Floating Ring Seal Testing Device and Detection System

Abstract

This invention discloses a floating ring sealing test device and testing system. The device includes a housing and a test section. The housing has a receiving cavity. The test section includes a rotating shaft, two bearing components spaced axially outside the rotating shaft, and a test piece disposed between the two bearing components. The rotating shaft passes horizontally through the receiving cavity and is mounted on the housing through the two bearing components. The test piece is disposed within the receiving cavity and includes a sealing track sleeved on the rotating shaft and two floating ring components mounted on the housing. The sealing track includes two annular protrusions located at both axial ends of the test piece. The two floating ring components are correspondingly arranged with the two annular protrusions, and the floating ring components are used for non-contact sealing with the outer walls of the annular protrusions. The two floating ring components, the sealing track, and the housing together form a test cavity for introducing the test medium. This invention can simultaneously test two floating ring components under the same operating conditions, significantly improving test efficiency and reducing the failure risk of the test section.

Description

Technical Field

[0001] This invention relates to the field of testing technology for high-speed sealing mechanisms, and in particular, to a floating ring seal testing device. Furthermore, it also relates to a testing system including the floating ring seal testing device. Background Technology

[0002] Floating ring graphite seals are non-contact sealing devices widely used in the sealing positions of main bearing cavities in aero-engines. They limit leakage by utilizing the fluid resistance of fluid flowing through a small gap. In aero-engines, floating ring graphite seals face complex operating environments characterized by high temperature, high pressure, high speed, and oil / air separation on one side. These conditions directly affect the working clearance and leakage rate of the floating ring graphite seal. Current theoretical analyses of floating ring graphite seal performance cannot fully account for the impact of these complex operating conditions, thus failing to fully reflect the working performance of floating ring graphite seals in aero-engines. Therefore, it is necessary to conduct durability tests on floating ring graphite seals under simulated engine operating conditions, revise the design based on the test results, and verify their feasibility, reliability, and durability for use in aero-engines.

[0003] The conventional floating ring seal testing apparatus consists of a rotor structure of the floating ring seal test piece cantilevered on a test bench. The bearing cavity on both sides of the transition section is sealed using clearance sealing methods such as reverse thread structures. The floating ring seal test piece is installed in a sealing mounting seat. The mounting structure, materials, and mating dimensions of the sealing mounting seat simulate the assembly structure and interface dimensions of the floating ring seal test piece in the engine. The outer diameter of the sealing raceway simulates the radial clearance between the floating ring seal test piece and the sealing raceway. During the test, the drive system rotates the main shaft of the transition section to a set speed to simulate the speed and direction of the sealing raceway in the engine. High-temperature, high-pressure gas is supplied to the intake chamber through the air system to simulate the gas temperature and pressure environment of the test piece in the engine.

[0004] The existing floating ring seal testing equipment has the following problems:

[0005] 1. Due to the limitations of the cantilever installation structure and rotor dynamics, the length of the floating ring seal test piece installation section is limited. It is difficult to have enough space to install two floating ring seal test pieces simultaneously while meeting the requirements of high-speed operation. This makes it impossible to test two floating ring seal test pieces simultaneously under the same operating conditions, resulting in long test cycles and low efficiency. In addition, the cantilever installation structure also means that when pressurizing the intake chamber, the axial force generated on the sealing track is entirely borne by the bearing of the transition section, which makes the bearing prone to failure due to the large load.

[0006] 2. The main shaft of the transition section is a solid shaft. When the air inlet chamber is heated, the heat is easily transferred along the axial direction through the main shaft, resulting in uneven deformation of the main shaft, which is not conducive to the long-term stable operation of the test.

[0007] 3. The reverse thread seal structure of the bearing cavity has poor sealing effect, and the bearing cavity in the transition section is not well isolated from the external environment. The floating ring seal is a gap seal. When the sealing pressure difference under test conditions is large, the gas leakage is also large. This can easily cause a large amount of high-temperature gas to enter the bearing cavity in the transition section, increasing the ambient temperature of the bearing. It may even cause the lubricating oil gas in the bearing cavity to be blown away by the entering gas, which is not conducive to the long-term reliable operation of the bearing in the transition section.

[0008] 4. Existing testing equipment lacks the ability to acquire multiple physical quantities simultaneously at high frequency, making it difficult to detect changes in the leakage performance of floating ring seal test pieces or abnormalities in transition section bearings and other components under long-term operating conditions. Summary of the Invention

[0009] This invention provides a floating ring seal testing device to solve the technical problems of long testing cycles and unfavorable long-term operation of existing floating ring seal testing devices.

[0010] According to one aspect of the present invention, a floating ring seal testing apparatus is provided, comprising:

[0011] The housing has a receiving cavity inside;

[0012] The test section includes a rotating shaft for connection to the drive system, two bearing components spaced apart axially outside the rotating shaft, and a test piece disposed between the two bearing components. The rotating shaft passes through the receiving cavity in the horizontal direction and is mounted on the housing through the two bearing components. The test piece is disposed in the receiving cavity of the housing.

