Floating ring seal scraping and rubbing test device for aero-engine

Abstract

The invention discloses a floating ring seal scraping and rubbing test device for an aero-engine, and the device comprises a positioning assembly which is used for positioning a test floating ring; the scraping and rubbing part is used for scraping and / or rubbing the test floating ring; the power assembly is connected with the scraping and rubbing part and is used for driving the scraping and rubbing part to be scraped and / or rubbed with the test floating ring; and the sensing assembly is used for monitoring the acting force of the scraping and rubbing part on the test floating ring. The invention provides a floating ring seal scraping and collision abrasion test device for an aero-engine, so as to solve the problem that a floating ring seal product for the aero-engine is difficult to effectively test and verify in the prior art, and achieve the purposes of quickly and effectively exciting the defects of a floating ring seal material, testing the performance of the product and verifying the floating ring seal product.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engine sealing, and in particular to a floating ring sealing scraping and abrasion testing device for aviation engines. Background Art

[0002] The floating ring seal is a new type of non-contact air film seal. Compared with the traditional fixed rotating shaft air film seal, it has a smaller sealing gap and better self-centering function, and has attracted much attention in the field of aerospace engine sealing. As an indispensable part of the aerospace engine, the performance of the floating ring air film seal also affects the overall performance of the aerospace engine. In order to ensure the superior performance of the aerospace engine, higher requirements are placed on the stability and service life of the engine sealing system performance. For the floating ring air film seal, leakage and stability are two important indicators to measure the sealing performance. The floating ring air film seal often breaks due to insufficient dynamic pressure, which causes the floating ring to collide and rub. For the floating ring air film seal, the radial clearance is an important factor affecting the performance of the whole machine. Too large a clearance will bring greater leakage problems, and too small a clearance will increase the risk of end face collision and rubbing, thereby affecting the service life of the floating ring air film seal.

[0003] Since most of the sealing devices in aircraft engines are compact and work under high temperature conditions for a long time, the sealing devices used in aircraft engines need a larger radial air film gap to reduce the thermal deformation caused by high temperature and the friction caused by thermal expansion. Therefore, the failure forms of floating ring seals mainly include fretting failure of the ring end face and friction failure of the bore cylindrical surface.

[0004] At present, the problems that restrict the development of floating ring seals for aircraft engines are mainly concentrated on the fact that the material properties have not been systematically verified and analyzed (floating rings are generally made of carbon graphite with low hardness), and the test equipment and testing technology are not perfect. The defects and deficiencies of floating rings for aircraft engines can only be discovered after a certain period of service. It is still difficult to effectively test them and effectively verify floating ring seal products for aircraft engines in the existing technology. Summary of the invention

[0005] The present invention provides a floating ring seal scraping and abrasion test device for aircraft engines, so as to solve the problem that it is difficult to effectively test and verify floating ring seal products for aircraft engines in the prior art, and achieve the purpose of quickly and effectively stimulating the defects of floating ring seal materials, testing product performance, and verifying floating ring seal products.

[0006] The present invention is achieved through the following technical solutions:

[0007] A scraping and abrasion test device for a floating ring seal for an aircraft engine, comprising:

[0008] Positioning assembly, used for positioning the test floating ring;

[0009] A scraping and rubbing component, used for scraping and / or rubbing the test floating ring;

[0010] 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;

[0011] The sensing component is used to monitor the force exerted by the scraping and rubbing components on the test floating ring.

[0012] Most of the sealing devices in aircraft engines are compact structures. Long-term high-temperature working conditions require a larger radial air film gap for the sealing devices used in aircraft engines. Therefore, the failure forms of floating ring seals mainly include micro-wear failure of the ring end face and friction failure of the bore cylindrical surface. Regarding the development of the performance verification test analysis of floating ring seal materials, the inventors of this case found in the process of continuous research that there is no complete radial scraping and friction test device in the prior art, nor a more systematic test and analysis method. In view of the problem that it is difficult to effectively test and verify floating ring seal products for aircraft engines in the prior art, the present invention proposes a scraping and friction test device for floating ring seals for aircraft engines. The device uses a positioning component to position the floating ring to be tested, which is defined as a test floating ring. The scraping and friction component is driven by the power component to continuously scrape and / or rub the test floating ring, and the force during the scraping and / or friction process is sensed by the sensing component. Those skilled in the art should understand that the area of ​​scraping and / or friction between the scraping and friction component and the test floating ring should be the sealing surface to be tested. In addition, the sensing component in the present application may include any force monitoring means in the prior art and be implemented using a force sensor.

