Floating ring seal test device and detection system

Abstract

The invention discloses a floating ring seal test device and a detection system, the device comprises a shell and a test part, the shell is internally provided with an accommodating cavity, the test part comprises a rotating shaft, two bearing parts and a test part, the rotating shaft is sleeved with the two bearing parts at intervals in the axial direction, and the test part is arranged between the two bearing parts; the rotating shaft penetrates through the containing cavity in the horizontal direction and is installed on the shell through two bearing pieces. The test piece is arranged in the containing cavity and comprises a sealing runway arranged on the rotating shaft in a sleeving mode and two floating ring pieces installed on the shell, the sealing runway comprises two annular protruding plates arranged at the two axial ends of the test piece respectively, and the two floating ring pieces and the two annular protruding plates are arranged in a one-to-one correspondence mode. The floating ring piece is used for performing non-contact sealing with the outer wall of the annular convex plate; and the two floating ring pieces, the sealing runway and the shell are enclosed to form a test cavity for introducing a test medium. Two floating ring pieces can be tested at the same time under the same working condition, the test efficiency is remarkably improved, and the failure risk of a test part is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of test of high-speed sealing mechanism, in particular, to a floating ring seal test device. Furthermore, the present application also relates to a detection system comprising the floating ring seal test device. BACKGROUND

[0002] The floating ring graphite seal is a non-contact sealing device widely used in the sealing position of the main bearing cavity of an aero-engine, and the fluid flow through the small gap is used to limit the leakage by fluid resistance. In the aero-engine, the floating ring graphite seal is subjected to the complex working condition environment of high temperature, high pressure, high rotating speed, and one side of oil gas and the other side of air, which directly affects the working gap and leakage of the floating ring graphite seal. At present, the theoretical analysis of the performance of the floating ring graphite seal cannot fully consider the influence of the above complex working conditions, so it is difficult to completely reflect the working performance of the floating ring graphite seal in the aero-engine. Therefore, it is necessary to carry out the endurance performance test of the floating ring graphite seal under the working condition of the aero-engine, to correct the design according to the test results, and to verify the feasibility, reliability and durability of the use of the floating ring graphite seal in the aero-engine.

[0003] The structure of the conventional floating ring seal test device suspends the rotor structure of the floating ring seal test piece on the test table by cantilever, seals the two sides of the bearing cavity of the adapter section by the gap sealing form such as reverse thread structure, installs the floating ring seal test piece in the sealing mounting seat, simulates the assembly structure and interface size of the floating ring seal test piece in the engine through the installation structure, material, fitting size, etc. of the sealing mounting seat, and simulates the radial gap between the floating ring seal test piece and the sealing runway through the outer diameter size of the sealing runway. During the test, the adapter section main shaft is driven to rotate to the set rotating speed to simulate the rotating speed and rotating direction of the sealing runway in the legal and the middle. The air system supplies high temperature and high pressure gas to the inlet cavity to simulate the gas temperature and pressure of the environment in which the test piece is located in the engine.

[0004] The existing floating ring seal test device has the following problems:

[0005] 1. Due to the structure form of cantilever installation and the limitation of rotor dynamics, the length of the installation section of the floating ring seal test piece is limited, it is difficult to have enough space to install two floating ring seal test pieces under the condition of meeting the high rotating speed requirement, it is impossible to test two floating ring seal test pieces under the same working condition, which leads to long test period and low efficiency; in addition, the axial force generated by the sealing runway when the inlet cavity is pressurized is completely borne by the bearing of the adapter section, which leads to the failure of the bearing due to large load.

[0006] 2. The adapter section main shaft adopts solid shaft, when the inlet cavity is heated, the heat is easily transmitted along the axial direction through the main shaft, which leads to 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] The oil injection plate is arranged in the oil cavity, and an oil passage for connecting the annular groove and the oil inlet hole is arranged in the oil injection plate.

[0019] Further, the floating ring assembly comprises a floating ring mounting seat mounted on the inner wall of the shell, a fixing plate mounted on the floating ring mounting seat, and a floating ring sealing member clamped between the floating ring mounting seat and the fixing plate.

[0020] The floating ring sealing member is used for non-contact sealing with the outer wall of the annular convex plate.

[0021] Further, the floating ring sealing test device further comprises a bearing cavity sealing mechanism for sealing the bearing cavity of the bearing assembly, the bearing cavity sealing mechanism comprising a labyrinth sealing member arranged on the side of the bearing assembly close to the test cavity, and a dynamic pressure sealing member arranged on the side of the bearing assembly away from the test cavity.