[0013] The test piece includes a sealed runway fitted on a rotating shaft and two floating rings installed on the housing. The sealed runway includes two annular convex plates located at both ends of the test piece along the axial direction. The two floating rings are arranged in a one-to-one correspondence with the two annular convex plates. The floating rings are used to perform non-contact sealing with the outer wall of the annular convex plates.

[0014] The two floating rings, the sealed raceway, and the shell together form a test chamber for introducing the test medium.

[0015] Furthermore, the edge of the annular convex plate is provided with a concave structure extending toward another annular convex plate, and an annular groove for introducing lubricating oil for cooling is provided in the concave structure.

[0016] The opening of the annular groove is set horizontally in a direction away from the other annular protrusion.

[0017] Furthermore, the two axial ends of the test piece are respectively enclosed by the shell to form a lubricating oil cavity. The shell has an oil inlet hole above the rotating shaft and an oil outlet hole communicating with the lubricating oil cavity below the rotating shaft.

[0018] An oil spray plate is installed inside the lubricating oil chamber, and the oil spray plate has an oil passage for connecting the annular groove and the oil inlet.

[0019] Furthermore, the floating ring component includes a floating ring mounting seat installed on the inner wall of the housing, a fixing plate installed on the floating ring mounting seat, and a floating ring seal sandwiched between the floating ring mounting seat and the fixing plate;

[0020] Floating ring seals are used for non-contact sealing with the outer wall of an annular convex plate.

[0021] Furthermore, the floating ring sealing test device also includes a bearing cavity sealing mechanism for sealing the bearing cavity of the bearing component. The bearing cavity sealing mechanism includes a labyrinth seal located on the side of the bearing component closer to the test cavity and a hydrodynamic seal located on the side of the bearing component away from the test cavity.

[0022] The labyrinth seal fits against the inner wall of the housing and is used to seal one end of the bearing cavity by step engagement with the rotating shaft. The hydrodynamic seal includes a sealing rotating ring sleeved on the outer wall of the rotating shaft, a sealing stationary ring disposed on the side of the sealing rotating ring away from the bearing cavity and surrounding the outside of the rotating shaft, and a stationary ring mounting seat sleeved on the sealing stationary ring and the sealing rotating ring for mounting the sealing stationary ring. The stationary ring mounting seat is connected to the outer wall of the housing.

[0023] Furthermore, a first cooling hole and a second cooling hole, both of which are axially connected, are provided inside the rotating shaft. The first cooling hole is located on the central axis of the rotating shaft, and the second cooling hole is arranged around the outside of the first cooling hole.

[0024] The rotating shaft has a return cavity inside the end that is connected to the drive system. The end of the first cooling hole away from the return cavity is used to introduce the cooling medium, and the end of the second cooling hole away from the return cavity is used to discharge the cooling medium.

[0025] Furthermore, the floating ring sealing test device also includes a cooling mechanism located at the end of the rotating shaft away from the return cavity and used to cool the rotating shaft. The cooling mechanism includes a cooling isolation seat that is sealed and sleeved on the outer wall of the rotating shaft, a cooling mounting seat that is provided around the end of the rotating shaft and sealed and sleeved outside the cooling isolation seat, and a cooling supply component installed on the cooling mounting seat and used to introduce cooling medium into the first cooling hole. Both the cooling isolation seat and the cooling mounting seat are installed on the stationary ring mounting seat.

[0026] A cooling cavity communicating with the second cooling hole is provided between the cooling mounting base and the cooling isolation base.

[0027] Furthermore, an air duct is provided between the cooling mechanism and the bearing components. The air duct is located within the stationary ring mounting base and the cooling isolation base, and is used to guide the sealing gas to the outer wall of the rotating shaft to prevent the cooling medium in the cooling chamber from leaking outward.

[0028] Furthermore, the floating ring sealing test device also includes a monitoring mechanism for real-time monitoring of test data. The monitoring mechanism includes a temperature measuring element for temperature measurement, a pressure measuring element for pressure measurement, a flow measuring element for flow measurement, and a vibration measuring element for monitoring the vibration of the test chamber. The temperature measuring element, pressure measuring element, and flow measuring element are located in the test chamber and / or bearing chamber.

[0029] Vibration measuring elements are placed on both sides of the test specimen and mounted on the housing.

[0030] According to another aspect of the present invention, a testing system is also provided, including the above-described floating ring seal testing device.

[0031] The present invention has the following beneficial effects:

[0032] 1. The floating ring sealing test device of the present invention, by having the test part pass through the accommodating cavity horizontally and installed on the housing, and by placing the test cavity between symmetrically arranged double floating rings to introduce the test medium, compared with the cantilever installation method in the prior art, not only can space be reserved for the simultaneous installation of double floating rings, but also the axial force balance of the test cavity under high speed conditions can be achieved, reducing the load on the bearing components during high pressure testing, reducing the risk of bearing component failure, and enhancing the stability and durability of the device.

