Method for measuring abrasion loss of circumferential floating ring seal for aero-engine

Abstract

The invention discloses a method for measuring the abrasion loss of a circumferential floating ring seal for an aero-engine, and the method comprises the steps: obtaining a first surface appearance of a circumferential sealing surface before a floating ring or a floating ring seal test piece is used or tested; unfolding the first surface appearance to obtain a first surface profile; after the floating ring or the floating ring sealing test piece is used or tested, a second surface appearance of the circumferential sealing surface is obtained; unfolding the second surface appearance to obtain a second surface profile; wear depth data and wear area data are obtained based on the first surface profile and the second surface profile; based on the wear depth data and the wear area data, a wear volume and / or a wear mass is calculated. The measuring method is used for solving the problems that in the prior art, a measuring method for the abrasion loss of the floating ring seal is single, low in precision and large in error, a new abrasion loss measuring method except a traditional weighing method is provided, and the purposes of reducing external interference, improving the measuring precision of the abrasion loss of the circumferential floating ring seal for the aero-engine and reducing the measuring error are achieved.

Description

Technical Field

[0001] The invention relates to the technical field of seal testing related to aircraft engines, and in particular to a method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine. Background Art

[0002] The floating ring seal is a new type of shaft end seal with a smaller sealing gap and better self-centering function. It has received extensive attention in the field of aero-engine sealing. The working principle of the floating ring seal is that during normal operation, the floating ring seal separates the sealing ring and the runway surface through a rigid fluid membrane to prevent gas leakage. The sealing end face is attached to the inner side of the shell under the combined action of the spring and the gas pressure difference to prevent radial gas leakage.

[0003] When the floating ring seal works normally, there is friction and wear between its end face and the shell, but it does not contact with its counterpart (rotor). Therefore, the life of the floating ring seal is closely related to friction and wear. In addition, the friction and wear between the inner surface of the floating ring seal and the runway has a significant restriction on the life of the seal. The friction and wear in this area will cause the leakage to exceed the standard, and in severe cases, it will even cause the floating ring seal to fail.

[0004] In the prior art, the wear measurement of the sealing ring is mostly for the wear measurement of the end face seal, and the measurement method is basically completed by using a micrometer, which is not suitable for the wear measurement of the inner surface circumference of the floating ring. In addition, when using a micrometer to measure the wear, it is often affected by the different clamping forces and clamping angles between the micrometer and the sealing surface, which will produce a large error in the measurement of the seal wear.

[0005] In the prior art, the wear measurement of circumferential seals (cylindrical seals) is limited to the weighing method. This measurement method will have different effects due to different materials. For soft materials, especially graphite materials commonly used in circumferential floating ring seals of aircraft engines, due to the good adsorption of graphite materials, a certain amount of wear medium will be adsorbed during the wear process, resulting in inaccurate wear weight difference. In addition, for the seal form used in aircraft engines, especially under the oil-gas two-phase working condition, if the wear is directly cleaned and dried in a drying oven before and after wear, there will always be residual test medium in the pores of the soft material, and the accurate wear amount cannot be obtained, and even the phenomenon of "the more you wear, the heavier" may occur. In addition, since the traditional weighing method for measuring wear requires the disassembly, cleaning and drying of the floating ring before and after wear, this process is extremely affected by human factors and environmental factors, which can easily lead to inaccurate measurement results and large errors, affecting the subsequent research process.

[0006] In summary, the test methods for floating ring seal wear in the prior art are relatively simple, and most of them are aimed at measuring the wear of conventional end face seals. Therefore, the prior art has great limitations in measuring the wear of circumferential floating ring seals for aircraft engines. Summary of the invention

[0007] The present invention provides a method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine, so as to solve the problem that the method for measuring the wear amount of a floating ring seal in the prior art is relatively single, has low precision and large error, and provides a new test method for obtaining the wear amount by breaking through the traditional single weighing method, so as to improve the wear amount measurement accuracy of a circumferential floating ring seal for an aircraft engine and reduce the measurement error.

