Aviation Turbine Engine Fireproof Coating Test and Evaluation System and Method

Abstract

The present invention discloses a test and evaluation system and method for a fireproof coating of an aero-turbine engine, which includes a base frame, a rubbing member, a simulated specimen and a driving assembly. One end of the rubbing member is rotatably connected to the base frame, and the other end is provided with a rubbing groove in a circular ring structure. The driving assembly includes a base having a lateral movement stroke on the base frame, and the simulated specimen is fixedly arranged on the base. A test part is provided on the side of the simulated specimen, and the test part can be subjected to fireproof coating treatment to simulate the rubbing end of a component with a fireproof coating of an aero-turbine engine. The test part faces the rubbing groove, so that the test part invades the rubbing groove with the lateral movement of the base to complete the rubbing test. The test part is used to simulate the component with a fireproof coating, and the rubbing member is used to simulate the rubbing pair in the working area of the component with a coating. The effect evaluation and performance assessment of the fireproof coating of the aero-turbine engine in a simulated service environment are carried out in accordance with the principle of matching the operating conditions, the oncoming flow environment and the fault characteristics.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and specifically to a test evaluation system and method for a fireproof coating of an aero-turbine engine. Background Art

[0002] The thrust-to-weight ratio of aero-turbine engines is continuously increasing, and the working environment is more severe. Therefore, it is required that the materials used to manufacture aero-turbine engines can resist environmental erosion such as salt spray and withstand the action of internal flow field loads such as high temperature, high pressure, and high-speed scouring. Lightweight and high-strength materials represented by titanium alloys have been widely used in aero-turbine engines.

[0003] Due to advantages such as high specific strength, low density, high melting point, and good corrosion resistance, titanium alloys are used to manufacture components such as fan blades, compressor casings, and blades in aero-turbine engines.

[0004] Currently, at home and abroad, three technical approaches are mainly used to solve the titanium fire problem: improving engine design, developing flame-retardant titanium alloy materials, and researching and developing fireproof (or flame-retardant) coatings. Fireproof (or flame-retardant) coatings have been widely used in engineering due to their relatively simple process, low cost, good maintainability, and obvious flame-retardant and fireproof effects.

[0005] For the evaluation and assessment of the performance and effect of the fireproof coating of an aero-turbine engine, the current method is to conduct a comparative test, that is, to divide a certain number of identical specimens into two groups, and apply a fireproof coating to one of the groups; then conduct high-temperature oxidation tests and thermal cycle load tests on these two groups of specimens under the same test conditions. By measuring data such as temperature and weight loss, the performance parameters of the fireproof coating are calculated according to relevant processing specifications. Compared with the service environment of the fireproof coating in an aero-turbine engine, this evaluation and assessment method does not consider the internal stress state of the materials of the components with the fireproof coating in the service environment. Therefore, there is a large difference between the test performance and the actual use performance. Summary of the Invention

[0006] Aiming at the deficiencies in the above-mentioned prior art, the present invention provides a test evaluation system and method for a fireproof coating of an aero-turbine engine, which completes the evaluation and assessment of the fireproof coating in the service environment by closely combining the test evaluation and performance assessment with the service environment.

[0007] To achieve the above object, the present invention provides a test evaluation system for a fireproof coating of an aero-turbine engine, including a base frame, a rubbing member, a simulated specimen, and a driving assembly;

[0008] One end of the rubbing member is rotatably connected to the base frame, and the other end is provided with a rubbing groove in a circular ring structure;

[0009] The driving assembly comprises a base, the base has a lateral movement stroke on the base frame, the simulation specimen has a fireproof coating, the bottom end of the simulation specimen is fixed on the base, and the top end of the simulation specimen extends vertically upward;

[0010] The side of the simulation specimen is provided with a test part, and the test part is treated with a fire retardant coating according to the test requirements to simulate the rubbing end of the aircraft turbine engine with a fire retardant coating component;

[0011] The test part faces the rubbing groove, so that the test part gradually penetrates into the rubbing groove along with the lateral movement of the base, and completes the rubbing test with the rotating rubbing member.