[0033] 2. This device designs the sealed runway as an integrated structure with two symmetrically arranged annular protrusions. The two floating rings are positioned one-to-one with the outer walls of the two annular protrusions for a non-contact seal. This ensures that the installation interface dimensions of the two floating rings are identical and that the test conditions are consistent. This allows the device to test two floating rings simultaneously under the same conditions, effectively shortening the test cycle and improving test efficiency. Furthermore, the symmetrical design of the two annular protrusions on the sealed runway can achieve axial force balance under high pressure differential conditions, reducing the load on the bearing components during high-pressure testing.

[0034] 3. The rotating shaft can achieve high speed through connection with the drive system, and the test chamber can be filled with high temperature and high pressure gas, which can more accurately simulate the complex working conditions of aero engines, provide reliable data for the sealing performance evaluation of floating ring components, and is suitable for multi-scenario testing needs of aero engine seals.

[0035] 4. This device can be adapted to floating rings of different sizes, has strong versatility, expands the testing range, and provides strong support for the research and development of aero-engine sealing technology.

[0036] 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

[0037] The accompanying drawings, which form part of this application, 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:

[0038] Figure 1 This is a schematic diagram of the structure of the floating ring sealing test device according to a preferred embodiment of the present invention;

[0039] Figure 2 This is a schematic diagram of the sealing track of the floating ring sealing test device according to a preferred embodiment of the present invention;

[0040] Figure 3 This is a schematic diagram of the cooling mechanism of the floating ring sealing test device according to a preferred embodiment of the present invention;

[0041] Figure 4 A schematic diagram of the monitoring mechanism layout of the floating ring sealing test device according to a preferred embodiment of the present invention.

[0042] Legend:

[0043] 100. Housing; 101. Left end cover; 102. Right end cover; 200. Test section; 201. Rotating shaft; 2011. First cooling hole; 2012. Second cooling hole; 2013. Return chamber; 202. Bearing component; 203. Sealed raceway; 2031. Raceway ring; 2032. Annular convex plate; 2033. Reverse concave structure; 2034. Ring groove; 204. Floating ring component; 2041. Floating ring mounting base; 2042. Fixing plate; 2043. Floating ring seal; 300. Test chamber; 400. Sliding... Oil cavity; 401, oil inlet; 402, oil outlet; 403, oil spray plate; 4031, oil passage; 500, bearing cavity sealing mechanism; 501, labyrinth seal; 5011, first step structure; 5012, second step structure; 502, dynamic pressure seal; 5021, sealing ring; 5022, sealing ring; 5023, ring mounting base; 600, cooling mechanism; 601, cooling isolation seat; 602, cooling mounting base; 603, cooling supply component; 604, cooling cavity; 700, air duct. Detailed Implementation

[0044] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0045] like Figure 1As shown, the floating ring sealing test device of this embodiment includes a housing 100 and a test section 200. The housing 100 has a receiving cavity, and the test section 200 is horizontally inserted into the receiving cavity and installed on the housing 100. In this embodiment, the housing 100 is a hollow cuboid structure, and the housing 100 includes a left end cap 101 and a right end cap 102 symmetrically arranged on both sides of the test cavity. Optionally, the housing 100 can also be a hollow cylindrical structure. The test section 200 includes a rotating shaft 201, two bearing components 202, and a test piece. The two bearing components 202 are axially spaced and sleeved on the outer wall of the rotating shaft 201, and each bearing component 202 has a bearing cavity. The test piece is disposed between the two bearing components 202 and sleeved on the outer wall of the rotating shaft 201. The left end cover 101 and right end cover 102 of the housing 100 are provided with corresponding horizontal mounting holes. The rotating shaft 201 passes through the mounting holes and enters the receiving cavity of the housing 100. One end of the rotating shaft 201 is mounted on the left end cover 101 through one of the bearing components 202, and the other end of the rotating shaft 201 is mounted on the right end cover 102 through another bearing component 202. Thus, the rotating shaft 201 can effectively distribute the load through the support structure formed by the symmetrical bearing components 202 at both ends, making the stress distribution more uniform, the deflection smaller, and the stress amplitude lower under cyclic loading, thereby extending its service life. Both ends of the rotating shaft 201 protrude from the outside of the housing 100. One end of the rotating shaft 201 is used to connect with the drive system for high-speed rotation to simulate the speed of an aircraft engine.

