structure, and relates to the field of aero-engines. The objective of the invention is to improve the problem of oil leakage risk in a core engine test process by using a slip ring device. The front supporting point sealing structure comprises a front supporting point sealing structure, a sliding ring stator piece and a sliding ring rotor piece, and the front supporting point sealing structure is used for being detachably connected between the front force bearing frame and the front end of the high-pressure rotor in a sealed mode so that a bearing cavity can be defined by the front force bearing frame, the front supporting point bearing, the high-pressure rotor and the front supporting point sealing structure; the slip ring stator part is used for being detachably connected with a front force bearing frame, the slip ring rotor part is used for being detachably connected with a high-pressure rotor, the slip ring rotor part and the slip ring stator part are in clearance sliding fit, and the slip ring stator part, the slip ring rotor part and the front fulcrum sealing structure define an outer cavity. The front fulcrum sealing structure is used for forming the bearing cavity in a surrounding mode, the closed state in the bearing cavity is guaranteed, and oil leakage of the bearing cavity in the core engine testing process is prevented.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically, to a test structure for sealing the front support point of an aero-engine core. Background Technology

[0002] The core engine is a key component of an aero-engine, primarily composed of three parts: the compressor, the combustion chamber, and the turbine. As the power source of the aero-engine, core engine testing is an indispensable process in the overall aero-engine design and verification. Conducting core engine testing before overall engine testing can significantly shorten the aero-engine development cycle and improve development efficiency. Furthermore, a proven and mature core engine can be matched with different low-pressure components to form various aero-engines.

[0003] Because core engine testing is relatively early in the aero-engine development cycle, it is necessary to monitor and verify many parameters, including rotor dynamic stress and rotor wall temperature. Currently, the industry uses telemetry or slip ring devices to solve this problem. Among them, high-pressure rotor dynamic stress and rotor wall temperature testing involves connecting a transfer shaft to the front end of the high-pressure rotor and inserting the test leads into the slip ring device. The slip ring stator is connected to the front load-bearing frame. There is a sealing structure between the rotor and stator of the slip ring, but this sealing function is only for the slip ring itself. In long-term, high-temperature testing, there is a risk of oil leakage in the bearing cavity. Summary of the Invention

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

[0005] The present invention includes, for example, providing a test structure for sealing the front support point of an aero-engine core, which can improve the problem of oil leakage risk during core engine testing using a slip ring device.

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

[0007] An embodiment of the present invention provides a test structure for sealing the front support point of an aero-engine core, which is used to be disposed between a front support frame and a high-pressure rotor. A front support bearing is disposed between the front support frame and the high-pressure rotor. The test structure for sealing the front support point of an aero-engine core includes a front support sealing structure, a slip ring stator, and a slip ring rotor. The front support sealing structure is used to detachably seal and connect between the front support frame and the front end of the high-pressure rotor, so that the front support frame, the front support bearing, the high-pressure rotor, and the front support sealing structure form a closed bearing cavity for accommodating lubricating oil.

[0008] The slip ring stator and the slip ring rotor are used to be connected to the slip ring test device during the test phase. The slip ring stator is detachably connected to the front load-bearing frame, and the slip ring rotor is detachably connected to the high-pressure rotor. The slip ring rotor and the slip ring stator are in clearance sliding fit. The slip ring stator, the slip ring rotor, and the front support sealing structure form a closed outer cavity on the side of the front support sealing structure away from the bearing cavity.

[0009] In addition, the aero-engine core engine front support sealing test structure provided in the embodiments of the present invention may also have the following additional technical features:

[0010] Optionally, the slip ring stator has an outer ring edge and an inner ring edge, the slip ring rotor has an outer ring edge and an inner ring edge, the outer ring edge of the slip ring stator is detachably connected to the front bearing frame, the outer ring edge of the slip ring rotor is detachably connected to the front end of the high-pressure rotor, and the inner ring edge of the slip ring stator and the inner ring edge of the slip ring rotor are in a clearance sliding fit.

[0011] Optionally, the slip ring rotor component is provided with a vent hole communicating with the outer chamber. The vent hole is used to allow gas from the high-pressure rotor shaft to flow into the outer chamber during the rotation of the high-pressure rotor, so that the pressure in the outer chamber is greater than that in the bearing cavity.

[0012] Optionally, the plane of rotation of the slip ring rotor is inclined at an angle to the rotation center line of the high-pressure rotor, and the center line of the vent hole is perpendicular to the plane of rotation of the high-pressure rotor.