[0012] In one of the embodiments, the drive assembly further includes a mounting platform;

[0013] The installation platform is slidably connected to the base frame in the longitudinal direction, and the base is slidably connected to the installation platform in the transverse direction.

[0014] In one of the embodiments, a load simulation mechanism is provided on the mounting platform for applying bending stress load and / or torsional stress load and / or tensile stress load to the simulated specimen.

[0015] In one embodiment, the load simulation mechanism includes a first driving assembly, a first rotating shaft, a connecting assembly and a loading lever;

[0016] The first rotating shaft is rotatably connected to the base, and the length direction of the first rotating shaft is parallel to the horizontal direction, the bottom end of the connecting component is fixedly connected to the first rotating shaft, and the top end of the connecting component extends vertically upward;

[0017] The loading lever is arranged horizontally, and one end of the loading lever is fixedly connected to the top of the connecting assembly, and the other end of the loading lever is fixedly connected to the top of the simulation specimen;

[0018] The first driving assembly is transmission-connected to the first rotating shaft, and is used for driving the first rotating shaft to rotate, and driving the connecting assembly and the loading lever to rotate around the first rotating shaft, thereby applying a bending stress load to the simulation specimen.

[0019] In one of the embodiments, the load simulation mechanism further includes a second drive assembly;

[0020] The connecting assembly includes a connecting cylinder and a second rotating shaft, the bottom end of the connecting cylinder is fixedly connected to the first rotating shaft, the bottom end of the second rotating shaft is rotatably connected to the connecting cylinder, and the loading lever is fixedly connected to the top end of the second rotating shaft;

[0021] The second driving component is in transmission connection with the second rotating shaft, and is used to drive the second rotating shaft to rotate, and drive the loading lever to rotate around the second rotating shaft, so as to apply a torsional stress load to the simulated specimen.

[0022] In one embodiment, the load simulation mechanism further includes a third driving component, a tension plate and a guide rod;

[0023] The top end of the guide rod is fixedly connected with the loading lever, and the bottom end of the guide rod extends vertically downward;

[0024] A tension loading bump is arranged on the simulated specimen. One end of the tension plate is slidably connected to the guide rod in the vertical direction, and the other end extends towards the simulated specimen and is located directly below the tension loading bump;

[0025] The third driving member is in transmission connection with the tension plate, and is used to drive the tension plate to slide along the guide rod, so as to apply a tensile stress load to the simulated specimen.

[0026] In one embodiment, the bottom end of the simulated specimen is fixedly arranged on the base through a multi-parameter sensor, so as to measure the bending stress load and / or torsional stress load and / or tensile stress load of the simulated specimen and the rubbing load in the rubbing test.

[0027] In one embodiment, the test part has a first test surface and a second test surface that are perpendicular to each other, and are used to respectively simulate the rubbing end surface and the rubbing side surface of the parts of the aero-turbine engine with a fireproof coating;

[0028] The rubbing groove has a first rubbing surface and a second rubbing surface that are perpendicular to each other. When the test part is embedded in the rubbing groove, the first rubbing surface is parallel to the first test surface and there is a first rubbing gap therebetween, and the second rubbing surface is parallel to the second test surface and there is a second rubbing gap therebetween.

[0029] In one embodiment, a plurality of first grooves are arranged at equal intervals in the circumferential direction of the rubbing groove on the first rubbing surface; and / or

[0030] A plurality of second grooves are arranged at equal intervals in the circumferential direction of the rubbing groove on the second rubbing surface.

[0031] To achieve the above object, the present invention also provides a method for testing and evaluating the fireproof coating of an aero-turbine engine, and uses the above aero-turbine engine fireproof coating test and evaluation system to conduct a rubbing test.