[0008] The present invention is achieved through the following technical solutions:

[0009] A method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine, comprising:

[0010] Before the floating ring or floating ring seal test piece is used or tested, a first surface morphology of the circumferential sealing surface is obtained;

[0011] Expanding the first surface topography into a plane to obtain a first surface profile;

[0012] After the floating ring or floating ring seal test piece is used or tested, a second surface morphology of the circumferential sealing surface is obtained;

[0013] unfolding the second surface topography into a plane to obtain a second surface profile;

[0014] Based on the first surface profile and the second surface profile, obtaining wear depth data and wear area data;

[0015] Based on the wear depth data and the wear area data, the wear volume and / or the wear mass are calculated.

[0016] In view of the problem that the measuring method of floating ring seal wear in the prior art is relatively simple, with low accuracy and large error, the present invention proposes a measuring method for the wear of a circumferential floating ring seal for aircraft engines. The measuring object of this method can be a floating ring in formal service or a floating ring seal test piece. When the measuring object is a floating ring in formal service, the first surface morphology and the second surface morphology are obtained for the floating ring before and after use respectively; when the measuring object is a floating ring seal test piece, the first surface morphology and the second surface morphology are obtained for the floating ring seal test piece before and after the test respectively. Since the measuring object of this application is a floating ring for aircraft engines, the sealing surface is a circumferential sealing surface, so this method needs to unfold the first surface morphology and the second surface morphology into a plane respectively, convert the circumferential curved surface information thereon into plane information, and then obtain the first surface contour and the second surface contour respectively, so as to obtain the surface morphology on the circumferential sealing surface before and after use or before and after the test respectively; then, the surface morphology obtained twice is compared and analyzed to obtain the data of wear depth and wear area, and finally calculate the wear volume and wear mass.

[0017] This application abandons the technical route of measuring wear by weighing method in the prior art, and proposes a new floating ring seal wear measurement method. The proposed measurement method is not affected by the material, and will not cause serious deviation in wear measurement due to the adsorption of graphite material of the circumferential floating ring of the aircraft engine. Now the measurement accuracy of the circumferential floating ring wear for aircraft engines is improved; at the same time, this application also avoids the need to disassemble, clean and dry the floating ring before and after wear. The complex operation process effectively reduces the interference of human factors and environmental factors, and is also conducive to improving the measurement accuracy and reducing the measurement error. In addition, this application converts the cylindrical wear information into the end face wear problem, which greatly simplifies the process and difficulty of the three-dimensional surface morphology analysis of the seal.

[0018] Further, the first surface morphology or the second surface morphology is obtained by the following method:

[0019] The surface morphology of the circumferential sealing surface is replicated by using the solidified molded object, and the morphology replicated on the surface of the solidified molded object is used as the first surface morphology or the second surface morphology.

[0020] Obviously, both the first surface morphology and the second surface morphology can be obtained by the method of this solution, but the objects of action are the circumferential sealing surface of the floating ring before and after use or testing. This solution creatively uses a solidified molded object to achieve the reproduction of the surface morphology of the circular sealing surface, which is convenient for efficiently and accurately converting the cylindrical surface information into the end surface information, which is conducive to the subsequent effective extraction of the surface contour.

[0021] It should be noted that the cured molded article in this scheme can be any material in the prior art that has good microscopic surface morphology expression performance and good ductility and a smooth surface after molding. Technical personnel in this field can choose any suitable material to achieve its function according to actual needs and based on the prior art, such as resin materials, polymers, silicone rubber materials that can replicate the surface morphology; in addition, the cured molded article in this scheme can be organic or inorganic.

[0022] Preferably, the cured molded product is a resin material, which has the characteristics of good ductility, smooth surface after molding, soft texture, etc., which is conducive to accurately replicating the microscopic surface morphology and maintaining stable morphology after unfolding to a plane.

[0023] Furthermore, the method for obtaining the first surface profile includes: unfolding the solidified molded object with the first surface morphology along the circumferential direction to obtain a first end face, obtaining protrusion information on the first end face, and obtaining the first surface profile;

[0024] The method for obtaining the second surface profile includes: unfolding the solidified molded object with the second surface morphology along the circumferential direction to obtain the second end face, acquiring the protrusion information on the second end face, and obtaining the second surface profile.

