Device and method for measuring high-temperature fretting friction coefficient of aero-engine margin plate damping block

Abstract

The invention discloses an aero-engine margin plate damping block high-temperature fretting friction coefficient measuring device and method, and relates to the technical field of high-temperature fretting friction testing. The aero-engine margin plate damping block high-temperature fretting friction coefficient measuring device is characterized in that the top of an upper connecting block is arranged on a load loading module and a linear reciprocating driving module of a friction-wear testing machine; the upper clamp is assembled at the bottom of the upper connecting block through a fastener, and the hemisphere is arranged between the upper connecting block and the upper clamp; the upper friction block is assembled at the bottom of the upper clamp through a fastener, the lower friction block is assembled at the top of the lower clamp through a fastener, the lower clamp is fixed on a reference platform of the friction-wear testing machine, and the lower clamp is also fixedly connected with the friction force sensor; the upper friction block and the lower friction block form a friction pair used for simulating the friction contact form of the aero-engine margin plate damping block. The technical problem that only point, line and surface contact material-grade high-temperature fretting friction tests can be carried out in the prior art is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of high-temperature fretting friction testing, and in particular to a device and method for measuring the high-temperature fretting friction coefficient of the blade damper of an aero-engine. Background Art

[0002] The existing high-temperature fretting friction testing systems usually focus on the experimental temperature range, experimental environment, etc. Taking the patent document with the application number CN202111331685.4 as an example, the existing system needs to be implemented in a vacuum environment, and the technical difficulty and cost required for the experiment are high; for the patent document with the application number CN 202310725581.4, it can realize ultra-high-temperature fretting wear experiments in an atmospheric environment, but the experimental system includes four servo cylinders and a high-temperature heating unit, and the expansion and contraction of the cylinders drive the specimen to do fretting friction, and the experimental device is relatively complex; for the patent document with the application number 202211608196.3, this patent document only considers using a thermocouple in a heating gas chamber to simulate the real working conditions of a specimen at a higher temperature, and fixing the friction pair through a fixture.

[0003] However, the above patent documents mainly focus on the friction forms of surface contact and line contact, and it is difficult to simulate the friction state of the complex contact surface between the blade tenon and the blade damper of an aero-engine. In the actual application environment, the friction contact area of the blade damper is at the wedge-shaped end face position, where one surface is for plane fretting friction and the other surface is for inclined plane fretting friction. Therefore, the existing devices and methods are difficult to meet the evaluation of the high-temperature fretting friction performance of the double-end face complex structure. In addition, in the existing devices and methods, it is not clear how to fix the specimen by the fixture and how to avoid the assembly tolerance between the upper and lower friction specimens. Taking the line contact fretting friction as an example, the upper and lower friction specimens often have an eccentric load or specimen deformation due to the assembly tolerance of the testing machine system. Especially under high-temperature conditions, the thermal expansion of the material leads to a greater assembly tolerance, which brings greater inaccuracy to the measurement result of the friction coefficient. In addition, fretting often reciprocates under extremely small amplitudes and high-frequency working conditions, and the displacement amplitude is usually in the order of hundreds of micrometers or even micrometers. During the high-temperature fretting friction experiment, the assembly of the measurement module often causes phenomena such as "jamming" or loosening of the connecting parts due to high-temperature fretting, resulting in the failure of the measurement module and affecting the safety and life of the high-temperature fretting friction test. Summary of the Invention

[0004] In order to solve the technical problem that the existing technology can only carry out high-temperature fretting friction tests at the material level of point, line, and surface contact, the embodiments of the present invention provide a device and method for measuring the high-temperature fretting friction coefficient of the blade damper of an aero-engine. The technical solution is as follows:

[0005] On the one hand, a device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block is provided, including: an upper connecting block, a hemisphere, an upper fixture, an upper friction block, a lower friction block and a lower fixture; wherein, the top of the upper connecting block is arranged on the load loading module and the linear reciprocating driving module of the friction and wear testing machine, the upper fixture is assembled to the bottom of the upper connecting block through fasteners, and the hemisphere is arranged at the middle position between the upper connecting block and the upper fixture; the upper friction block is assembled to the bottom of the upper fixture through the fasteners, the lower friction block is assembled to the top of the lower fixture through the fasteners, the lower fixture is fixed on the reference platform of the friction and wear testing machine, and the lower fixture is also fixedly connected with a friction force sensor; the upper friction block and the lower friction block form a friction pair for simulating the friction contact form of the aero-engine rim damping block.