[0013] This application can conduct radial scraping and abrasion tests on the test floating ring, effectively simulating the scraping between the inner side of the floating ring seal and the runway under engine operating conditions; at the same time, by controlling the frequency of scraping and / or abrasion, the wear resistance of the floating ring seal under service conditions can be tested in a short period of time. This application can quickly and effectively stimulate the design defects of the test floating ring (such as whether the carbon graphite material with lower hardness is easy to break under harsh working conditions) through radial scraping and abrasion tests, which is conducive to determining the performance of the test product and providing a scientific and reasonable basis for the verification of floating ring seal products.

[0014] Furthermore, the positioning assembly includes a shell for accommodating a test floating ring, a plurality of floating mechanisms connected to the shell, and a floating ring fixture connected to the floating end of the floating mechanism; the floating ring fixture is located inside the shell, and a plurality of the floating ring fixtures are distributed in a ring.

[0015] In this scheme, the test floating ring is clamped by a plurality of fixtures in the circumferential direction through each floating mechanism. Since the fixture is located at the floating end of the floating mechanism, each fixture can float radially, thereby simulating the floating state of the test floating ring, thereby effectively simulating the actual working conditions of the floating ring air film seal in the aircraft engine, making the test results more accurate and reliable.

[0016] Furthermore, the scraping and rubbing component is eccentrically arranged inside the shell, and the scraping and rubbing component is radially facing one of the floating ring fixtures. This solution is conducive to simulating the eccentric working conditions of the actual service process of the floating ring seal, so that the scraping and rubbing component can continuously scrape and rub the test floating ring at the specified position, which is conducive to shortening the test time and more quickly and effectively stimulating possible design defects. In addition, the scraping and rubbing component is radially facing one of the floating ring fixtures, which is conducive to providing a stable reaction force in the radial direction to the test floating ring through the floating mechanism, thereby more realistically simulating the scraping and rubbing between the inner side of the seal and the runway. In addition, the scraping and rubbing position of the floating ring in actual service is not stable, and this solution performs continuous scraping and rubbing at the specified position, which can simulate more severe extreme conditions and realize the verification and testing of the floating ring performance in a shorter time.

[0017] Furthermore, the floating mechanism includes a sleeve connected to the housing, a gland connected inside the sleeve, and an elastic member located between the gland and the floating ring clamp; the floating ring clamp is located at the radially inward end of the sleeve. In this solution, the elastic member is positioned from the radially outward end by the gland, and the deformation capacity of each elastic member fully simulates the working state of the floating ring seal.

[0018] Furthermore, it also includes a preload adjustment mechanism for adjusting the relative position of the gland and the sleeve. This solution adjusts the relative position of the gland and the sleeve through the preload adjustment mechanism, and then can flexibly adjust the preload of the elastic member as needed, so as to simulate different service conditions and expand the scope of application of this application. The preload adjustment mechanism can be implemented by any structure that can adjust the relative position of the gland inside the sleeve, such as threaded connection between the gland and the sleeve, or key fit between the gland and the sleeve and temporary locking, etc.

[0019] Furthermore, the scraping and rubbing component includes a cam, and the cam includes at least one protrusion.

[0020] The number of protrusions arranged along the circumferential direction of the cam in this solution can be replaced according to specific test conditions. When a short-time, high-frequency scraping and rubbing test is performed, the number of protrusions is preferably 1. This selection can ensure that when the cam rotates one circle, the protrusion performs a radial scraping and rubbing on the floating ring seal end face. When a short-time radial scraping and rubbing test is performed, it is ensured that the loading force acting on the floating ring seal contact end face is always consistent each time; when a long-time, low-frequency floating ring seal radial scraping and rubbing test is performed, multiple protrusions can be evenly arranged along the circumferential direction of the cam structure. When the cam rotates one circle, the radial scraping and rubbing test can be performed multiple times. On the premise of ensuring that the test loading force is basically unchanged, the effect of effectively shortening the test time is achieved.

[0021] Preferably, the number of protrusions on a single cam is generally not more than 3. If it exceeds 3, radial scraping and rubbing may be too frequent, so that the scraped material adheres to the surface of the test floating ring, which may affect the accuracy of the test.

[0022] Furthermore, the power assembly includes a main shaft connected to the scraping and rubbing component and a motor for driving the main shaft to rotate. The output end of the motor and the main shaft can be driven by any transmission method that can be realized by those skilled in the art, and no specific limitation is made here.

[0023] Furthermore, the sensing component is also used to monitor the frequency of the scraping and / or rubbing of the scraping and rubbing component on the test floating ring, and / or the sensing component is also used to monitor the temperature and / or humidity of the test environment. This solution enables the staff to more accurately grasp the detailed parameters of the scraping and rubbing test, and provide more sufficient data support for subsequent data analysis, performance verification, etc.