[0025] In this solution, the protrusions obtained by replicating the surface of the solidified molded object correspond to the wear on the sealing surface of the floating ring; therefore, this solution can obtain the first surface profile and the second surface profile respectively by obtaining the protrusion information of the first end face and the second end face.

[0026] Furthermore, by scanning with a three-dimensional ultra-depth-of-field surface profiler or a line laser scanner, the protrusion information on the first plane and the second plane is obtained, and then the first surface profile and the second surface profile are obtained.

[0027] Furthermore, the protrusion information includes the height, contour curve and projection area of ​​all protrusions. Among them, the height of the protrusion can represent the wear depth; the contour curve of the protrusion can represent the morphology of each wear area; the projection area of ​​the protrusion can represent the size of the wear range. Based on these three parameters, the wear changes before and after use or testing can be clearly determined.

[0028] Further, the method for obtaining wear depth data includes:

[0029] Extracting the protrusion height data in the first surface contour and the second surface contour respectively;

[0030] The first surface profile and the second surface profile are registered, and the protrusion heights of each area are subtracted to obtain wear depth data.

[0031] This solution can be understood as extracting the wear depth data before and after use or testing, and then aligning the first surface profile before use or testing with the second surface profile after use or testing, so as to obtain which areas are areas of new wear due to use or testing, and which areas are areas where wear is aggravated due to use or testing. By comparing the depth of each wear area before use or testing, the wear depth data caused by the current use or test can be obtained.

[0032] Further, the method for obtaining the wear area data includes:

[0033] calibrating a wear area based on the wear depth data;

[0034] Acquire image data of each wear area on the first surface contour and the second surface contour respectively, and perform edge image processing to obtain a first wear area contour data set and a second wear area contour data set respectively;

[0035] The first wear region profile data set is compared with the second wear region profile data set to obtain the wear area of ​​each wear region.

[0036] This solution first calibrates all the wear areas based on the wear depth data, and then obtains the initial area images before and after the wear. Based on the edge image processing technology, the first wear area contour data set and the second wear area contour data set can be obtained, which correspond to the damaged area contour data before the wear and the damaged area contour data after the wear, respectively. By comparing the damaged area contour data before and after the wear, the wear area generated by the use or test can be obtained. In this solution, based on the mature edge image processing technology in the prior art, its purpose is to process the irregular wear area into a roughly regular shape, so that the wear width and wear length of the floating ring seal can be easily obtained, and then the change of the wear area can be obtained, which is convenient for calculating the wear area.

[0037] Furthermore, the method for calculating the wear volume includes: matching the obtained wear depth data and the wear area data, and multiplying the corresponding wear depth data by the corresponding wear area data, summing them, and obtaining the wear volume. This solution can calculate the wear area of ​​each wear area, the wear depth corresponding to each wear area, obtain the wear volume of each wear area, and finally obtain the total wear volume.

[0038] Further, the method for calculating the wear mass includes: multiplying the wear volume by the density of the floating ring or the floating ring seal test piece to obtain the wear mass.

[0039] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0040] 1. The present invention discloses a method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine, which abandons the technical route of measuring the wear amount by weighing method in the prior art and proposes a new method for measuring the wear amount of a floating ring seal. The proposed method breaks through the limitations of the traditional weighing method and is not affected by uncertain factors such as human factors, environment, and cleaning weighing. It is also not affected by the material and will not cause serious deviations in the wear amount measurement due to the adsorption of the graphite material of the circumferential floating ring of the aircraft engine. The measurement accuracy of the circumferential floating ring of the aircraft engine is now improved.

[0041] 2. Compared with the traditional weighing method, the method for measuring the wear of the circumferential floating ring seal for an aircraft engine of the present invention avoids the need to disassemble, clean and dry the floating ring before and after wear, and effectively reduces the interference of human and environmental factors, which is also conducive to improving the measurement accuracy and reducing the measurement error.