[0013] Optionally, the aero-engine core front support sealing test structure further includes a plug, which is used to detachably connect to the front support frame when the slip ring stator is disassembled from the front support frame. The plug, the front support sealing structure, and the high-pressure rotor form a closed total chamber, the slip ring rotor can be located in the total chamber, and a gap is left between the plug and the slip ring rotor.

[0014] Optionally, the plug has an outer edge that is detachably connected to the front load-bearing frame.

[0015] Optionally, the middle part of the plug protrudes to one side relative to the outer edge of the plug, away from the front end of the high-pressure rotor.

[0016] Optionally, the aero-engine core engine front support sealing test structure further includes a slip ring support structure, which is detachably connected to the front load-bearing frame. The slip ring stator is fixedly connected to the slip ring support structure. The front support sealing structure, the slip ring support structure, the slip ring stator, and the slip ring rotor form the outer cavity on the side of the front support sealing structure away from the bearing cavity.

[0017] Optionally, the front support sealing test structure of the aero-engine core engine further includes a sealing rubber ring; the front support sealing structure has an outer ring edge and an inner ring edge, the outer ring edge of the front support sealing structure is detachably connected to the front load-bearing frame by bolts and sealed by the sealing rubber ring, and the inner ring edge of the front support sealing structure is connected to the front end of the high-pressure rotor.

[0018] Optionally, the aero-engine core engine front support sealing test structure further includes a front clamping nut, which is provided with a serrated structure. The front clamping nut is fixed to the front end of the high-pressure rotor. The inner edge of the front support sealing structure is provided with a honeycomb structure, which is sealed to the serrated structure, so that the front support sealing structure is sealed to the front end of the high-pressure rotor.

[0019] The beneficial effects of the aero-engine core engine front support sealing test structure of this invention include, for example:

[0020] The aero-engine core engine front support sealing test structure is used to be installed between the front load-bearing frame and the high-pressure rotor. A front support bearing is installed between the front load-bearing frame and the high-pressure rotor. The aero-engine core engine front support sealing test structure includes a front support sealing structure, a slip ring stator, and a slip ring rotor. The front support sealing structure is used to detachably seal and connect between the front load-bearing frame and the front end of the high-pressure rotor, so that the front load-bearing frame, the front support bearing, the high-pressure rotor, and the front support sealing structure form a closed bearing cavity for accommodating lubricating oil. The slip ring stator and the slip ring rotor are used to be connected to the slip ring test device during the test phase. The slip ring stator is used to be detachably connected to the front load-bearing frame, and the slip ring rotor is used to be detachably connected to the high-pressure rotor. The slip ring rotor and the slip ring stator have a clearance sliding fit. The slip ring stator, the slip ring rotor, and the front support sealing structure form a closed outer chamber on the side of the front support sealing structure away from the bearing cavity.

[0021] The front support sealing structure is used to enclose the bearing cavity, ensuring a sealed state within the cavity and preventing oil leakage during core machine testing. Structurally, it guarantees no oil leakage during testing, preventing oil from the front support bearing cavity from flowing into the slip ring, damaging it, increasing oil consumption, and affecting the test. The front support sealing structure can be installed with or without a slip ring structure to ensure a tight seal at the front support. Attached Figure Description

[0022] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0023] Figure 1 This is a schematic diagram of the test phase of the aero-engine core engine front support sealing test structure provided in an embodiment of the present invention;

[0024] Figure 2 This is a schematic diagram of the structure for removing the slip ring and installing the plug in the aero-engine core engine front support sealing test structure provided in an embodiment of the present invention;

[0025] Figure 3 This is a schematic diagram of the structure for removing the slip ring stator and installing the plug in the test structure for sealing the front support point of the aero-engine core engine, provided in an embodiment of the present invention.

[0026] Icons: 10-Front load-bearing frame; 20-Front pivot bearing; 30-High-pressure rotor; 40-Front pivot sealing test structure for aero-engine core; 500-Front pivot sealing structure; 510-Honeycomb structure; 520-Sealing rubber ring; 501-Bearing cavity; 600-Slip ring support structure; 700-Slip ring stator; 800-Slip ring rotor; 810-Ventilation hole; 801-Outer chamber; 900-Plug; 901-Main chamber; 400-Front clamping nut; 410-Grate structure. Detailed Implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0028] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0029] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0030] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0031] The following is combined Figures 1 to 3 The test structure for sealing the front support point of the aero-engine core engine provided in this embodiment is described in detail.