[0046] The test piece is located in the middle of the accommodating cavity. The test piece includes a sealing track 203 fitted onto the outer wall of the rotating shaft 201, and two floating rings 204 arranged axially on the outer wall of the sealing track 203. The two floating rings 204 are symmetrically arranged, with one floating ring 204 installed on the inner wall of the left end cover 101 and the other floating ring 204 installed on the inner wall of the right end cover 102. The sealing track 203 includes two annular protrusions 2032 located at both axial ends of the test piece. The two annular protrusions 2032 are symmetrically arranged at both ends of the sealing track 203, and the two floating rings 204 are arranged one-to-one with the two annular protrusions 2032. The floating rings 204 are used for non-contact sealing with the outer wall of the annular protrusions 2032. Thus, the test piece can form a symmetrical structure vertically within the accommodating cavity of the housing 100, with the middle of the sealing track 203 as its axis. The sealed runway 203 forms a test chamber 300 between two annular protrusions 2032, two floating rings 204, and the housing 100. The housing 100 has a medium hole communicating with the test chamber 300. Test medium can be introduced into the test chamber 300 through the medium hole to simultaneously perform performance tests on the two floating rings 204. Preferably, the medium hole is located on the housing 100 above the rotating shaft 201, and the test medium is a high-temperature, high-pressure gas.

[0047] Therefore, the floating ring sealing test device of the present invention, by having the test section 200 pass through the accommodating cavity in the horizontal direction and be installed on the housing 100, and by placing the test cavity 300 between the symmetrically arranged double floating ring components 204 to allow the introduction of the test medium, not only leaves space for the simultaneous installation of the double floating ring components 204 compared with the cantilever installation method in the prior art, but also enables the rotating shaft 201 to achieve axial force balance when the test cavity 300 is pressurized under high speed conditions, reduces the load borne by the bearing component 202 during high pressure testing, reduces the risk of bearing component 202 failure, and enhances the stability and durability of the device.

[0048] like Figure 1 and Figure 2 As shown, the sealed runway 203 is an integral symmetrical structure. The sealed runway 203 includes a runway ring 2031 for interference fitting onto the outer wall of the rotating shaft 201, and two annular protrusions 2032 disposed at both axial ends of the runway ring 2031. The two annular protrusions 2032 are symmetrically arranged at both ends of the runway ring 2031, and are integrally formed with the runway ring 2031. The annular protrusions 2032 are arranged around the outer wall of the runway ring 2031 and extend radially away from the runway ring 2031. Integrating the two annular protrusions 2032 with the runway ring 2031 ensures that the outer diameter of the two annular protrusions 2032 is the same, thus ensuring that the interface dimensions of the sealed runway 203 of the two floating ring components 204 are the same during the test. Furthermore, the radial fit clearance between the floating ring component 204 and the sealed runway 203 can be simulated by the outer diameter of the annular protrusions 2032. Therefore, the sealed runway 203, by integrally machining the runway ring 2031 and the two annular protrusions 2032 into a symmetrical structure, and by setting the two floating rings 204 one-to-one with the outer walls of the two annular protrusions 2032 for non-contact sealing, not only ensures that the installation interface dimensions of the two floating rings 204 are the same, accurately simulating the interface dimensions, materials, surface coatings, and other mating conditions of the floating rings 204 in the sealed runway 203 of the aero-engine, but also ensures that the test conditions of the two floating rings 204 are consistent. This allows the device to test the two floating rings 204 simultaneously under the same conditions, effectively shortening the test cycle and improving test efficiency. In addition, the symmetrical design of the two annular protrusions 2032 of the sealed runway 203 can also achieve axial force balance when facing high pressure differential conditions, reducing the load on the bearing 202 during high pressure tests.

[0049] like Figure 1 and Figure 2As shown, the edge of the annular convex plate 2032 is provided with a concave structure 2033 extending toward another annular convex plate 2032. The concave structure 2033 is located at the end of the annular convex plate 2032 away from the runway ring 2031. An annular groove 2034 is formed in the concave structure 2033. The opening of the annular groove 2034 is set in the horizontal direction away from the other annular convex plate 2032. By introducing lubricating oil into the annular groove 2034, the sealing runway 203 can be cooled. The annular groove 2034 is located near the sealing surface of the sealing runway 203 and the floating ring 204. Under the centrifugal force of the sealing runway 203, the lubricating oil can form a stable cooling oil film in the high-temperature area of ​​the groove near the sealing surface to cool the sealing surface, thereby simulating the cooling conditions of the floating ring 204 in the environment of the aero-engine. The design of the concave structure 2033 of the annular convex plate 2032 can simulate the interface structure of the floating ring component 204 in an aero-engine, ensuring that the installation conditions of the floating ring component 204 under test are the same as those in reality. In addition, placing the annular groove 2034 within the concave structure 2033 not only avoids oil splashing and reduces oil consumption, but also allows the oil within the annular groove 2034 to enhance heat dissipation through the airflow vortex effect, thereby improving cooling efficiency.