[0022] The labyrinth sealing member is attached to the inner wall of the shell and is used for sealing one end of the bearing cavity by engaging with the stepped portion of the rotating shaft, and the dynamic pressure sealing member comprises a sealing dynamic ring sleeved on the outer wall of the rotating shaft, a sealing static ring arranged on the side of the sealing dynamic ring away from the bearing cavity and annularly arranged on the outside of the rotating shaft, and a static ring mounting seat sleeved on the outside of the sealing static ring and the sealing dynamic ring and used for mounting the sealing static ring, the static ring mounting seat being connected to the outer wall of the shell.

[0023] Further, the rotating shaft is provided with a first cooling hole and a second cooling hole which are both through in the axial direction, the first cooling hole is arranged on the central axis of the rotating shaft, and the second cooling hole is annularly arranged on the outside of the first cooling hole.

[0024] The inside of the end of the rotating shaft connected to the driving system is provided with a return flow cavity in communication with the first cooling hole and the second cooling hole, one end of the first cooling hole away from the return flow cavity is used for introducing cooling medium, and one end of the second cooling hole away from the return flow cavity is used for discharging cooling medium.

[0025] Further, the floating ring sealing test device further comprises a cooling mechanism arranged on the end of the rotating shaft away from the return flow cavity and used for cooling the rotating shaft, the cooling mechanism comprising a cooling isolation seat sealingly sleeved on the outer wall of the rotating shaft, a cooling mounting seat arranged around the end of the rotating shaft and sealingly sleeved on the outside of the cooling isolation seat, and a cooling supply member mounted on the cooling mounting seat and used for introducing cooling medium into the first cooling hole, the cooling isolation seat and the cooling mounting seat being both mounted on the static ring mounting seat.

[0026] A cooling cavity in communication with the second cooling hole is arranged between the cooling mounting seat and the cooling isolation seat.

[0027] Further, an air guide channel is arranged between the cooling mechanism and the bearing assembly, the air guide channel being arranged in the static ring mounting seat and the cooling isolation seat and being used for guiding the sealing air to the outer wall of the rotating shaft to prevent the cooling medium in the cooling cavity from leaking outward.

[0028] Further, the floating ring seal test device further comprises a monitoring mechanism for monitoring the test data in real time, the monitoring mechanism comprising a temperature measuring element for measuring temperature, a pressure measuring element for measuring pressure, a flow measuring element for measuring flow, and a vibration measuring element for monitoring vibration of the test cavity;

[0029] The vibration measuring element is arranged on both sides of the test piece and mounted on the shell.

[0030] According to another aspect of the present application, a detection system is also provided, comprising the floating ring seal test device described above.

[0031] The present application has the following advantages:

[0032] 1. The floating ring seal test device of the present application, by allowing the test part to pass through the accommodation cavity in the horizontal direction and be mounted on the shell, and allowing the test cavity to be arranged between the two symmetrically arranged floating ring parts to pass through the test medium, compared with the cantilever mounting method in the prior art, not only can the space for mounting the two floating ring parts be left, but also the axial force balance during pressurization of the test cavity can be realized under the condition of meeting high speed of the rotating shaft, the load borne by the bearing part during high pressure test is reduced, the risk of failure of the bearing part is reduced, and the stability and durability of the device are enhanced.

[0033] 2. The device, by designing the sealing runway as an integral structure with two symmetrically arranged annular convex plates, and allowing the two floating ring parts to be arranged one by one corresponding to the outer walls of the two annular convex plates and to be sealed in a non-contact manner, not only can the installation interface sizes of the two floating ring parts be ensured to be the same, but also the test conditions of the two floating ring parts can be ensured to be consistent, so that the device can simultaneously test the two floating ring parts under the same condition, effectively shorten the test period, and improve the test efficiency. In addition, the symmetric design of the two annular convex plates of the sealing runway can also realize axial force balance when facing high pressure difference conditions, and reduce the load borne by the bearing part during high pressure test.

[0034] 3. The rotating shaft can realize high speed through connection with the driving system, and the test cavity can pass through high temperature and high pressure gas, so that the complex working conditions of the aero-engine can be more accurately simulated, reliable data for evaluation of the sealing performance of the floating ring part can be provided, and the device is suitable for multi-scene test requirements of aero-engine sealing parts.