[0032] Please refer to Figure 1 An embodiment of the present invention provides a test structure 40 for sealing the front support point of an aero-engine core engine, which is disposed between a front support frame 10 and a high-pressure rotor 30. A front support bearing 20 is disposed between the front support frame 10 and the high-pressure rotor 30. The test structure 40 includes a front support sealing structure 500, a slip ring stator 700, and a slip ring rotor 800. The front support sealing structure 500 is used for detachably sealing the connection between the front support frame 10 and the front end of the high-pressure rotor 30, so that the front support frame 10, the front support bearing 20, the high-pressure rotor 30, and the front support bearing 20 are sealed together. The front support sealing structure 500 forms a closed bearing cavity 501 for containing lubricating oil; the slip ring stator 700 and the slip ring rotor 800 are used to be connected to the slip ring test device during the test phase. The slip ring stator 700 is detachably connected to the front load-bearing frame 10, and the slip ring rotor 800 is detachably connected to the high-pressure rotor 30. The slip ring rotor 800 and the slip ring stator 700 are in clearance sliding fit. The slip ring stator 700, the slip ring rotor 800 and the front support sealing structure 500 form a closed outer cavity 801 on the side of the front support sealing structure 500 away from the bearing cavity 501.

[0033] Reference Figure 1During the core machine testing phase, the front support frame 10, the front pivot bearing 20, the high-pressure rotor 30, and the front pivot sealing structure 500 form a bearing cavity 501. The slip ring stator 700, the slip ring rotor 800, and the front pivot sealing structure 500 form an outer chamber 801. The slip ring stator 700 and the slip ring rotor 800 are connected to the slip ring testing device for core machine testing. The bearing cavity 501 contains lubricating oil for lubricating the front pivot bearing 20. The front pivot sealing structure 500 forms the bearing cavity 501, ensuring a closed state within the bearing cavity 501 and preventing oil leakage during the core machine testing. Structurally, this ensures that the lubricating oil will not leak during the test, preventing oil from the front pivot bearing 20 cavity from flowing into the slip ring, damaging the slip ring, increasing lubricating oil consumption, and affecting the test. The slip ring includes a slip ring stator component 700 and a slip ring rotor component 800. The front support sealing structure 500 can be installed with or without the slip ring structure to ensure the sealing of the front support.

[0034] As the testing progresses, the core engine rotor dynamic stress and rotor wall temperature measurement points that have been verified will be successively removed. During the whole engine test, the front support sealing structure 500 will be removed to accommodate the entire aero engine. The structure of the whole engine will not need to be changed, and no modifications will be required to the part of the engine to be assembled.

[0035] Reference Figure 1 In this embodiment, the slip ring stator 700 has an outer ring edge and an inner ring edge, and the slip ring rotor 800 has an outer ring edge and an inner ring edge. The outer ring edge of the slip ring stator 700 is detachably connected to the front load-bearing frame 10, and the outer ring edge of the slip ring rotor 800 is detachably connected to the front end of the high-pressure rotor 30. The inner ring edge of the slip ring stator 700 and the inner ring edge of the slip ring rotor 800 are in a clearance sliding fit.

[0036] It should be noted that the front support sealing structure 500, the slip ring stator component 700, and the slip ring rotor component 800 all have a 360° rotating structure, that is, a ring structure. The front load-bearing frame 10 and the high-pressure rotor 30 also have a ring structure. Figures 1 to 3 All of these are structures obtained by cross-sectioning through the plane containing the centerline of the high-voltage rotor, and Figures 1 to 3 Only the upper half of the cross-section is shown. The complete cross-sectional structure can be formed by adding the lower half, which is symmetrical about the center line of the high-pressure rotor 30.

[0037] Both the slip ring stator 700 and the slip ring rotor 800 are annular structures. The slip ring stator 700 is connected to the front load-bearing frame 10. The slip ring rotor 800 rotates with the high-pressure rotor 30 and rotates relative to the slip ring stator 700.

[0038] Reference Figure 1In this embodiment, the slip ring rotor component 800 is provided with a vent 810 communicating with the outer chamber 801. The vent 810 is used to allow the axial gas of the high-pressure rotor 30 to flow into the outer chamber 801 during the rotation of the high-pressure rotor 30, so that the pressure in the outer chamber 801 is greater than that in the bearing cavity 501.

[0039] When slip rings are required during the core testing phase, the installation structure is as follows: Figure 1 The slip ring rotor component 800 is provided with a vent hole 810 to introduce the high-pressure rotor 30 shaft gas into the outer chamber 801. The gas pressure is greater than the bearing cavity 501 pressure, and the gas pressure ensures that the high-temperature oil-gas mixture will not leak during the test.