[0050] like Figure 1 As shown, the axial ends of the test piece are respectively enclosed by the housing 100 to form an oil cavity 400. The housing 100 has an oil inlet hole 401 above the rotating shaft 201 and an oil outlet hole 402 communicating with the oil cavity 400 below the rotating shaft 201. An oil spray plate 403 is installed in the oil cavity 400, and the oil spray plate 403 has an oil passage 4031 for connecting the annular groove 2034 and the oil inlet hole 401. Thus, by allowing the lubricating oil to flow into the oil cavity 400 sequentially through the oil inlet hole 401, the oil passage 4031 in the oil spray plate 403, and the groove of the sealed runway 203, and then discharged through the oil outlet hole 402 on the housing 100, the lubricating oil is circulated and cooled. By controlling the oil injection pressure, the oil and gas environment and oil injection flow of the floating ring 204 in the bearing cavity side of the aero-engine are simulated, thereby ensuring that the test conditions of the two floating rings 204 are consistent.

[0051] like Figure 1As shown, the two floating ring components 204 are arranged symmetrically in the vertical direction between the bearing components 202 supported at both ends and disposed within the receiving cavity of the housing 100. Each floating ring component 204 includes a floating ring mounting seat 2041, a fixing plate 2042, and a floating ring seal 2043. The floating ring mounting seats 2041 of the two floating ring components 204 are symmetrically arranged within the receiving cavity. One floating ring mounting seat 2041 is connected and fixed to the inner wall of the left end cover 101 of the housing 100, and the other floating ring mounting seat 2041 is connected and fixed to the inner wall of the right end cover 102 of the housing 100. The fixing plate 2042 is disposed on the floating ring mounting seat 2041 away from the inner wall of the housing 100. On one side, the fixing plate 2042 and the floating ring mounting seat 2041 are provided with a slot, and the floating ring seal 2043 is snapped into the slot. The fixing plate 2042 presses the floating ring seal 2043 axially onto the floating ring mounting seat 2041 to achieve the positioning of the floating ring seal 2043. This ensures that the lower ends of the two floating ring seals 2043 correspond one-to-one with the outer walls of the two annular protrusions 2032 of the sealed runway 203 and perform non-contact sealing. Through the design of the floating ring mounting seat 2041 and the fixing plate 2042, the installation structure, interface size, materials, and other conditions of the floating ring seal 2043 in the aero-engine can be simulated. The test chamber 300 is located between the two floating ring seals 2043. By introducing a set high-temperature and high-pressure gas into the test chamber 300, it can be ensured that the two floating ring seals 2043 are under the same high-temperature and high-pressure gas test conditions during the test, and the gas temperature and pressure of the floating ring seals 2043 in the aero-engine environment can be simulated.

[0052] like Figure 1 and Figure 3As shown, the floating ring sealing test device also includes a bearing cavity sealing mechanism 500. The bearing cavity sealing mechanism 500 is used to be disposed at both ends of the bearing component 202 and to seal the bearing cavity. The bearing cavity sealing mechanism 500 includes a labyrinth seal 501 and a dynamic pressure seal 502. The labyrinth seal 501 is disposed on the side of the bearing component 202 near the test cavity 300 and is disposed in the receiving cavity of the housing 100. The dynamic pressure seal 502 is disposed on the side of the bearing component 202 away from the test cavity 300 and is disposed outside the housing 100. Specifically, the maze seal 501 is disposed between the sealed runway 203 and the bearing component 202. The maze seal 501 includes a first stepped structure 5011 disposed on the outer wall of the rotating shaft 201 and a second stepped structure 5012 disposed on the inner wall of the right end cover 102 of the housing 100. The first stepped structure 5011 is interference-fitted on the outer wall of the rotating shaft 201 or fixed to the rotating shaft 201. The second stepped structure 5012 is circumferentially disposed on the outside of the rotating shaft 201 and seals the outer wall of the rotating shaft 201. The sealed runway 203 is axially limited by the two first stepped structures 5011 between the two bearing components 202. The second step structure 5012 forms a stepped sealing engagement surface with the second step structure 5012 to seal one end of the bearing cavity of the bearing component 202. The labyrinth seal 501 can achieve a lower leakage amount by changing the flow direction of the leaking gas through multiple deflections, thereby reducing the impact of high temperature gas leakage on the operation and life of the bearing component 202.

[0053] The dynamic pressure seal 502 includes a dynamic sealing ring 5021, a stationary sealing ring 5022, and a stationary ring mounting base 5023. The dynamic sealing ring 5021 is interference-fitted onto the outer wall of the rotating shaft 201 to rotate synchronously with the rotating shaft 201. The stationary sealing ring 5022 is fitted onto the outer wall of the rotating shaft 201 and located on the side of the dynamic sealing ring 5021 away from the bearing cavity. The stationary ring mounting base 5023 is encircled around the outside of the stationary sealing ring 5022 and the dynamic sealing ring 5021 and is connected and fixed to the outer wall of the housing 100, so that a stable micron-level gas film is formed between the dynamic sealing ring 5021 and the stationary sealing ring 5022 to isolate the dynamic sealing ring 5021 and the stationary sealing ring 5022. This allows the seal at the end of the bearing cavity of the bearing component 202 away from the test piece to operate reliably for a long time with low leakage. Preferably, the hydrodynamic seal 502 further includes an elastic element installed within the stationary ring mounting base 5023. The elastic force of the elastic element axially presses the rotating sealing ring 5021 and the stationary sealing ring 5022 together, forming a stable and reliable sealing surface between them and ensuring a good sealing effect. Preferably, the elastic element is a spring. Preferably, the end face of the rotating sealing ring 5021 is provided with a hydrodynamic groove, which is a spiral groove with an outer diameter facing outwards.