[0032] An aviation turbine engine fireproof coating test and evaluation system and method provided by the present invention simulate the components with fireproof coatings of an aviation turbine engine through a test unit, and at the same time simulate the rubbing pair in the operating environment of the components through a rubbing part. The evaluation and assessment of the fireproof coating of the aviation turbine engine are carried out according to the principle of matching the operating conditions, the oncoming flow environment, and the fault characteristics, closely combining the evaluation and assessment conditions with the service environment to complete the verification of the performance of the fireproof coating. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following-described drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0034] Figure 1 Is the first axonometric view of the rubbing test system in the embodiment of the present invention;

[0035] Figure 2 Is the second axonometric view of the rubbing test system in the embodiment of the present invention;

[0036] Figure 3 Is the axonometric view of the simulated specimen in the embodiment of the present invention;

[0037] Figure 4 Is the structural schematic diagram of the rubbing part in the first implementation manner in the embodiment of the present invention, used for the friction test between the rubbing part and the simulated specimen;

[0038] Figure 5 Is the structural schematic diagram of the rubbing part in the second implementation manner in the embodiment of the present invention, used for the collision or rubbing test between the rubbing part and the simulated specimen. In the collision test, the groove depth of the rubbing part is greater than the maximum deformation of the simulated specimen, and in the rubbing test, the groove depth of the rubbing part is less than the maximum deformation of the simulated specimen;

[0039] Figure 6 Is the structural schematic diagram of the rubbing part in the third implementation manner in the embodiment of the present invention, realizing the simulation of the collision test in the external scraping and rubbing;

[0040] Figure 7 Is the structural schematic diagram of the rubbing part in the fourth implementation manner in the embodiment of the present invention, realizing the simulation of the collision + friction test in the external scraping and rubbing;

[0041] Figure 8 Is the structural schematic diagram of the rubbing part in the fifth implementation manner in the embodiment of the present invention, realizing the simulation of the collision test in the internal extrusion rubbing;

[0042] Figure 9 This is a schematic structural diagram of the rubbing component in the sixth implementation manner in the embodiments of the present invention, realizing the simulation of the collision + friction test in internal extrusion rubbing;

[0043] Figure 10 This is a partial schematic diagram of the load loading mechanism in the embodiments of the present invention;

[0044] Figure 11 This is a schematic structural diagram of the rubbing test system in the embodiments of the present invention under the condition of loading bending stress on the simulated specimen;

[0045] Figure 12 This is a schematic structural diagram of the rubbing test system in the embodiments of the present invention under the condition of loading torsional stress on the simulated specimen.

[0046] Reference numerals in the drawings:

[0047] Rubbing component 1, rubbing groove 101, first rubbing surface 102, second rubbing surface 103, first groove 104, second groove 105, matching mass block 106, elastic beam 107, friction ring 108;

[0048] Simulated specimen 2, test part 201, first test surface 202, second test surface 203, tensile loading bump 204;

[0049] Base 3, first rotating shaft 301, second bracket 302, third driving rod 303, first worm 304, first worm gear 305, second bearing 306, first handwheel 307;

[0050] Base plate 4, first bracket 401, transmission shaft 402, first bearing 403, first support rod 404, first support seat 405, first driver 406, first driving rod 407;

[0051] Installation platform 5, second support rod 501, second support seat 502, second driver 503, second driving rod 504;

[0052] Loading lever 6, tensile plate 601, guide rod 602, fifth driving rod 603, third handwheel 604;

[0053] Connecting cylinder 7, second rotating shaft 701, third bearing 702, third bracket 703, fourth driving rod 704, second worm 705, second worm gear 706, fourth bearing 707, second handwheel 708;

[0054] Multi-parameter sensor 8.

[0055] The realization, functional features and advantages of the object of the present invention will be further described with reference to the embodiments and the accompanying drawings. Specific implementation manners

[0056] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0057] It should be noted that all the directional indications (such as up, down, left, right, front, back,...) in the embodiments of the present invention are only used to explain the relative positional relationship and movement conditions between components in a specific posture (as shown in the drawings). If the specific posture changes, the directional indications will also change accordingly.