[0035] 4. The device can adapt to floating ring parts of different sizes, has strong universality, expands the test range, and provides strong support for research and development of aero-engine sealing technology.

[0036] In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described in detail below with reference to the drawings. 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 seal test device of the embodiment comprises a shell 100 and a test part 200, the shell 100 is provided with a containing cavity, and the test part 200 is arranged in the containing cavity in the horizontal direction and is installed on the shell 100. In the embodiment, the shell 100 is a hollow cuboid structure, and the shell 100 comprises a left end cover 101 and a right end cover 102 which are symmetrically arranged on both sides of the test cavity. Alternatively, the shell 100 can also be a hollow cylindrical structure. The test part 200 comprises a rotating shaft 201, two bearing members 202 and a test piece, the two bearing members 202 are axially spaced and arranged on the outer wall of the rotating shaft 201, the bearing member 202 is provided with a bearing cavity, and the test piece is arranged between the two bearing members 202 and is arranged on the outer wall of the rotating shaft 201. The left end cover 101 and the right end cover 102 of the shell 100 are provided with mounting holes corresponding in the horizontal direction, the rotating shaft 201 penetrates the containing cavity of the shell 100 through the mounting holes, one end of the rotating shaft 201 is installed on the left end cover 101 through one of the bearing members 202, and the other end of the rotating shaft 201 is installed on the right end cover 102 through the other bearing member 202, so that the support structure formed by the two symmetric bearing members 202 at both ends of the rotating shaft 201 can effectively share the load, the stress distribution is more uniform, the deflection is smaller, the stress amplitude under cyclic load is lower, and the service life is prolonged. The two ends of the rotating shaft 201 protrude from the outside of the shell 100, and one end of the rotating shaft 201 is used for connecting with the driving system for high-speed rotation to simulate the rotating speed of the aero-engine.

[0046] The test piece is arranged in the middle of the containing cavity, and the test piece comprises a sealing runway 203 arranged on the outer wall of the rotating shaft 201 and two floating ring members 204 arranged on the outer wall of the sealing runway 203 in the axial direction, the two floating ring members 204 are symmetrically arranged, one of the floating ring members 204 is installed on the inner wall of the left end cover 101, and the other floating ring member 204 is installed on the inner wall of the right end cover 102. The sealing runway 203 comprises two annular convex plates 2032 arranged on both ends of the sealing runway 203, the two annular convex plates 2032 are symmetrically arranged at both ends of the sealing runway 203, the two floating ring members 204 are correspondingly arranged with the two annular convex plates 2032, and the floating ring member 204 is used for non-contact sealing with the outer wall of the annular convex plate 2032. Thus, the test piece can form a symmetric structure in the containing cavity of the shell 100 along the vertical direction with the middle of the sealing runway 203 as the axis. The sealing runway 203 forms a test cavity 300 between the two floating ring members 204 and the shell 100 through the two annular convex plates 2032, and the shell 100 is provided with a medium hole communicating with the test cavity 300, and the test medium can be introduced into the test cavity 300 through the medium hole to simultaneously test the performance of the two floating ring members 204. Preferably, the medium hole is arranged on the shell 100 above the rotating shaft 201, and the test medium is high-temperature and high-pressure gas.

[0047] Therefore, the floating ring seal test device of the present application can leave space for installing the double floating ring members 204 by making the test part 200 penetrate into the accommodating cavity along the horizontal direction and being installed on the shell 100, and making the test cavity 300 be arranged between the double floating ring members 204 arranged symmetrically to be communicated with the test medium. Compared with the cantilever installation mode in the prior art, not only the space for installing the double floating ring members 204 can be left, but also the axial force balance of the test cavity 300 under pressure can be realized under the working condition of high rotation speed of the rotating shaft 201, the load borne by the bearing member 202 under high pressure test is reduced, the risk of failure of the bearing member 202 is reduced, and the stability and durability of the device are enhanced.