[0040] Reference Figure 1 In this embodiment, the plane of rotation of the slip ring rotor 800 is inclined at an angle to the rotation center line of the high-pressure rotor 30, and the center line of the vent 810 is perpendicular to the plane of rotation of the high-pressure rotor 30.

[0041] The centerline of the vent 810 is inclined to the rotation centerline of the high-pressure rotor 30. The airflow flowing into the outer chamber 801 is located just in front of the connection between the front support sealing structure 500 and the high-pressure rotor 30. The gas pressure is greater than that inside the bearing cavity 501, which can more effectively prevent the leakage of the oil-gas mixture inside the bearing cavity 501. This avoids the oil in the front support bearing 20 cavity from flowing into the slip ring during the test, damaging the slip ring, increasing the lubricating oil consumption, and affecting the test.

[0042] Reference Figure 2 and Figure 3 In this embodiment, the front support sealing test structure 40 of the aero-engine core engine also includes a plug 900. The plug 900 is used to detachably connect to the front support frame 10 when the slip ring stator 700 is disassembled from the front support frame 10. The plug 900, the front support sealing structure 500 and the high-pressure rotor 30 form a closed total chamber 901. The slip ring rotor 800 can be located in the total chamber 901, and a gap is left between the plug 900 and the slip ring rotor 800.

[0043] Reference Figure 2 During the stage when the core machine does not need to use slip rings, the plug 900 is installed and the front support sealing structure 500 remains connected. During the long-term test, the high-pressure rotor 30 rotates. The gas pressure at the shaft of the high-pressure rotor 30 is greater than the pressure in the bearing cavity 501. The gas pressure ensures that the high-temperature oil-gas mixture will not leak during the test.

[0044] Reference Figure 3If the slip ring test is not yet complete, and you don't want to affect other tests, such as long-term tests, then to allow for subsequent slip ring tests, only the slip ring stator 700 and slip ring support structure 600 are removed, while the slip ring moving part remains connected. Then, the plug 900 is installed for other tests, or to prevent external components from interfering with or colliding with the slip ring rotor 800 during a pause in the slip ring test. In this case, there is a gap between the slip ring rotor 800 and the plug 900, preventing interference and facilitating continuous testing while ensuring the structure's effectiveness. Because the test structure has a short service life, during long-term testing, the slip ring stator 700 can be quickly disassembled, and the plug 900 and front support sealing structure 500 can be installed. The slip ring rotor 800 is easily damaged, so frequent disassembly is not recommended.

[0045] Reference Figure 2 and Figure 3 In this embodiment, the plug 900 has an outer edge, and the outer edge of the plug 900 is detachably connected to the front load-bearing frame 10. (Refer to...) Figure 1 During the core machine testing phase requiring slip rings, the plug 900 does not need to be installed, refer to... Figure 2 and Figure 3 In the core machine testing phase where slip rings are not required, a plug 900 needs to be installed to allow for long-term testing or to reduce external interference.

[0046] Reference Figure 3 In this embodiment, the middle part of the plug 900 protrudes to one side relative to the outer edge of the plug 900, away from the front end of the high-pressure rotor 30. After the plug 900 is installed on the front support frame 10, the middle part of the plug 900 protrudes away from the front end of the high-pressure rotor 30 relative to the outer edge of the plug 900, thereby maintaining a gap with the unremoved slip ring rotor component 800 and preventing mutual interference.

[0047] Refer again Figure 1 In this embodiment, the front support sealing test structure 40 of the aero-engine core engine also includes a slip ring support structure 600. The slip ring support structure 600 is used to be detachably connected to the front load-bearing frame 10. The slip ring stator 700 is fixedly connected to the slip ring support structure 600. The front support sealing structure 500, the slip ring support structure 600, the slip ring stator 700 and the slip ring rotor 800 form an outer chamber 801 on the side of the front support sealing structure 500 away from the bearing cavity 501.

[0048] The slip ring support structure 600 also adopts a ring structure, which is used to install the slip ring stator 700 and provides support for the slip ring stator 700.

[0049] Reference Figure 1In this embodiment, the front support sealing test structure 40 of the aero-engine core engine also includes a sealing rubber ring 520; the front support sealing structure 500 has an outer ring edge and an inner ring edge, the outer ring edge of the front support sealing structure 500 is detachably connected to the front load-bearing frame 10 by bolts and sealed by the sealing rubber ring 520, and the inner ring edge of the front support sealing structure 500 is connected to the front end of the high-pressure rotor 30.