[0054] like Figure 1 and Figure 3As shown, the rotating shaft 201 has a double-layered hollow structure. Specifically, the rotating shaft 201 has a first cooling hole 2011 and a second cooling hole 2012, both of which are axially continuous. The first cooling hole 2011 is located on the central axis of the rotating shaft 201, and the second cooling hole 2012 is arranged around the outside of the first cooling hole 2011. A cover plate is sealed to the end of the rotating shaft 201 that is connected to the drive system. A return flow cavity 2013 communicating with the first cooling hole 2011 and the second cooling hole 2012 is provided between the cover plate and the end of the rotating shaft 201. The end of the first cooling hole 2011 away from the return flow cavity 2013 is used to introduce cooling medium, and the end of the second cooling hole 2012 away from the return flow cavity 2013 is used to discharge cooling medium. Thus, after the cooling medium is introduced into the first cooling hole 2011 at the end of the rotating shaft 201 away from the return cavity 2013, the cooling medium can flow along the first cooling hole 2011 to the return cavity 2013. After being blocked by the cover plate, the cooling medium flows into the second cooling hole 2012 and is discharged from the end of the rotating shaft 201 away from the return cavity 2013 through the second cooling hole 2012, forming a flow cooling of the cooling medium in the rotating shaft 201.

[0055] like Figure 1 and Figure 3As shown, specifically, the floating ring sealing test device also includes a cooling mechanism 600. The cooling mechanism 600 is located at the end of the rotating shaft 201 away from the return cavity 2013, and is connected to the first cooling hole 2011 and the second cooling hole 2012 of the rotating shaft 201 to cool the rotating shaft 201. The cooling mechanism 600 includes a cooling isolation seat 601, a cooling mounting seat 602, and a cooling supply component 603. The cooling isolation seat 601 is sealed and fitted onto the outer wall of the rotating shaft 201. The cooling mounting seat 602 is provided around the end of the rotating shaft 201 and sealed and fitted onto the outside of the cooling isolation seat 601. Both the cooling isolation seat 601 and the cooling mounting seat 602 are mounted on the stationary ring mounting seat 5023. A cooling cavity 604 communicating with the second cooling hole 2012 is provided between the cooling mounting seat 602 and the cooling isolation seat 601. A cooling component 603 is mounted on a cooling mounting base 602 and communicates with a first cooling hole 2011 to allow cooling medium to flow into the first cooling hole 2011. A certain gap is provided between the cooling component 603 and the inner wall of the first cooling hole 2011 to prevent the cooling component 603 from rotating with the rotating shaft 201. Preferably, the cooling medium is cooling water. Preferably, a drain hole communicating with a cooling chamber 604 is provided in the cooling mounting base 602, through which cooling water in the cooling chamber 604 can be discharged to the outside. In use, external cooling water is injected into the first cooling hole 2011 of the rotating shaft 201 through the cooling supply component 603. The cooling water flows along the first cooling hole 2011 to the return chamber 2013, and after being blocked by the cover plate, it flows into the second cooling hole 2012. After passing through the second cooling hole 2012, it flows into the cooling chamber 604 for recycling. The recycled cooling water in the cooling chamber 604 is discharged to the external circulation system through the drain hole. After being cooled, filtered, and pressurized by the circulation system, it is then connected to the cooling supply component 603, which injects cooling water into the rotating shaft 201, forming a circulating water flow cooling system. For the high-temperature conditions above 300°C required by the floating ring seal 2043, this invention effectively reduces the core temperature of the rotating shaft 201 by using this method to cool the rotating shaft 201, avoiding deformation of the rotating shaft 201 caused by uneven thermal expansion. At the same time, it is beneficial to the cooling of the bearing components 202 at both ends of the rotating shaft 201, thereby extending the service life of the bearing components 202. Preferably, in order to avoid uneven mass distribution of the rotating shaft 201 caused by the double-layer hollow structure, the rotating shaft 201 is subjected to high-speed dynamic balancing treatment to further reduce vibration during high-speed test conditions.

[0056] like Figure 3As shown, an air duct 700 is also provided between the cooling mechanism 600 and the bearing component 202. The air duct 700 is located in the stationary ring mounting base 5023 and the cooling isolation base 601. The air duct 700 is connected to the outer wall of the rotating shaft 201. By passing the pressurized sealing gas through the air duct to the outer wall of the rotating shaft 201, the sealing gas can seal the space between the cooling chamber 604 and the sealing stationary ring 5022, preventing the oil and gas in the bearing cavity from leaking outward and preventing the cooling water in the cooling chamber 604 from entering the bearing cavity. This improves the operating environment of the bearing component 202 and enables the bearing component 202 to achieve long-term reliable operation under high parameter conditions.