[0048] As shown in Figure 1 and Figure 2 , the sealing track 203 is a symmetrical structure of one piece, and the sealing track 203 includes a track ring 2031 for interference fitting on the outer wall of the rotating shaft 201 and two annular convex plates 2032 arranged at the axial ends of the track ring 2031. The two annular convex plates 2032 are symmetrically arranged at the two ends of the track ring 2031, and the two annular convex plates 2032 are integrally formed with the track ring 2031. The annular convex plate 2032 is annularly arranged on the outer wall of the track ring 2031 and extends in the radial direction away from the track ring 2031. Integrally forming the two annular convex plates 2032 with the track ring 2031 can ensure that the outer diameters of the two annular convex plates 2032 are the same, thereby ensuring that the interface sizes of the sealing track 203 of the two floating ring members 204 are the same during the test, and the radial fit clearance between the floating ring member 204 and the sealing track 203 can be simulated by the outer diameter of the annular convex plate 2032. Therefore, the sealing track 203 is integrally formed with the track ring 2031 and the two annular convex plates 2032 in a symmetrical structure, and the two floating ring members 204 are correspondingly arranged on the outer walls of the two annular convex plates 2032 and are non-contact sealed. Not only can the installation interface sizes of the double floating ring members 204 be ensured to be the same, but also the interface sizes, materials, surface coatings and other counterpart conditions of the sealing track 203 of the floating ring member 204 in the aero-engine can be accurately simulated. In addition, the test working conditions of the double floating ring members 204 can be consistent, the device can simultaneously test the double floating ring members 204 under the same working condition, the test period can be effectively shortened, and the test efficiency can be improved. Furthermore, the symmetrical design of the two annular convex plates 2032 of the sealing track 203 can realize axial force balance under high pressure difference working condition, and reduce the load borne by the bearing member 202 under high pressure test.

[0049] As shown in Figure 1 and Figure 2As shown, the edge of the annular convex plate 2032 is provided with a reverse concave structure 2033 extending in the direction towards the other annular convex plate 2032, the reverse concave structure 2033 is arranged at one end of the annular convex plate 2032 away from the raceway ring 2031, and a ring groove 2034 is formed in the reverse concave structure 2033, the opening of the ring groove 2034 is arranged in the horizontal direction towards the direction away from the other annular convex plate 2032. By feeding the lubricating oil into the ring groove 2034, the cooling of the sealing raceway 203 can be realized, and the ring groove 2034 is arranged at the position close to the sealing surface of the sealing raceway 203 and the floating ring member 204, so that the lubricating oil can form a stable cooling oil film in the high temperature area on the side of the groove close to the sealing surface under the centrifugal force of the sealing raceway 203, so as to cool the sealing surface, thereby simulating the cooling condition of the environment of the floating ring member 204 in the aero-engine. The design of the reverse concave structure 2033 of the annular convex plate 2032 can simulate the interface structure of the floating ring member 204 in the aero-engine, so as to ensure that the installation condition of the floating ring member 204 under test is the same as the actual condition. In addition, arranging the ring groove 2034 in the reverse concave structure 2033 can not only avoid the splashing of the lubricating oil and reduce the consumption of the lubricating oil, but also can strengthen the heat dissipation of the lubricating oil in the ring groove 2034 through the airflow vortex effect, thereby improving the cooling efficiency.

[0050] As shown in Figure 1 The axial ends of the test piece are respectively surrounded by the shell 100 to form a lubricating oil cavity 400, the shell 100 is provided with an oil inlet hole 401 above the rotating shaft 201, and the shell 100 is provided with an oil outlet hole 402 below the rotating shaft 201 and communicating with the lubricating oil cavity 400. The oil injection plate 403 is installed in the lubricating oil cavity 400, and the oil injection plate 403 is provided with an oil channel 4031 for communicating the ring groove 2034 and the oil inlet hole 401. Thus, the lubricating oil flows into the lubricating oil cavity 400 through the oil inlet hole 401, the oil channel 4031 in the oil injection plate 403 and the sliding groove of the sealing raceway 203 in sequence, and then is discharged through the oil outlet hole 402 of the shell 100, so as to realize the circulating cooling of the lubricating oil, and the oil injection pressure is controlled to simulate the oil-gas environment and the oil injection flow rate of the bearing cavity side of the floating ring member 204 in the aero-engine, thereby ensuring that the test working conditions of the double-piece floating ring member 204 are consistent.