[0006] Optionally, the fasteners include bolt fasteners; through holes are arranged at the four corners of the upper connecting block, threaded holes are arranged at the corresponding positions of the four corners of the upper fixture, and the through holes, the threaded holes and the bolt fasteners are assembled and clamped in cooperation.

[0007] Optionally, a wedge-shaped groove is arranged on the upper surface of the threaded hole, and a leveling pad block with a wedge-shaped structure is embedded in the wedge-shaped groove; the leveling pad block is used to adjust the levelness of the upper fixture by adjusting the depth of embedding in the wedge-shaped groove.

[0008] Optionally, grooves are arranged at the bottom of the upper fixture and the top of the lower fixture, and the upper friction block and the lower friction block are respectively arranged in the bottom groove of the upper fixture and the top groove of the lower fixture.

[0009] Optionally, a flat groove is arranged on the lower surface of the upper connecting block, and a spherical groove is arranged on the upper surface of the upper fixture; the flat groove is matched with the plane of the hemisphere, and the spherical groove is matched with the spherical crown of the hemisphere.

[0010] Optionally, the contact form of the friction pair composed of the upper friction block and the lower friction block includes any one of the following: point contact, line contact, surface contact.

[0011] Optionally, when the contact form of the friction pair is the point contact, the upper friction block is a sphere and the lower friction block is a plane; when the contact form of the friction pair is the line contact, the upper friction block is a cylinder and the lower friction block is a plane; when the contact form of the friction pair is the surface contact, the contact surfaces of the upper friction block and the lower friction block are both planes.

[0012] Optionally, the upper friction block includes a lower plane and a lower inclined side surface, the lower friction block includes an upper plane and an upper inclined side surface, the lower plane is in frictional contact with the upper plane, and the lower inclined side surface is in frictional contact with the upper inclined side surface.

[0013] Optionally, the surfaces of the upper connecting block, the fastener, the hemisphere, the upper fixture, the upper friction block, the lower friction block and the lower fixture are all coated with a metal nitride coating.

[0014] On the other hand, a method for measuring the high-temperature fretting friction coefficient of an aero-engine rim damper block is also provided, which is applied to the high-temperature fretting friction coefficient measuring device for an aero-engine rim damper block provided in the embodiments of the present invention; the method includes: installing the upper connecting block on the load loading module and the linear reciprocating driving module of a friction and wear testing machine, installing the upper fixture with the hemisphere on the upper connecting block, connecting and fastening with a fastener, and leveling; installing the upper friction block and the lower friction block in the bottom groove of the upper fixture and the top groove of the lower fixture respectively, and connecting and fastening with a fastener; installing the lower fixture equipped with the lower friction block on the reference platform of the friction and wear testing machine; turning on the heating module to raise the temperatures of the upper friction block and the lower friction block to a preset temperature; turning on the loading module to transfer the load from the upper fixture to the upper friction block, and transferring the load from the upper friction block to the lower friction block; turning on the linear reciprocating driving module to drive the upper friction block to perform reciprocating linear rolling friction on the surface of the lower friction block, and measuring the frictional force.

[0015] The embodiments of the present invention provide a device and a method for measuring the high-temperature fretting friction coefficient of an aero-engine rim damper block, which overcome the problem that the existing high-temperature fretting friction measuring device can only carry out material-level high-temperature fretting friction tests with point, line and surface contacts, realize that the upper and lower friction blocks can simulate the actual fretting friction state of the structural-level rim damper block, and at the same time, solve the defects of load offset caused by assembly tolerance, "seizing" of the connecting parts due to high-temperature adhesion or loosening due to fretting during the experiment, resulting in inaccurate measurement, and carry out accurate measurement of the high-temperature fretting friction coefficient. Description of the Drawings