[0042] 3. The present invention provides a method for measuring the wear of a circumferential floating ring seal for an aircraft engine. The solidified molded article is used to replicate the surface morphology of a circular sealing surface, which is convenient for efficiently and accurately converting cylindrical information into end face information, and is beneficial for the subsequent effective extraction of the surface contour. At the same time, the solidified molded article can be used to convert cylindrical wear information into end face wear problems, which greatly simplifies the process and difficulty of three-dimensional surface morphology analysis of seals.

[0043] 4. The present invention provides a method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine, which can quickly obtain wear depth information and wear profile area, and can easily obtain wear volume, and obtain accurate wear quality in combination with the density of the floating ring seal material. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of this application, and do not constitute a limitation of the embodiments of the present invention. In the drawings:

[0045] Figure 1 It is a schematic diagram of a flow chart of a specific embodiment of the present invention;

[0046] Figure 2 It is a structural schematic diagram of a test device in a specific embodiment of the present invention;

[0047] Figure 3 It is a schematic diagram of the scraping and rubbing parts in the test device of a specific embodiment of the present invention;

[0048] Figure 4 It is a schematic diagram of another implementation of the scraping and rubbing component in the test device of a specific embodiment of the present invention;

[0049] Figure 5 is a schematic diagram of a positioning component in a test device according to a specific embodiment of the present invention;

[0050] Figure 6 It is a schematic diagram of a power component in a test device according to a specific embodiment of the present invention.

[0051] 12-housing, 13-floating ring fixture, 14-cam, 15-protrusion, 16-support saddle, 17-test bench;

[0052] 21- gland, 22- sleeve, 23- elastic member;

[0053] 32-spindle, 33-end cover, 34-vent, 35-coupling, 36-motor, 37-upper housing, 38-lower housing. DETAILED DESCRIPTION

[0054] In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention is further described in detail below in conjunction with the examples and the accompanying drawings. The schematic embodiments of the present invention and the description thereof are only used to explain the present invention and are not intended to limit the present invention. In the description of the present application, it should be understood that the orientation or positional relationship indicated by terms such as "front", "rear", "left", "right", "up", "down", "vertical", "horizontal", "high", "low", "inside", "outside", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present application.

[0055] Embodiment 1:

[0056] like Figure 1 The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine shown in the figure comprises the following steps:

[0057] S1. Before the floating ring or floating ring seal test piece is used or tested, a first surface morphology of the circumferential sealing surface is obtained; specifically, the surface morphology of the circumferential sealing surface at this time is replicated by using the solidified molding as the first surface morphology;

[0058] S2, unfolding the first surface topography into a plane to obtain a first surface profile;

[0059] S3. After the floating ring or floating ring seal test piece is used or tested, a second surface morphology of the circumferential sealing surface is obtained; specifically, the surface morphology of the circumferential sealing surface at this time is replicated with a new solidified molding as the second surface morphology;

[0060] S4, unfolding the second surface topography into a plane to obtain a second surface profile;

[0061] S5. Based on the first surface profile and the second surface profile, use existing instruments such as a three-dimensional ultra-depth surface profiler and / or a line laser scanner to scan and compare the scanning results of the first surface profile and the second surface profile to obtain depth information of the floating ring before and after friction and wear, and further obtain a wear depth value;

[0062] In addition, the surface profile information of the replicated organic solidified molding is measured, and the wear profile area information of the floating ring is obtained by combining the actual friction and wear conditions of the floating ring seal and the geometric structure parameters of the floating ring seal. The wear profile area is processed to obtain the wear area.

[0063] S6. Calculating the wear volume and / or wear mass based on the wear depth data and the wear area data;

[0064] The method for calculating the wear volume includes: matching the obtained wear depth data and the wear area data, and multiplying the corresponding wear depth data by the corresponding wear area data, summing them, and obtaining the total wear volume.

[0065] The method for calculating the wear mass includes: multiplying the total wear volume by the density of the floating ring or floating ring seal test piece to obtain the wear mass.

[0066] The cured molded product in this embodiment is made of resin material, preferably a resin material for a molded body, such as the resin material disclosed in Chinese patent CN114096571B.