[0024] Furthermore, it also includes a temperature control component for controlling the temperature of the test environment. This solution enables the staff to more accurately grasp the test conditions and provide more sufficient data support for subsequent data analysis and performance verification.

[0025] Furthermore, 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. This solution uses the temperature regulating device and the heat preservation device to achieve stable control of the test environment, so that the test environment can effectively simulate the harsh high temperature working conditions of the floating ring seal of the aircraft engine, thereby making the test results closer to the actual service conditions.

[0026] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0027] 1. The present invention provides a scraping and abrasion test device for a floating ring seal for an aircraft engine, which can be used to carry out a radial scraping and abrasion test on a test floating ring, effectively simulating the scraping between the inner side of the floating ring seal and 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 period of time.

[0028] 2. The present invention provides a scraping and abrasion test device for a floating ring seal for an aircraft engine, which can quickly and effectively stimulate the design defects of the test floating ring (such as whether the carbon graphite material with low hardness is easy to break under harsh working conditions), thereby facilitating the determination of the performance of the test product and providing a scientific and reasonable basis for the verification of the floating ring seal product.

[0029] 3. The present invention provides a scraping and abrasion test device for a floating ring seal for an aircraft engine, which can effectively simulate the floating state of a sealing floating ring for an aircraft engine, and further effectively simulate the actual working condition of a floating ring air film seal in an aircraft engine, making the test result more accurate and reliable.

[0030] 4. The present invention provides a scraping and rubbing test device for a floating ring seal for an aircraft engine. The scraping and rubbing component can continuously scrape and rub the test floating ring at a specified position, which is beneficial to shorten the test time and more quickly and effectively stimulate possible design defects.

[0031] 5. The present invention provides a scraping and abrasion test device for a floating ring seal for an aircraft engine. The test environment provided by the device can effectively simulate the harsh high-temperature working conditions of the floating ring seal of an aircraft engine, thereby making the test results closer to the actual service conditions.

[0032] 6. The present invention provides a scraping and rubbing test device for a floating ring seal for an aircraft engine, which performs continuous scraping and rubbing at a specified position, can simulate more severe extreme working conditions, and verify and test the performance of the floating ring in a shorter time. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] 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:

[0034] Figure 1 It is a structural schematic diagram of a specific embodiment of the present invention;

[0035] Figure 2 A schematic diagram of a scraping and rubbing component in a specific embodiment of the present invention;

[0036] Figure 3 A schematic diagram of another scraping and rubbing component in a specific embodiment of the present invention;

[0037] Figure 4A schematic diagram of a positioning component in a specific embodiment of the present invention;

[0038] Figure 5 It is a schematic diagram of a power assembly in a specific embodiment of the present invention;

[0039] Figure 6 Schematic diagram of the process of measuring wear amount in a specific embodiment of the present invention.

[0040] Marks and corresponding parts names in the attached drawings:

[0041] 12-housing, 13-floating ring fixture, 14-cam, 15-protrusion, 16-support saddle, 17-test bench;

[0042] 21- gland, 22- sleeve, 23- elastic member;

[0043] 32-spindle, 33-end cover, 34-vent, 35-coupling, 36-motor, 37-upper housing, 38-lower housing. DETAILED DESCRIPTION

[0044] 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.

[0045] Embodiment 1:

[0046] A scraping and abrasion test device for floating ring seals for aircraft engines, such as Figures 1 to 5 As shown, including:

[0047] Positioning assembly, used for positioning the test floating ring;

[0048] A scraping and rubbing component, used for scraping and / or rubbing the test floating ring;

[0049] 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;

[0050] A sensing component, used for monitoring the force exerted by the scraping and rubbing components on the test floating ring;

[0051] Temperature control component, used to control the test environment temperature.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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 2 and Figure 3 As shown, the scraping and rubbing component includes a cam 14 having 1 to 3 protrusions 15 .

[0056] 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 .

[0057] 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.

[0058] Embodiment 2:

[0059] A floating ring seal scraping and abrasion test device for an aircraft engine, based on Example 1, the power component is as follows Figure 5As 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] 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 on the test floating ring, and / or the sensing component is further used to monitor the temperature and / or humidity of the test environment.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] Embodiment 3:

[0068] A method for scraping and abrasion testing of a floating ring seal for an aircraft engine is implemented based on the test device in any of the above embodiments, and comprises the following steps:

[0069] Install the test floating ring on the positioning assembly;

[0070] Select appropriate scraping and rubbing components according to test requirements and connect them to the power components;

[0071] Adjust the test environment temperature to the required temperature through the temperature control component;

[0072] Start the power component to make the scraping and rubbing parts scrape and / or rub against the test floating ring at a set frequency, and start the sensing component for monitoring during this period.