[0057] The floating ring seal testing device of the present invention uses a drive system to rotate the rotating shaft 201 at a set speed to simulate the rotational speed and direction of the sealing runway 203 in an aero-engine. High-temperature, high-pressure gas is introduced into the test chamber 300 to simulate the gas temperature and pressure environment of the floating ring seal 2043 in the aero-engine. The structural design of the sealing runway 203 simulates the interface dimensions, materials, surface coatings, and other mating components of the sealing runway 203 in the aero-engine. The design of the floating ring mounting base 2041 and the fixing plate 2042 is used to simulate the installation structure, interface size, and installation materials of the floating ring seal 2043 in the engine. The flow path design in the lubricating cavity 400 between the main end cover and the right end cover 102 of the housing 100 and the floating ring 204, as well as the control of the injection pressure, are used to simulate the oil and gas environment and injection flow of the floating ring seal 2043 on the bearing cavity side of the aero-engine. This ensures that the test conditions of the two floating ring seals 2043 are consistent.

[0058] like Figure 4As shown, the floating ring seal testing device also includes a monitoring mechanism for real-time monitoring of test data. The monitoring mechanism includes a temperature measuring element for temperature measurement, a pressure measuring element for pressure measurement, a flow measuring element for flow measurement, and a vibration measuring element for monitoring the vibration of the test chamber 300. The temperature measuring element, pressure measuring element, and flow measuring element are located in the test chamber 300 and / or the bearing cavity, while the vibration measuring element is located on both sides of the test piece and mounted on the housing 100, thereby achieving real-time monitoring of parameters such as the temperature of the test chamber 300, the pressure of the test chamber 300, the leakage of the test chamber 300, and the temperature of the bearing cavity. Preferably, the flow measuring element is a flow meter, the temperature measuring element is a temperature sensor, the pressure measuring element is a pressure sensor, and the vibration measuring element is a vibration sensor. The temperature measuring element, pressure measuring element, flow measuring element, and vibration measuring element are electrically connected to a data acquisition unit to collect the monitoring data. Preferably, the monitoring mechanism is equipped with an over-limit alarm. When monitored parameters such as temperature, pressure, and vibration exceed the upper limit alarm value, automatic shutdown can be achieved through the data acquisition device, ensuring the safety of the device during long-term operation under high-parameter conditions. By performing synchronous high-frequency acquisition of multiple physical quantities during the test of the 2043 floating ring seal, the monitoring capability is greatly improved.

[0059] According to another aspect of the present invention, a testing system is also provided, including the floating ring seal testing device. The testing system further includes a drive system, an air supply device, an oil supply device, and a cooling device. Specifically, one end of the rotating shaft 201 is connected to the cooling device via a cooling mechanism 600, and the other end of the rotating shaft 201 is connected to the drive system disposed outside the housing 100 via a flexible coupling. Preferably, the drive system is a motor to drive the rotating shaft 201 to rotate at high speed. In this embodiment, the motor enables the rotating shaft 201 to adapt to high-speed operating conditions of 30,000 r / min or higher. Preferably, the motor is connected to a frequency converter. The flexible coupling is a bellows coupling, which can absorb the vibration and impact during the operation of the rotating shaft 201, extending the service life of the floating ring seal testing device.

[0060] The gas supply system uses a high-temperature, high-pressure gas heater as the gas source to supply gas to the test chamber 300, simulating the gas temperature and pressure environment of the floating ring seal 2043 in an aero-engine. The high-temperature, high-pressure gas heater has an automatic temperature control device, and its gas pressure is controlled by a pressure sensor at the test chamber 300 to ensure that the gas pressure entering the test chamber 300 meets the requirements. The oil supply system uses an oil pump to supply oil to the interior of the test chamber 200, simulating the lubricating oil environment of the floating ring seal 2043 in an aero-engine.

[0061] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A floating ring sealing test device, characterized in that, include: A housing (100) having a receiving cavity inside; The test section (200) includes a rotating shaft (201) for connection with a drive system, two bearing members (202) spaced axially outside the rotating shaft (201), and a test piece disposed between the two bearing members (202). The rotating shaft (201) passes through the accommodating cavity in a horizontal direction and is mounted on the housing (100) through the two bearing members (202). The test piece is disposed in the accommodating cavity of the housing (100). The test piece includes a sealed runway (203) sleeved on the rotating shaft (201) and two floating rings (204) installed on the housing (100). The sealed runway (203) includes two annular protrusions (2032) respectively disposed at both ends of the axial direction of the test piece. The two floating rings (204) are arranged in a one-to-one correspondence with the two annular protrusions (2032). The floating rings (204) are used to perform non-contact sealing with the outer wall of the annular protrusions (2032). The two floating rings (204), the sealed raceway (203), and the housing (100) together form a test chamber (300) for introducing the test medium; The edge of the annular convex plate (2032) is provided with a concave structure (2033) extending toward the other annular convex plate (2032). The concave structure (2033) is provided with an annular groove (2034) for passing lubricating oil for cooling. The opening of the annular groove (2034) is arranged horizontally toward the direction away from the other annular convex plate (2032).