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0017] Figure 1 is a schematic structural diagram of a device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damper block provided in the embodiments of the present invention;

[0018] Figure 2 is an exploded view of a device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damper block provided in the embodiments of the present invention;

[0019] Figure 3 is a three-dimensional schematic diagram of a fastener provided by an embodiment of the present invention;

[0020] Figure 4 is a three-dimensional schematic diagram of an upper connecting block provided by an embodiment of the present invention;

[0021] Figure 5 is a three-dimensional schematic diagram of an upper fixture provided by an embodiment of the present invention;

[0022] Figure 6 is a three-dimensional schematic diagram of a leveling pad provided by an embodiment of the present invention;

[0023] Figure 7 is a three-dimensional schematic diagram of a lower fixture provided by an embodiment of the present invention;

[0024] Figure 8 is a kind provided by an embodiment of the present invention Figure 1 enlarged schematic diagram at position A in;

[0025] Figure 9 is a flowchart of a method for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block provided by an embodiment of the present invention;

[0026] Figure 10 is a friction coefficient curve graph under high-temperature working conditions provided by an embodiment of the present invention.

[0027] Illustration: 1. Upper connecting block, 11. Through hole, 2. Fastener, 3. Hemisphere, 4. Upper fixture, 41. Threaded hole, 42. Wedge-shaped groove, 43. Spherical groove, 5. Upper friction block, 6. Lower friction block, 7. Lower fixture, 8. Leveling pad. Detailed implementation manners

[0028] The following describes the technical solutions in the present invention with reference to the accompanying drawings.

[0029] In the embodiments of the present invention, words such as "exemplarily" and "for example" are used to represent examples, illustrations or explanations. Any embodiment or design solution described as "example" in the present invention should not be construed as being more preferred or having more advantages than other embodiments or design solutions. Rather, the use of the word "example" is intended to present concepts in a specific manner. In addition, in the embodiments of the present invention, the meaning expressed by "and / or" can be both, or either one of the two.

[0030] To make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the accompanying drawings and specific embodiments.

[0031] Figure 1It is a schematic structural diagram of a device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block according to an embodiment of the present invention. Figure 2 It is an exploded view of a device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block according to an embodiment of the present invention. As Figure 1 and Figure 2 shown, the device includes: an upper connecting block 1, a hemisphere 3, an upper fixture 4, an upper friction block 5, a lower friction block 6, and a lower fixture 7.

[0032] In an optional embodiment provided by the embodiments of the present invention, the upper connecting block 1, the fastener 2, the hemisphere 3, the upper fixture 4, the upper friction block 5, the lower friction block 6, and the lower fixture 7 are all processed from high-temperature resistant alloy materials, and the surfaces after processing are all coated with a metal nitride coating. Specifically, the metal nitride coating can effectively protect the anti-"seizing" and anti-loosening properties of the fastener under high-temperature fretting conditions, ensure the accuracy and reliability of the measurement of the fretting friction coefficient, and at the same time the metal nitride effectively reduces the high-temperature adhesion risk and extends the service life of the high-temperature fretting friction coefficient measurement module.

[0033] Optionally, the metal nitride oxide coating includes: a titanium nitride coating, a chromium nitride coating, and a tungsten nitride coating.

[0034] Specifically, as Figure 1 shown, the top of the upper connecting block 1 is arranged on the load loading module and the linear reciprocating drive module of the friction and wear testing machine. The upper fixture 4 is assembled to the bottom of the upper connecting block 1 through the fastener 2, and the hemisphere 3 is arranged at the middle position between the upper connecting block 1 and the upper fixture 4.

[0035] Specifically, the hemisphere 3 plays a role in regulating the levelness in the middle.

[0036] Specifically, the load loading module is above the upper connecting block 1 and applies a vertically downward load to the upper friction block 5. The linear reciprocating drive module is fixedly connected to the upper connecting block 1 through a linear bearing and a connecting mechanism for driving, so that the upper connecting block 1 can perform a reciprocating linear motion, driving the upper fixture 4 and the upper friction block 5 to perform a reciprocating motion on the surface of the lower friction block 6.