[0051] As shown in Figure 1As shown, the two-piece floating ring member 204 is arranged vertically symmetrically between the bearing member 202 supported at both ends and in the accommodating cavity of the housing 100, and includes a floating ring mounting seat 2041, a fixed plate 2042 and a floating ring seal member 2043. The floating ring mounting seats 2041 of the two floating ring members 204 are symmetrically arranged in the accommodating cavity, one of which is fixedly connected with the inner wall of the left end cover 101 of the housing 100, and the other is fixedly connected with the inner wall of the right end cover 102 of the housing 100. The fixed plate 2042 is arranged on the side of the floating ring mounting seat 2041 away from the inner wall of the housing 100. The fixed plate 2042 and the floating ring mounting seat 2041 are internally provided with clamping grooves, the floating ring seal member 2043 is clamped in the clamping grooves, and the floating ring seal member 2043 is pressed on the floating ring mounting seat 2041 along the axial direction through the fixed plate 2042 to realize positioning of the floating ring seal member 2043, so that the lower ends of the two floating ring seal members 2043 are arranged in one-to-one correspondence with the outer walls of the two annular convex plates 2032 of the sealing runway 203 and are sealed in a non-contact manner. Through the design of the floating ring mounting seat 2041 and the fixed plate 2042, the installation structure, interface size, material and other conditions of the floating ring seal member 2043 in the aero-engine can be simulated. The test cavity 300 is located between the two-piece floating ring seal member 2043, so that by introducing a set of high-temperature and high-pressure gas into the test cavity 300, the high-temperature and high-pressure gas test conditions of the two floating ring seal members 2043 can be ensured to be the same during the test, and the simulation of the gas temperature and pressure of the environment in which the floating ring seal member 2043 is located in the aero-engine can be realized.

[0052] As Figure 1 and Figure 3As shown, the floating ring seal test device further comprises bearing cavity sealing mechanisms 500 for sealing the bearing cavities at both ends of the bearing members 202, the bearing cavity sealing mechanisms 500 comprising labyrinth seals 501 and dynamic pressure seals 502, the labyrinth seals 501 being arranged on the side of the bearing members 202 close to the test cavity 300 and in the accommodating cavity of the housing 100, and the dynamic pressure seals 502 being arranged on the side of the bearing members 202 away from the test cavity 300 and outside the housing 100. Specifically, the labyrinth seals 501 are arranged between the sealing runways 203 and the bearing members 202, and the labyrinth seals 501 comprise first stepped structures 5011 arranged on the outer wall of the rotating shaft 201 and second stepped structures 5012 arranged in sealing contact with the inner wall of the right end cover 102 of the housing 100, the first stepped structures 5011 being interference-fitted on the outer wall of the rotating shaft 201 or being integrated with the rotating shaft 201, and the second stepped structures 5012 being annularly arranged outside the rotating shaft 201 and sealingly connected with the outer wall of the rotating shaft 201, the sealing runways 203 being axially limited by the two first stepped structures 5011 between the two bearing members 202. The second stepped structures 5012 and the second stepped structures 5012 form stepped sealing engagement surfaces to seal one end of the bearing cavities of the bearing members 202, and the labyrinth seals 501 can achieve lower leakage by changing the flow direction of the leaked gas through multiple deflections, thereby reducing the influence of high-temperature gas leakage on the operation and service life of the bearing members 202.

[0053] The dynamic pressure seals 502 comprise sealing moving rings 5021, sealing stationary rings 5022, and stationary ring mounting seats 5023, the sealing moving rings 5021 being interference-fitted on the outer wall of the rotating shaft 201 to rotate synchronously with the rotating shaft 201, the sealing stationary rings 5022 being fitted on the outer wall of the rotating shaft 201 and arranged on the side of the sealing moving rings 5021 away from the bearing cavities, and the stationary ring mounting seats 5023 being annularly arranged outside the sealing stationary rings 5022 and the sealing moving rings 5021 and fixedly connected with the outer wall of the housing 100, so that a stable micron-level gas film is formed between the sealing moving rings 5021 and the sealing stationary rings 5022 to isolate the sealing moving rings 5021 from the sealing stationary rings 5022, thereby enabling the sealing of the end of the bearing cavities of the bearing members 202 away from the test member to be reliably operated for a long time under low leakage. Preferably, the dynamic pressure seals 502 further comprise elastic members mounted in the stationary ring mounting seats 5023, and the elastic members are used to press the sealing moving rings 5021 and the sealing stationary rings 5022 in the axial direction by the elastic force of the elastic members, so that a stable and reliable sealing surface is formed between the sealing moving rings 5021 and the sealing stationary rings 5022 to ensure the sealing effect. Preferably, the elastic members are springs. Preferably, the end surface of the sealing moving ring 5021 is provided with a fluid dynamic pressure groove, and the fluid dynamic pressure groove is an outwardly-numbered spiral groove.