[0067] Preferably, the method of using a solidified molded object to replicate the surface morphology of the circumferential sealing surface can be carried out by sticking the unsolidified solidified molded object to the surface of the circumferential sealing surface and pressing it, waiting for it to solidify; or the solidified molded object in a flowing state can be injected into the interior of the floating ring structure to achieve the replication of the surface morphology; other methods of replicating the surface morphology that can be implemented by technical personnel in this field can also be used.

[0068] This embodiment converts cylindrical information into end face information, uses existing technical means to measure the three-dimensional morphology of the sealing surface, and obtains wear depth information and wear contour area by comparing and analyzing the three-dimensional surface morphology before and after wear, and finally obtains the wear amount of the floating ring seal.

[0069] In a more preferred embodiment, the method for obtaining wear depth data includes: extracting the protrusion height data in the first surface contour and the second surface contour respectively; aligning the first surface contour and the second surface contour, and subtracting the protrusion height of each area respectively to obtain the wear depth data.

[0070] In a more preferred embodiment, the method for obtaining wear area data includes: calibrating the wear area based on the wear depth data; respectively obtaining image data of each wear area on the first surface contour and the second surface contour, and performing edge image processing to obtain a first wear area contour data set and a second wear area contour data set, respectively; comparing the first wear area contour data set with the second wear area contour data set to obtain the wear area of ​​each wear area.

[0071] In a more preferred embodiment, point cloud data representing the three-dimensional morphology can be scanned and obtained, divided into grids, and then the average wear depth is calculated based on each grid, and then the wear volume corresponding to each wear area is calculated.

[0072] Embodiment 2:

[0073] A method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine, based on Example 1:

[0074] The method for obtaining the first surface profile comprises: unfolding the solidified molded object with the first surface morphology along the circumferential direction to obtain a first end face, obtaining protrusion information on the first end face, and obtaining the first surface profile;

[0075] The method for obtaining the second surface profile includes: unfolding the solidified molded object with the second surface morphology along the circumferential direction to obtain the second end face, acquiring the protrusion information on the second end face, and obtaining the second surface profile.

[0076] In this embodiment, the first surface profile and / or the second surface profile is obtained by scanning with a three-dimensional ultra-depth surface profiler or a line laser scanner.

[0077] The protrusion information obtained in this embodiment includes the height, contour curve and projection area of ​​all protrusions.

[0078] Preferably, the wear depth of this embodiment is obtained by the following method:

[0079] The surface of the unfolded organic cured molding is scanned radially using a three-dimensional ultra-depth surface profiler and a line laser scanner to obtain the corresponding depth information images before and after the floating ring wear. According to the initial depth information image, the affine transformation method is used for alignment to obtain the processed depth information image, and the processed depth information after wear is aligned with the processed depth information before wear, and the differences are taken in turn to obtain the wear depth distribution map of the floating ring sealing surface.

[0080] The wear area of ​​this embodiment is obtained by the following technical means:

[0081] Firstly, based on the wear depth distribution map of the floating ring sealing surface, the wear area is calibrated, and the wear area of ​​the sealing surface is collected to obtain the corresponding wear area contour images before and after the floating ring wear. The obtained wear area contour images are filtered, denoised, and segmented in turn, and the contour edges are fitted, corrected, and reconstructed to obtain the target edge contour image. Then, the target edge contour image is processed with contour external points to obtain the final wear area contour. The final wear area contours obtained before and after wear are registered and compared to obtain the wear area.

[0082] It should be noted that the registration, image processing, contour extraction and other technologies used in the process of calculating the wear depth, wear area, and comparing the data before and after wear in this embodiment can all be implemented using existing mature technologies, which is not difficult to implement for those skilled in the art.

[0083] Embodiment 3:

[0084] A method for measuring the wear of a circumferential floating ring seal for an aircraft engine, based on any of the above embodiments, uses the following test device to test a floating ring seal test piece, and measures the wear during the test based on the test method of the present application. Figures 2 to 6 As shown, including:

[0085] Positioning assembly, used for positioning the test floating ring;

[0086] A scraping and rubbing component, used for scraping and / or rubbing the test floating ring;

[0087] A power assembly connected to the scraping and rubbing component, and used to drive the scraping and rubbing component to scrape and / or rub against the test floating ring;

[0088] A sensing component, used for monitoring the force exerted by the scraping and rubbing components on the test floating ring;

[0089] Temperature control component, used to control the test environment temperature.