[0058] In addition, in the present invention, descriptions such as "first" and "second" are only for descriptive purposes, and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0059] In the present invention, unless otherwise clearly defined and limited, terms such as "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, a physical connection or a wireless communication connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0060] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present invention.

[0061] Such as Figures 1-12Shown is a rubbing test system of an aviation turbine engine fireproof coating under load simulation according to this embodiment, which mainly includes a base frame, a rubbing member 1, a simulated specimen 2 and a driving assembly. One end of the rubbing member 1 is rotatably connected to the base frame, and the other end is provided with a rubbing groove 101 in a circular ring structure; the driving assembly includes a base 3, the base 3 has a lateral movement stroke on the base frame, the bottom end of the simulated specimen 2 is fixedly installed on a multi-parameter sensor 8 on the base 3, and the top end of the simulated specimen 2 extends vertically upward; a test portion 201 is provided on the side of the simulated specimen 2 for simulating the rubbing end of a component with a fireproof coating; the test portion 201 faces the rubbing groove 101, so that the test portion 201 gradually penetrates into the rubbing groove 101 as the base 3 moves laterally, and a rubbing test is completed with the rotating rubbing member 1.

[0062] In this embodiment, the rubbing member 1 is used to simulate the rubbing pair of a component with a fireproof coating in an operating state. Specifically, the rubbing member 1 is selected with the same material and processing technology as the casing or stator blade. The rubbing groove 101 has a first rubbing surface 102 and a second rubbing surface 103 that are perpendicular to each other, which are respectively used as the end rubbing surface and the side rubbing surface of the rubbing pair. The simulated specimen 2 is selected with the same material and technology as the actual component with a fireproof coating. Specifically, a test portion 201 is provided on the side of the simulated specimen 2 for the rubbing end of the component with a fireproof coating. The test portion 201 has a first test surface 202 and a second test surface 203 that are perpendicular to each other, which are used to respectively simulate the rubbing end surface and the rubbing side surface of the rubbing pair of the component with a fireproof coating of an aeroengine. During the rubbing test, when the test portion 201 is embedded in the rubbing groove 101, the first rubbing surface 102 and the first test surface 202 are parallel to each other and have a first rubbing allowance therebetween, which is used to simulate the rubbing in the internal extrusion mode, and the second rubbing surface 103 and the second test surface 203 are parallel to each other and have a second rubbing allowance therebetween, which is used to simulate the rubbing in the external scraping mode.

[0063] The rubbing member 1 in this embodiment has six implementation manners:

[0064] The first manner is as Figure 4 shown. In this implementation manner, the first rubbing surface 102 and the second rubbing surface 103 are continuous circular ring structures, and the rubbing member 1 in this implementation manner is used to simulate a continuous friction test;

[0065] The second manner is as Figure 5 shown. In this implementation manner, a plurality of first grooves 104 are equidistantly arranged along the circumferential direction of the rubbing groove 101 on the first rubbing surface 102, and a plurality of second grooves 105 are equidistantly arranged along the circumferential direction of the rubbing groove 101 on the second rubbing surface 103. That is, the first rubbing surface 102 and the second rubbing surface 103 are tooth surface structures, and the rubbing member 1 in this implementation manner is used to simulate an intermittent collision or rubbing test.