[0037] The upper friction block 5 is assembled to the bottom of the upper fixture 4 through the fastener 2, the lower friction block 6 is assembled to the top of the lower fixture 7 through the fastener 2, the lower fixture 7 is fixed on the reference platform of the friction and wear testing machine, and the lower fixture 7 is also fixedly connected to a friction force sensor, and the friction force sensor is used to measure the friction force.

[0038] Preferably, the upper fixture 4 and the upper friction block 5 are assembled through two fasteners 2; the lower fixture 7 and the lower friction block 6 are assembled through two fasteners 2.

[0039] Specifically, the upper friction block 5 and the lower friction block 6 form a friction pair for simulating the friction contact form of the rim damping block of an aero-engine.

[0040] Figure 3 It is a three-dimensional schematic diagram of a fastener provided according to an embodiment of the present invention. As Figure 3 shown, the fastener 2 includes a bolt fastener.

[0041] Figure 4 It is a three-dimensional schematic diagram of an upper connecting block provided according to an embodiment of the present invention, Figure 5 It is a three-dimensional schematic diagram of an upper fixture provided according to an embodiment of the present invention. As Figure 4 and Figure 5 shown, through holes 11 are provided at the four corners of the upper connecting block 1, and threaded holes 41 are provided at the corresponding positions at the four corners of the upper fixture 4. The through holes 11, the threaded holes 41 and the bolt fastener are assembled and clamped.

[0042] Specifically, as Figure 5 shown, a wedge-shaped groove 42 is provided on the upper surface of the threaded hole 41, and a leveling pad 8 with a wedge-shaped structure is embedded in the wedge-shaped groove 42. Figure 6 It is a three-dimensional schematic diagram of a leveling pad provided according to an embodiment of the present invention. As Figure 6 shown, a U-shaped sliding groove is provided in the middle of the leveling pad 8 for passing through the fastener 2 inserted into the threaded hole 41.

[0043] Specifically, the leveling pad 8 is used to adjust the level of the upper fixture 4 by adjusting the depth of embedding in the wedge-shaped groove 42.

[0044] Figure 7 It is a three-dimensional schematic diagram of a lower fixture provided according to an embodiment of the present invention. As Figure 5 and Figure 7 shown, grooves are provided at the bottom of the upper fixture 4 and the top of the lower fixture 7. The upper friction block 5 and the lower friction block 6 are respectively arranged in the bottom groove of the upper fixture 4 and the top groove of the lower fixture 7.

[0045] Specifically, a flat groove is provided on the lower surface of the upper connecting block 1, and the flat groove is matched with the plane of the hemisphere 3.

[0046] Specifically, as Figure 5 shown, a spherical groove 43 is provided on the upper surface of the upper fixture 4; the spherical groove 43 is matched with the spherical crown of the hemisphere 3.

[0047] In the embodiment of the present invention, both the upper friction block 5 and the lower friction block 6 are processed from the same material as the rim damping block and the blade tenon of the aero-engine.

[0048] In an alternative embodiment provided by the embodiments of the present invention, the contact form of the friction pair composed of the upper friction block 5 and the lower friction block 6 includes any one of the following: point contact, line contact, and surface contact.

[0049] For example, when the contact form of the friction pair is point contact, the upper friction block is a sphere and the lower friction block 6 is a plane, simulating the high-temperature fretting friction state of point contact;

[0050] When the contact form of the friction pair is line contact, the upper friction block 5 is a cylinder and the lower friction block 6 is a plane, simulating the high-temperature fretting friction state of line contact;

[0051] When the contact form of the friction pair is surface contact, the contact surfaces of the upper friction block 5 and the lower friction block 6 are both planes, simulating the high-temperature fretting friction state of surface contact.

[0052] Figure 8 is a kind provided according to the embodiments of the present invention Figure 1 The enlarged schematic view of position A. As Figure 8 shown, in an embodiment provided by the embodiments of the present invention, the upper friction block 5 includes a lower plane and a lower inclined side surface, the lower friction block 6 includes an upper plane and an upper inclined side surface, the lower plane is in frictional contact with the upper plane, and the lower inclined side surface is in frictional contact with the upper inclined side surface.