[0050] The front support sealing structure 500 is detachably connected to the front load-bearing frame 10 by bolts, and the sealing rubber ring 520 is located between the front support sealing structure 500 and the front load-bearing frame 10.

[0051] Reference Figure 1 In this embodiment, the front support sealing test structure 40 of the aero-engine core engine also includes a front clamping nut 400. The front clamping nut 400 is provided with a toothed structure 410410. The front clamping nut 400 is fixed to the front end of the high-pressure rotor 30. The inner edge of the front support sealing structure 500 is provided with a honeycomb structure 510. The honeycomb structure 510 and the toothed structure 410410 are sealed together so that the front support sealing structure 500 is sealed to the front end of the high-pressure rotor 30.

[0052] During core engine testing, a front support sealing structure 500 is added, which is bolted to the mounting edge of the front load-bearing frame 10 and sealed with a sealing rubber ring 520. The lower part of the front support sealing structure 500 has a honeycomb structure, and the sealing is ensured by the grates and honeycomb. The honeycomb grate structure 410 and the pressure difference ensure the sealing of the compressor front support bearing 20 cavity.

[0053] It should be noted that the "detachable connection" mentioned in this embodiment can be achieved using fasteners that facilitate disassembly and fixation, such as bolts or screws.

[0054] According to the aero-engine core engine front support sealing test structure 40 provided in this embodiment, the working principle of the aero-engine core engine front support sealing test structure 40 includes:

[0055] When there is no testing requirement and the slip ring is not installed, its assembly relationship is as follows: Figure 2 The components shown include: a front load-bearing frame 10, a front pivot bearing 20, a high-pressure rotor 30, and a front pivot sealing structure 500. Figure 1Similarly, the slip ring structure of the slip ring support structure 600, slip ring stator 700, and slip ring rotor 800 is replaced with a plug 900. During core machine testing, a front support sealing structure 500 is added, which is bolted to the mounting edge of the front load-bearing frame 10 and secured with a sealing rubber ring 520. The lower part of the front support sealing structure 500 has a honeycomb structure, and the sealing is ensured by the grates and honeycomb. That is, the front load-bearing frame 10, the front support bearing 20, the high-pressure rotor 30, and the front support sealing structure 500 form a cavity, structurally ensuring that lubricating oil will not leak during testing. During complete machine testing, the front support sealing structure 500 can be removed and the entire machine can be directly assembled.

[0056] When slip rings are required for core machine testing, install the slip ring support structure 600, the slip ring stator component 700, and the slip ring rotor component 800, as follows: Figure 1 The slip ring rotor component 800 has a vent hole 810 to introduce high-pressure rotor 30 shaft gas into the outer chamber 801. The pressure of this gas is greater than that of the bearing cavity 501, and the gas pressure ensures that the high-temperature oil-gas mixture will not leak during the test.

[0057] When the core machine does not require the use of slip rings, install the plug cover 900, such as... Figure 2 The gas pressure at the shaft center of the high-pressure rotor 30 is greater than the pressure in the bearing cavity 501. The gas pressure ensures that the high-temperature oil-gas mixture will not leak during the test.

[0058] The 900-position circular center protrusion structure of the plug allows for direct installation of the plug when the slip ring stator component 700 is removed during testing, leaving the slip ring rotor component 800 intact. There will be no interference with the slip ring leads. (See attached image.) Figure 3 .

[0059] The aero-engine core engine front support sealing test structure 40 provided in this embodiment has at least the following advantages:

[0060] The front support sealing structure 500 is used to enclose the bearing cavity 501, ensuring the closed state inside the bearing cavity 501 and preventing oil leakage from the bearing cavity 501 during the core machine test. Structurally, it ensures that the lubricating oil will not leak during the test, and avoids the oil in the front support bearing 20 cavity from flowing into the slip ring and damaging the slip ring during the test. The front support sealing structure 500 can be installed whether or not a slip ring structure is installed to ensure the sealing of the front support.

[0061] The front support sealing structure 500 is connected and fixed to the front load-bearing casing using bolts. The front bearing cavity 501 is sealed via a honeycomb structure 510 and a front clamping toothed nut on the compressor front journal used to press the bearing. Since the outer chamber 801 is a large air intake chamber with unstable pressure, a plug 900 is added to the left side of the front support sealing structure 500 to form a total chamber 901, stabilizing the sealing pressure outside the bearing cavity 501. When the core engine is subsequently assembled into a complete unit, only the front support sealing test structure 40 of the aero-engine core engine needs to be removed; no replacement or modification of the high-pressure section is required. The slip ring can be quickly disassembled and sealed on a test bench.