[0054] As Figure 1 and Figure 3As shown, the rotating shaft 201 is provided with an inner-outer double-layer hollow structure. Specifically, the rotating shaft 201 is provided with a first cooling hole 2011 and a second cooling hole 2012 penetrating through the rotating shaft 201 along the axial direction. The first cooling hole 2011 is arranged at the center axis of the rotating shaft 201, and the second cooling hole 2012 is arranged outside the first cooling hole 2011. The end of the rotating shaft 201 connected with the driving system is sealingly connected with a cover plate. The cover plate and the end of the rotating shaft 201 are provided with a backflow cavity 2013 in communication with the first cooling hole 2011 and the second cooling hole 2012. The end of the first cooling hole 2011 away from the backflow cavity 2013 is used for introducing the cooling medium, and the end of the second cooling hole 2012 away from the backflow cavity 2013 is used for discharging the cooling medium. Thus, after the cooling medium is introduced into the first cooling hole 2011 away from the backflow cavity 2013 of the rotating shaft 201, the cooling medium can flow to the backflow cavity 2013 along the first cooling hole 2011. The cooling medium blocked by the cover plate flows into the second cooling hole 2012 and is discharged from the end of the rotating shaft 201 away from the backflow cavity 2013 through the second cooling hole 2012, thereby forming the flow cooling of the cooling medium in the rotating shaft 201.

[0055] As Figure 1 and Figure 3As shown, specifically, the floating ring seal test device further comprises a cooling mechanism 600 arranged at the end of the rotating shaft 201 away from the backflow cavity 2013, and connected with 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 comprises a cooling isolation seat 601, a cooling mounting seat 602 and a cooling component 603. The cooling isolation seat 601 is sealingly sleeved on the outer wall of the rotating shaft 201, the cooling mounting seat 602 is arranged around the end of the rotating shaft 201 and sealingly sleeved on the outside of the cooling isolation seat 601, and the cooling isolation seat 601 and the cooling mounting seat 602 are both mounted on the static ring mounting seat 5023. A cooling cavity 604 in communication with the second cooling hole 2012 is arranged between the cooling mounting seat 602 and the cooling isolation seat 601. The cooling component 603 is mounted on the cooling mounting seat 602 and in communication with the first cooling hole 2011 to introduce cooling medium into the first cooling hole 2011. A certain gap is arranged between the cooling component 603 and the inner wall of the first cooling hole 2011 to avoid rotation of the cooling component 603 with the rotating shaft 201. Preferably, the cooling medium is cooling water. Preferably, a drain hole in communication with the cooling cavity 604 is arranged in the cooling mounting seat 602 to drain the cooling water in the cooling cavity 604 to the outside. In use, the external cooling water is injected into the first cooling hole 2011 of the rotating shaft 201 through the cooling component 603, flows into the backflow cavity 2013 along the first cooling hole 2011, flows into the second cooling hole 2012 after being blocked by the cover plate, and flows into the cooling cavity 604 through the second cooling hole 2012 for recycling. The cooling water recycled in the cooling cavity 604 is drained to the external circulation system through the drain hole, cooled, filtered and pressurized through the circulation system, and then introduced into the cooling component 603 to inject the cooling water into the rotating shaft 201 to form a circulating water flow for cooling. For the high-temperature working condition of 300 DEG C or above required to be achieved by the floating ring seal 2043, the rotating shaft 201 is cooled in this way, which can effectively reduce the shaft center temperature of the rotating shaft 201, avoid deformation of the rotating shaft 201 caused by uneven thermal expansion, and facilitate cooling of the bearing 202 at both ends of the rotating shaft 201, thereby prolonging the service life of the bearing 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 in high-speed test working condition.

[0056] As Figure 3As shown, the cooling mechanism 600 and the bearing piece 202 are further provided with an air guide channel 700, which is arranged in the static ring mounting seat 5023 and the cooling isolation seat 601, and is in communication with the outer wall of the rotating shaft 201. By guiding the pressurized sealing gas to the outer wall of the rotating shaft 201 through the air guide channel, the sealing gas can seal between the cooling cavity 604 and the sealing static ring 5022, prevent the oil gas in the bearing cavity from leaking outward, and prevent the cooling water in the cooling cavity 604 from entering the bearing cavity, thereby improving the operating environment of the bearing piece 202 and enabling the bearing piece 202 to realize long-time reliable operation under high-parameter working conditions.