[0090] In this embodiment, the positioning assembly includes a housing 12 for accommodating a test floating ring, a plurality of floating mechanisms connected to the housing 12, and a floating ring fixture 13 connected to the floating end of the floating mechanism; the floating ring fixture 13 is located inside the housing 12, and a plurality of the floating ring fixtures 13 are distributed in an annular manner. The floating mechanism includes a sleeve 22 connected to the housing 12, a gland 21 connected to the sleeve 22, and an elastic member 23 located between the gland 21 and the floating ring fixture 13; the floating ring fixture 13 is located at one end of the sleeve 22 that is radially inward. It also includes a preload adjustment mechanism for adjusting the relative position of the gland 21 and the sleeve 22.

[0091] In this embodiment, the sleeves 22 are evenly arranged along the circumferential direction of the shell 12 at four directions: upper, lower, left and right. Adjacent sleeves 22 maintain an angle of 90°. Springs of the same model and specification are arranged in the four spring sleeves as elastic members 23.

[0092] Preferably, the outer wall of the gland 21 is provided with an external thread, and the inner wall of the sleeve 22 is provided with a matching internal thread. The gland 21 is partially screwed into the sleeve 22 through the thread, and the screwing depth of the gland 21 can be flexibly adjusted, thereby adjusting the preload force of the spring. More preferably, a scale can be provided on the gland 21 to ensure that the force applied in each direction is basically consistent.

[0093] In this embodiment, the scraping and rubbing component is eccentrically arranged inside the housing 12, and the scraping and rubbing component is radially facing one of the floating ring fixtures 13. Figure 3 and Figure 4 As shown, the scraping and rubbing component includes a cam 14 having 1 to 3 protrusions 15 .

[0094] In a more preferred embodiment, the housing 12 is cylindrical, the sleeve 22 is fixedly passed through the housing 12 , the housing 12 is fixed on a supporting saddle 16 , and the supporting saddle 16 is fixed on a test bench 17 .

[0095] In a more preferred embodiment, the sensing assembly includes a force sensor disposed in each sleeve 22, and the force sensor is used to monitor the force exerted by the spring on the gland 21 in the corresponding sleeve.

[0096] The power assembly is as follows Figure 6 As shown, it includes a main shaft 32 connected to the cam 14 and a motor 36 for driving the main shaft 32 to rotate. One end of the main shaft 32 is connected to the motor 36 through a coupling 35, and the other end is connected to the cam 04. The main shaft 32 is eccentrically installed relative to the housing 12 to ensure the required eccentricity.

[0097] The main shaft 32 passes through the bearing box and is rotatably connected to the bearing box; the bearing box includes an upper box body 37, a lower box body 38, an end cover 33, a vent hole 34 and other structures.

[0098] During specific use, the eccentricity of the floating ring seal during the test can be set accordingly according to the actual use conditions of the floating ring seal in the aircraft engine, and the main shaft can be eccentrically positioned and installed to ensure the required eccentricity.

[0099] In a more preferred embodiment, the cam 14 is detachably connected to the main shaft 32, so that the cam 14 with different numbers of protrusions 15 can be replaced according to specific needs.

[0100] In a more preferred embodiment, the sensing component is further used to monitor the frequency of the scraping and / or rubbing of the scraping and rubbing component against the test floating ring, and / or the sensing component is further used to monitor the temperature and / or humidity of the test environment.

[0101] In a more preferred embodiment, the temperature control assembly includes a temperature regulating device and a heat preservation device, and the heat preservation device includes a refractory brick layer, a rock wool layer and a stainless steel layer arranged in sequence from the inside to the outside. The heat preservation device is arranged on the outside of the scraping and rubbing parts and the floating mechanism to cover them in the internal space.

[0102] In a more preferred embodiment, the temperature control assembly further comprises a temperature regulating device and a shaft end heat dissipation system. The temperature regulating device comprises a resistance wire for heating the test environment temperature, preferably Cr 20 Ni 80 The material is a heating resistor wire with a heating power of not less than 1000W; the shaft end heat dissipation system adopts a combination of fin heat dissipation and fan heat dissipation to dissipate the heat inside the bearing box to ensure that the corresponding bearing front end temperature meets the working requirements.