[0062] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An aeroengine core front pivot seal test structure for being disposed between a front load frame and a high pressure rotor, a front pivot bearing being disposed between the front load frame and the high pressure rotor, characterised in that, The aero-engine core machine front fulcrum sealing test structure comprises: A front fulcrum sealing structure is detachably connected between the front load frame and the front end of the high-pressure rotor, so that the front load frame, the front fulcrum bearing, the high-pressure rotor and the front fulcrum sealing structure form a closed bearing cavity for containing lubricating oil. A slip ring stator and a slip ring rotor are used to access a slip ring test device during a test phase, the slip ring stator is detachably connected with the front load frame, the slip ring rotor is detachably connected with the high-pressure rotor, the slip ring rotor and the slip ring stator are in a clearance fit, and the slip ring stator, the slip ring rotor and the front fulcrum sealing structure form a closed outer chamber on the side of the front fulcrum sealing structure away from the bearing cavity.

2. The aeroengine core engine fore pivot seal test structure of Claim 1, wherein, The slip ring stator has an outer rim and an inner rim, the slip ring rotor has an outer rim and an inner rim, the outer rim of the slip ring stator is detachably connected with the front load frame, the outer rim of the slip ring rotor is detachably connected with the front end of the high-pressure rotor, and the inner rim of the slip ring stator and the inner rim of the slip ring rotor are in a clearance fit.

3. The aeroengine core engine fore pivot seal test structure of Claim 1, wherein, The slip ring rotor is provided with a vent hole in communication with the outer chamber, the vent hole is used for allowing the gas in the shaft center of the high-pressure rotor to flow into the outer chamber during rotation of the high-pressure rotor, so that the pressure of the outer chamber is greater than that of the bearing cavity.

4. The aeroengine core engine fore pivot seal test structure of Claim 3, wherein, The rotation plane of the slip ring rotor is arranged at an inclined angle with the center line of the rotation of the high-pressure rotor, and the center line of the vent hole is perpendicular to the rotation plane of the high-pressure rotor.

5. The aeroengine core engine fore pivot seal test structure of Claim 1, wherein, The aero-engine core machine front fulcrum sealing test structure further comprises a plug, which is detachably connected with the front load frame when the slip ring stator is detached from the front load frame, the plug, the front fulcrum sealing structure and the high-pressure rotor form a closed total chamber, the slip ring rotor can be located in the total chamber, and a clearance is left between the plug and the slip ring rotor.

6. The aeroengine core engine fore pivot seal test structure of Claim 5, wherein, The plug has an outer rim, and the outer rim of the plug is detachably connected with the front load frame.

7. The aeroengine core engine fore pivot seal test structure of Claim 5, wherein, The middle part of the plug protrudes towards one side relative to the outer rim of the plug to be away from the front end of the high-pressure rotor.

8. The aeroengine core engine fore pivot seal test structure of any of claims 1-7, wherein, The aero-engine core machine front fulcrum sealing test structure further comprises a slip ring support structure, which is detachably connected with the front load frame, the slip ring stator is fixedly connected with the slip ring support structure, and the front fulcrum sealing structure, the slip ring support structure, the slip ring stator and the slip ring rotor form the outer chamber on the side of the front fulcrum sealing structure away from the bearing cavity.

9. The aeroengine core engine fore pivot seal test structure of any of claims 1-7, wherein, The aero-engine core machine front fulcrum sealing test structure further comprises a sealing rubber ring; The front fulcrum sealing structure has an outer edge and an inner edge, the outer edge of the front fulcrum sealing structure is detachably connected with the front force frame through bolts and is sealed through a sealing rubber ring, and the inner edge of the front fulcrum sealing structure is connected with the front end of the high-pressure rotor.

10. The aeroengine core engine fore pivot seal test structure of Claim 9, wherein, The aero-engine core machine front fulcrum sealing test structure further comprises a front pressing large nut, the front pressing large nut is provided with a gill structure, the front pressing large nut is fixed to the front end of the high-pressure rotor, the inner edge of the front fulcrum sealing structure is provided with a honeycomb structure, and the honeycomb structure is sealingly connected with the gill structure, so that the front fulcrum sealing structure is sealingly connected with the front end of the high-pressure rotor.

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