[0057] The floating ring seal test device of the present application enables the rotating shaft 201 to rotate at a set rotating speed by driving of the driving system, simulates the rotating speed and rotating direction of the sealing track 203 in the aero-engine, simulates the gas temperature and pressure of the environment in which the floating ring seal piece 2043 is located in the aero-engine by inputting high-temperature and high-pressure gas into the test cavity 300, simulates the counterpart conditions such as the interface size, material and surface coating of the sealing track 203 of the floating ring seal piece 2043 in the aero-engine through the structural design of the sealing track 203, simulates the cooperation conditions such as the mounting structure, interface size and mounting material of the floating ring seal piece 2043 in the engine through the design of the floating ring mounting seat 2041 and the fixed plate 2042, simulates the oil gas environment and oil injection flow rate of the bearing cavity side of the floating ring seal piece 2043 in the aero-engine through the flow path design in the oil cavity 400 between the main end cover and the right end cover 102 of the shell 100 and the floating ring piece 204 and the control of the oil injection pressure, and thus the test working conditions in which the double-piece floating ring seal piece 2043 is located can be ensured to be consistent.

[0058] As shown in the drawings, Figure 4As shown, the floating ring seal test device further comprises a monitoring mechanism for real-time monitoring of test data. The monitoring mechanism comprises 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 cavity 300. The temperature measuring element, the pressure measuring element, and the flow measuring element are arranged at the test cavity 300 and / or the bearing cavity, and the vibration measuring element is arranged on both sides of the test piece and mounted on the shell 100, so as to realize real-time monitoring of the temperature of the test cavity 300, the pressure of the test cavity 300, the leakage of the test cavity 300, and the temperature of the bearing cavity. Preferably, the flow measuring element uses a flow meter, the temperature measuring element uses a temperature sensor, the pressure measuring element uses a pressure sensor, and the vibration measuring element uses a vibration sensor. The temperature measuring element, the pressure measuring element, the flow measuring element, and the vibration measuring element are electrically connected to a data acquisition element for collecting monitoring data. Preferably, the monitoring mechanism is provided with an over-limit alarm. When the monitoring parameters such as temperature, pressure, and vibration exceed the upper limit alarm value, automatic parking can be realized through the data acquisition element to ensure the safety of the device in high-parameter working conditions. Through synchronous high-frequency collection of multiple physical quantities during the test of the floating ring seal 2043, the monitoring capability is greatly improved.

[0059] According to another aspect of the present application, a detection system is also provided, comprising the floating ring seal test device. The detection system further comprises a driving system, a gas supply device, an oil supply device, and a cooling device. Specifically, one end of the rotating shaft 201 is connected to the cooling device through the cooling mechanism 600, and the other end of the rotating shaft 201 is connected to the driving system arranged outside the shell 100 through a flexible coupling. Preferably, the driving system uses a motor to drive the rotating shaft 201 to rotate at a high speed. In the present embodiment, the motor can adapt to a high-speed working condition of more than 30000r / min. Preferably, the motor is connected to a frequency converter. The flexible coupling uses a bellows coupling, which can absorb the vibration and impact during the operation of the rotating shaft 201, thereby prolonging the service life of the floating ring seal test device.

[0060] The gas supply device uses a high-temperature and high-pressure gas heater as a gas source to supply gas to the test cavity 300, so as to simulate the gas temperature and pressure of the environment in which the floating ring seal 2043 is located in the aero-engine. The high-temperature and high-pressure gas heater has a temperature automatic control device, and the gas pressure is controlled by the pressure sensor at the test cavity 300, so as to ensure that the gas pressure in the test cavity 300 meets the requirements. The oil supply device uses an oil pump to supply oil to the inside of the test part 200, so as to simulate the oil environment in which the floating ring seal 2043 is located in the aero-engine.

[0061] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

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 runway (203), and the housing (100) together form a test chamber (300) for introducing the test medium.

2. The floating ring sealing test device according to claim 1, characterized in that, The edge of the annular convex plate (2032) is provided with a concave structure (2033) extending in the direction toward the other annular convex plate (2032), and 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 in a direction away from the other annular protrusion (2032).

3. The floating ring sealing test device according to claim 2, 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).

4. 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).

5. 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).

6. The floating ring sealing test device according to claim 5, 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.

7. The floating ring sealing test device according to claim 6, 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).

8. The floating ring sealing test device according to claim 7, 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.

9. 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).

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

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