[0073] Embodiment 4:

[0074] A method for scraping and abrasion testing of floating ring seals for aircraft engines, based on Example 3, further includes measuring the wear amount during the test. The measuring method is as follows: Figure 6 As shown, specifically including:

[0075] S1. Before the test, a first surface morphology of the circumferential sealing surface of the test floating ring is obtained; specifically, a solidified molded object is attached to the circumferential sealing surface, and the solidified molded object is pressed against the circumferential sealing surface, and the solidified molded object is removed, and the morphology of the surface of the solidified molded object is used as the first surface morphology;

[0076] S2, unfolding the first surface topography into a plane to obtain a first surface profile;

[0077] S3, conducting a test using the method in Example 3, and obtaining a second surface morphology of the circumferential sealing surface of the test floating ring after the test; specifically, removing the test floating ring, attaching a solidified molded object to the circumferential sealing surface again, and pressing the solidified molded object to the circumferential sealing surface, removing the solidified molded object, and using the morphology of the surface of the solidified molded object as the second surface morphology;

[0078] S4, unfolding the second surface topography into a plane to obtain a second surface profile;

[0079] 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 test floating ring before and after friction and wear, and further obtain a wear depth value;

[0080] 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.

[0081] S6. Calculating the wear volume and / or wear mass based on the wear depth data and the wear area data;

[0082] 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.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] 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.

[0089] In a more preferred embodiment, the method for obtaining the first surface profile includes: unfolding the solidified molded object with the first surface topography along the circumferential direction to obtain a first plane, acquiring protrusion information on the first plane, and obtaining the first surface profile;

[0090] The method for obtaining the second surface contour comprises: unfolding the solidified molded object with the second surface morphology along the circumferential direction to obtain a second plane, acquiring protrusion information on the second plane, and obtaining the second surface contour.

[0091] Wherein, the first surface profile and / or the second surface profile are obtained by scanning with a three-dimensional ultra-depth-of-field surface profiler or a line laser scanner.

[0092] The protrusion information obtained in this embodiment includes the height, contour curve and projection area of ​​all protrusions.

[0093] Preferably, the wear depth of this embodiment is obtained by the following method:

[0094] 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.

[0095] The wear area of ​​this embodiment is obtained by the following technical means:

[0096] 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.

[0097] 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.

[0098] 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 floating ring seal scraping and rubbing test device for aircraft engines, characterized in that: include: Positioning assembly, used for positioning the test floating ring; A scraping and rubbing component, used for scraping and / or rubbing the test floating ring; 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; The sensing component is used to monitor the force exerted by the scraping and rubbing components on the test floating ring.

2. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 1, characterized in that: The positioning assembly comprises a shell (12) for accommodating a test floating ring, a plurality of floating mechanisms connected to the shell (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 shell (12), and a plurality of the floating ring fixtures (13) are distributed in an annular shape.

3. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 2, characterized in that: 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 clamps (13).

4. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 2, characterized in that: The floating mechanism comprises a sleeve (22) connected to the housing (12), a pressure cover (21) connected inside the sleeve (22), and an elastic member (23) located between the pressure cover (21) and the floating ring clamp (13); the floating ring clamp (13) is located at an end of the sleeve (22) facing radially inward.

5. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 4, characterized in that: It also includes a preload adjustment mechanism for adjusting the relative position of the gland (21) and the sleeve (22).

6. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 1, characterized in that: The scraping and rubbing component comprises a cam (14), and the cam (14) comprises at least one protrusion (15).

7. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 1, characterized in that: The power assembly comprises a main shaft (32) connected to the scraping and rubbing component and a motor (36) for driving the main shaft (32) to rotate.

8. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 1, characterized in that: The sensing component is also used to monitor the frequency of the scraping and / or rubbing of the scraping and rubbing component on the test floating ring, and / or the sensing component is also used to monitor the temperature and / or humidity of the test environment.

9. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 1, characterized in that: It also includes a temperature control component for controlling the temperature of the test environment.

10. The floating ring seal scraping and rubbing test device for aircraft engines according to claim 9, characterized in that: The temperature control component comprises a temperature regulating device and a heat preservation device, and the heat preservation device comprises a refractory brick layer, a rock wool layer and a stainless steel layer which are sequentially arranged from the inside to the outside.

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