[0053] Figure 9 is a flowchart of a method for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block provided according to the embodiments of the present invention, which is applied to the device for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block provided by the embodiments of the present invention. As Figure 8 shown, the method specifically includes the following steps:

[0054] Step S902, install the upper connecting block on the load loading module and the linear reciprocating driving module of the friction and wear testing machine, install the upper fixture with a hemisphere on the upper connecting block, connect and fasten with fasteners, and level it.

[0055] Specifically, install the upper connecting block on the loading module and the reciprocating driving module to ensure that the upper connecting block does not shake; place the hemisphere in the central spherical groove of the upper fixture so that it is in a natural horizontal state; install the upper fixture with a hemisphere on the upper connecting block and use fasteners for connection and fastening; place the leveling pads in the wedge-shaped grooves at the four corners of the upper fixture, and the wedge-shaped leveling pads are auxiliary leveling components for the upper connecting block and the upper fixture; tighten the four fasteners diagonally and use a level to ensure that the upper fixture is in a horizontal state.

[0056] Step S904, install the upper friction block and the lower friction block in the bottom groove of the upper fixture and the top groove of the lower fixture respectively, and connect and fasten them with fasteners.

[0057] Step S906: Install the lower fixture equipped with the lower friction block on the reference platform of the friction and wear testing machine.

[0058] Step S908: Turn on the heating module to raise the temperatures of the upper friction block and the lower friction block to the preset temperature.

[0059] Step S910: Turn on the loading module to transfer the load from the upper fixture to the upper friction block, and then from the upper friction block to the lower friction block.

[0060] Step S912: Turn on the linear reciprocating drive module to drive the upper friction block to perform reciprocating linear rolling friction on the surface of the lower friction block and measure the frictional force.

[0061] Among them, the upper friction block and the lower friction block are designed in a double-sided contact structure form, which can be closer to the contact form between the tenon head and the rim damper block of the aero-engine, so as to simulate the high-temperature fretting friction and wear performance of the two. In addition, the friction block can be designed as a sphere or a cylinder according to needs, and cooperate with the lower friction block. The surface of the lower friction block can be a plane or an arc track. The positioning of the arc track should match that of the upper friction block to ensure that it fits with the running track of the upper friction block. The arc track can fully simulate the actual running contact state of the bearing.

[0062] For example, set the working conditions as follows: load 71N, frequency 200Hz, stroke 0.1mm, temperature 750°C, duration 1h, and the friction coefficient results are as Figure 10 shown, where Figure 10 is a friction coefficient curve graph under high-temperature working conditions provided according to an embodiment of the present invention.

[0063] As can be seen from the above description, the embodiment of the present invention provides a device and method for measuring the high-temperature fretting friction coefficient of the rim damper block of an aero-engine. Compared with the prior art, it has the following technical effects:

[0064] (1) The present invention can not only evaluate the high-temperature fretting friction and wear performance at the tenon head of the aero-engine blade according to the actual contact form between the tenon head and the rim damper block of the aero-engine blade, but also adjust the flatness of the friction pair contact surface by the friction and wear testing machine itself, and coat the fasteners with a metal nitride coating to avoid loosening and "jamming" caused by high-frequency fretting, thereby improving the accuracy of the test results and the service life of the module.

[0065] (2) The upper friction block and the lower friction block designed by the present invention can simulate the actual contact state between the tenon head and the rim damper block of the aero-engine blade, fully simulate the structure of multiple friction contact surfaces under high-temperature fretting conditions, and ensure the consistency with the actual contact state.

[0066] (3) The hemispherical structure and leveling pads designed in the present invention can adjust the pitch of the upper friction block in multiple directions, so as to make the contact loads at all positions between the upper friction block and the lower friction block consistent and evenly distributed, ensuring that the friction state is consistent with the actual working conditions.

[0067] (4) The present invention coats the fasteners with a metal nitride coating, which can effectively reduce the phenomena of "seizing" and loosening of the fasteners caused by high temperature and fretting in the high-temperature fretting friction experiment, and fully extend the service life of the high-temperature fretting friction coefficient measurement module.