2. The floating ring sealing test device according to claim 1, characterized in that, The test piece has two axial ends that are respectively enclosed with the housing (100) to form a lubricating oil cavity (400). The housing (100) has an oil inlet hole (401) above the rotating shaft (201) and an oil outlet hole (402) communicating with the lubricating oil cavity (400) below the rotating shaft (201). An oil spray plate (403) is installed inside the lubricating oil cavity (400), and the oil spray plate (403) is provided with an oil passage (4031) for connecting the annular groove (2034) and the oil inlet (401).

3. The floating ring sealing test device according to claim 1, characterized in that, The floating ring component (204) includes a floating ring mounting base (2041) installed on the inner wall of the housing (100), a fixing plate (2042) installed on the floating ring mounting base (2041), and a floating ring seal (2043) sandwiched between the floating ring mounting base (2041) and the fixing plate (2042); The floating ring seal (2043) is used for non-contact sealing with the outer wall of the annular convex plate (2032).

4. The floating ring sealing test device according to claim 1, characterized in that, The floating ring sealing test device further includes a bearing cavity sealing mechanism (500) for sealing the bearing cavity of the bearing component (202). The bearing cavity sealing mechanism (500) includes a labyrinth seal (501) disposed on the side of the bearing component (202) close to the test cavity (300) and a hydrodynamic seal (502) disposed on the side of the bearing component (202) away from the test cavity (300). The labyrinth seal (501) is fitted to the inner wall of the housing (100) and is used to seal one end of the bearing cavity by step engagement with the rotating shaft (201). The hydrodynamic seal (502) includes a sealing moving ring (5021) sleeved on the outer wall of the rotating shaft (201), a sealing stationary ring (5022) disposed on the side of the sealing moving ring (5021) away from the bearing cavity and surrounding the outside of the rotating shaft (201), and a stationary ring mounting seat (5023) sleeved on the sealing stationary ring (5022) and the sealing stationary ring (5022) and used to install the sealing stationary ring (5022). The stationary ring mounting seat (5023) is connected to the outer wall of the housing (100).

5. The floating ring sealing test device according to claim 4, characterized in that, The rotating shaft (201) has a first cooling hole (2011) and a second cooling hole (2012) that are both axially connected. The first cooling hole (2011) is located on the central axis of the rotating shaft (201), and the second cooling hole (2012) is arranged around the outside of the first cooling hole (2011). The rotating shaft (201) has a return cavity (2013) inside the end that is connected to the drive system, which communicates with the first cooling hole (2011) and the second cooling hole (2012). The end of the first cooling hole (2011) away from the return cavity (2013) is used to introduce cooling medium, and the end of the second cooling hole (2012) away from the return cavity (2013) is used to discharge cooling medium.

6. The floating ring sealing test device according to claim 5, characterized in that, The floating ring sealing test device further includes a cooling mechanism (600) disposed at one end of the rotating shaft (201) away from the return cavity (2013) and used to cool the rotating shaft (201). The cooling mechanism (600) includes a cooling isolation seat (601) sealed and sleeved on the outer wall of the rotating shaft (201), a cooling mounting seat (602) disposed around the end of the rotating shaft (201) and sealed and sleeved outside the cooling isolation seat (601), and a cooling supply component (603) mounted on the cooling mounting seat (602) and used to introduce cooling medium into the first cooling hole (2011). The cooling isolation seat (601) and the cooling mounting seat (602) are both mounted on the stationary ring mounting seat (5023). A cooling cavity (604) communicating with the second cooling hole (2012) is provided between the cooling mounting base (602) and the cooling isolation base (601).

7. The floating ring sealing test device according to claim 6, characterized in that, An air duct (700) is provided between the cooling mechanism (600) and the bearing component (202). The air duct (700) is located in the stationary ring mounting base (5023) and the cooling isolation base (601) and is used to guide the sealing gas to the outer wall of the rotating shaft (201) to prevent the cooling medium of the cooling chamber (604) from leaking outward.

8. The floating ring sealing test device according to claim 1, characterized in that, The floating ring sealing test device also includes a monitoring mechanism for real-time monitoring of test data. The monitoring mechanism includes a temperature measuring element for temperature measurement, a pressure measuring element for pressure measurement, a flow measuring element for flow measurement, and a vibration measuring element for monitoring the vibration of the test chamber (300). The temperature measuring element, pressure measuring element and flow measuring element are located in the test chamber (300) and / or the bearing cavity. The vibration measuring elements are located on both sides of the test piece and installed on the housing (100).

9. A detection system, characterized in that, The floating ring sealing test apparatus includes any one of claims 1 to 8.

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