[0103] In a more preferred embodiment, a test analysis system is also included to receive all data monitored by the sensing component for subsequent display and analysis.

[0104] The test device provided in this embodiment can be used to carry out radial scraping and abrasion tests on the test floating ring, effectively simulating the scraping of the inner side of the floating ring seal with the runway under the engine operation condition; by controlling the frequency of scraping and / or abrasion, the wear resistance of the floating ring seal under the service condition can be tested in a short time; the design defects of the test floating ring can be quickly and effectively stimulated, which is conducive to determining the performance of the test product and providing a scientific and reasonable basis for the verification of the floating ring seal product; the floating state of the sealing floating ring for the aircraft engine can be effectively simulated, and the actual working condition of the floating ring air film seal in the aircraft engine can be effectively simulated, so that the test results are more accurate and reliable; the scraping and abrasion component can continuously scrape and abrade the test floating ring at a specified position, which is conducive to shortening the test time and more quickly and effectively stimulating possible design defects; the harsh high temperature working condition of the floating ring seal of the aircraft engine can be effectively simulated, so that the test results are closer to the actual service condition.

[0105] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0106] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In addition, the term "connected" used in this article can be directly connected or indirectly connected via other components without special explanation.

Claims

1. A method for measuring the wear of a circumferential floating ring seal for an aircraft engine, characterized in that: include: Before the floating ring or floating ring seal test piece is used or tested, a first surface morphology of the circumferential sealing surface is obtained; Expanding the first surface topography into a plane to obtain a first surface profile; After the floating ring or floating ring seal test piece is used or tested, a second surface morphology of the circumferential sealing surface is obtained; unfolding the second surface topography into a plane to obtain a second surface profile; Based on the first surface profile and the second surface profile, obtaining wear depth data and wear area data; Based on the wear depth data and the wear area data, the wear volume and / or the wear mass are calculated.

2. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 1, characterized in that: The first surface morphology or the second surface morphology is obtained by the following method: The surface morphology of the circumferential sealing surface is replicated by using a solidified molding; The topography of the surface of the solidified molded object is replicated as the first surface topography or the second surface topography.

3. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 2, characterized in that: The cured product is a resin material.

4. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 2, characterized in that: The method for obtaining the first surface profile comprises: unfolding the solidified molded object with the first surface morphology along the circumferential direction to obtain a first end face, obtaining protrusion information on the first end face, and obtaining the first surface profile; The method for obtaining the second surface profile includes: unfolding the solidified molded object with the second surface morphology along the circumferential direction to obtain the second end face, acquiring the protrusion information on the second end face, and obtaining the second surface profile.

5. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 4, characterized in that: The first surface profile and / or the second surface profile are obtained by scanning with a three-dimensional ultra-depth surface profiler or a line laser scanner.

6. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 4, characterized in that: The protrusion information includes heights, contour curves and projection areas of all protrusions.

7. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 4, characterized in that: Methods for obtaining wear depth data include: Extracting the protrusion height data in the first surface contour and the second surface contour respectively; The first surface profile and the second surface profile are registered, and the protrusion heights of each area are subtracted to obtain wear depth data.

8. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 4, characterized in that: Methods for obtaining wear area data include: calibrating a wear area based on the wear depth data; Acquire image data of each wear area on the first surface contour and the second surface contour respectively, and perform edge image processing to obtain a first wear area contour data set and a second wear area contour data set respectively; The first wear region profile data set is compared with the second wear region profile data set to obtain the wear area of ​​each wear region.

9. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 1, characterized in that: The method for calculating the wear volume includes: matching the obtained wear depth data and the wear area data, and multiplying the corresponding wear depth data by the corresponding wear area data, summing the data, and obtaining the wear volume.

10. The method for measuring the wear amount of a circumferential floating ring seal for an aircraft engine according to claim 1, characterized in that: The method for calculating the wear mass includes: multiplying the wear volume by the density of the floating ring or floating ring seal test piece to obtain the wear mass.

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