[0068] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A measuring device for the high-temperature fretting friction coefficient of an aero-engine rim damping block, characterized in that, Comprising: an upper connecting block, a hemisphere, an upper fixture, an upper friction block, a lower friction block and a lower fixture; wherein, the top of the upper connecting block is arranged on the load loading module and the linear reciprocating driving module of the friction and wear testing machine, the upper fixture is assembled to the bottom of the upper connecting block through fasteners, and the hemisphere is arranged at the middle position between the upper connecting block and the upper fixture; the upper friction block is assembled to the bottom of the upper fixture through the fasteners, the lower friction block is assembled to the top of the lower fixture through the fasteners, the lower fixture is fixed on the reference platform of the friction and wear testing machine, and the lower fixture is also fixedly connected with a friction force sensor; the upper friction block and the lower friction block form a friction pair for simulating the friction contact form of the rim damper block of an aeroengine.

2. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, wherein The fasteners include bolt fasteners; through holes are arranged at the four corners of the upper connecting block, threaded holes are arranged at the corresponding positions of the four corners of the upper fixture, and the through holes, the threaded holes and the bolt fasteners are fitted and clamped.

3. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 2, characterized in that A wedge-shaped groove is arranged on the upper surface of the threaded hole, and a leveling pad block with a wedge-shaped structure is embedded in the wedge-shaped groove; The leveling pad block is used for adjusting the levelness of the upper fixture by adjusting the depth of embedding into the wedge-shaped groove.

4. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, characterized in that, Grooves are arranged at the bottom of the upper fixture and the top of the lower fixture, and the upper friction block and the lower friction block are respectively arranged in the bottom groove of the upper fixture and the top groove of the lower fixture.

5. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, characterized in that A flat groove is arranged on the lower surface of the upper connecting block, and a spherical groove is arranged on the upper surface of the upper fixture; the flat groove is matched with the flat surface of the hemisphere, and the spherical groove is matched with the spherical crown of the hemisphere.

6. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, characterized in that The contact form of the friction pair composed of the upper friction block and the lower friction block includes any one of the following: point contact, line contact, surface contact.

7. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 6, characterized in that, When the contact form of the friction pair is the point contact, the upper friction block is a sphere and the lower friction block is a plane; When the contact form of the friction pair is the line contact, the upper friction block is a cylinder and the lower friction block is a plane; When the contact form of the friction pair is the surface contact, the contact surfaces of the upper friction block and the lower friction block are both planes.

8. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, wherein The upper friction block includes a lower plane and a lower inclined side surface, the lower friction block includes an upper plane and an upper inclined side surface, the lower plane is in frictional contact with the upper plane, and the lower inclined side surface is in frictional contact with the upper inclined side surface.

9. The high-temperature fretting friction coefficient measuring device for the aero-engine rim damping block according to claim 1, wherein The surfaces of the upper connecting block, the fasteners, the hemisphere, the upper fixture, the upper friction block, the lower friction block and the lower fixture are all coated with a metal nitride coating.

10. A method for measuring the high-temperature fretting friction coefficient of an aero-engine rim damping block, characterized in that, Applied to the aeroengine rim damper block high-temperature fretting friction coefficient measuring device according to any one of claims 1-9; the method includes: Install the upper connecting block on the load loading module and the linear reciprocating driving module of the friction and wear testing machine, install the upper fixture with the hemisphere on the upper connecting block, connect and fasten with fasteners, and level; Install the upper friction block and the lower friction block in the bottom groove of the upper fixture and the top groove of the lower fixture respectively, and connect and fasten with fasteners; Install the lower fixture equipped with the lower friction block on the reference platform of the friction and wear testing machine; Turn on the heating module to raise the temperatures of the upper friction block and the lower friction block to the preset temperature; Turn on the loading module to transfer the load from the upper fixture to the upper friction block, and then transfer the load from the upper friction block to the lower friction block; Turn on the linear reciprocating driving module to drive the upper friction block to perform reciprocating linear rolling friction on the surface of the lower friction block and measure the frictional force.

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