[0066] The third method is as follows Figure 6 As shown, in this embodiment, the rubbing member 1 only has the first rubbing surface 102. The rubbing member 1 is a disc-shaped structure. A transmission shaft connecting the driving component is arranged at the center of the circle at one end of the rubbing member 1. There is a rubbing groove 101 coaxial with the transmission shaft at the other end of the rubbing member 1. The rubbing groove 101 is a circular sunk groove structure. The first rubbing surface 102 is the side wall surface of the rubbing groove 101. The rubbing member 1 has a number of matching mass blocks 106 and elastic beams 107. There are four matching mass blocks 106 and four elastic beams 107, and they correspond one by one. The matching mass blocks 106 are fan-shaped columnar structures with the same curvature as the first rubbing surface 102. The first ends of the four elastic beams 107 are connected to the first rubbing surface 102 at equal intervals, and the tails all face the center of the rubbing groove 101. The center of the long arc wall surface of the fan shape of the matching mass block 106 is arranged at the tail end of the corresponding elastic beam 107, and the center of the short arc wall surface of the fan shape of the matching mass block 106 faces the center of the rubbing groove 101. The test part 201 on the simulation specimen 2 is a plate-shaped structure. During the rubbing test, after the simulation specimen 2 is inserted into the rubbing groove 101, it makes a linear displacement in the direction of the first rubbing surface 102 until a collision occurs with the matching mass block 106 but no friction occurs with the first rubbing surface 102. After the collision occurs, the matching mass block 106 generates a small displacement and recovers under the action of the elastic beam 107, thereby realizing the simulation of the collision test in external scraping rubbing.

[0067] The fourth method is as follows Figure 7As shown in the figure, in this embodiment, the rubbing member 1 only has the first rubbing surface 102. The rubbing member 1 is in a disc-shaped structure. A transmission shaft connecting the driving component is arranged at the center position of one end of the rubbing member 1. The other end of the rubbing member 1 has a rubbing groove 101 coaxial with the transmission shaft. The rubbing groove 101 is a circular sunk groove structure. The first rubbing surface 102 is the side wall surface of the rubbing groove 101. The rubbing member 1 has a friction ring 108, a number of matching mass blocks 106 and elastic beams 107. There are four matching mass blocks 106 and elastic beams 107 respectively corresponding to each other. The matching mass block 106 is a sector-shaped columnar structure with the same curvature as the first rubbing surface 102 and the friction ring 108. The first ends of the four elastic beams 107 are connected to the first rubbing surface 102 at equal intervals, and the second ends all face the center of the rubbing groove 101 and are connected to the outer wall surface of the friction ring 108 at equal intervals, so that the friction ring 108 and the first rubbing surface 102 are concentric. The long arc wall surface of the sector of the matching mass block 106 is connected to the inner wall surface of the friction ring 108. The center of the short arc wall surface of the sector of the matching mass block 106 faces the center of the rubbing groove 101. And the matching mass block 106 and the corresponding elastic beam 107 are located on the same radial line of the friction ring 108. The test part 201 on the simulation specimen 2 is in a plate-shaped structure. During the rubbing test, after the simulation specimen 2 is inserted into the rubbing groove 101, it makes a linear displacement in the direction of the first rubbing surface 102 until a collision occurs with the matching mass block 106 and at the same time friction occurs with the inner wall surface of the friction ring 108. After the collision occurs, the matching mass block 106 and the friction ring 108 produce a small displacement and recover under the action of the elastic beam 107, thereby realizing the simulation of both rubbing and friction tests in the external scraping rubbing.

[0068] The fifth way is as Figure 8As shown, in this implementation, the rubbing component 1 only has the first rubbing surface 102. The rubbing component 1 is in a disc-shaped structure. Transmission shafts for connecting the driving component are arranged at the center positions of both ends of the rubbing component 1. The rubbing surface 102 is the side wall surface of the rubbing component 1. The rubbing component 1 has a number of matching mass blocks 106 and elastic beams 107. Both the matching mass blocks 106 and the elastic beams 107 are four in number and correspond one by one. The matching mass blocks 106 are in a sector-columnar structure with the same curvature as that of the rubbing surface 102. The first ends of the four elastic beams 107 are connected to the rubbing surface 102 at equal intervals, and the second ends are all located on the radial extension line of the rubbing component 1. The center of the short arc wall surface of the sector of the matching mass block 106 is set at the second end of the corresponding elastic beam 107, and the center of the long arc wall surface of the sector of the matching mass block 106 is located on the radial extension line of the rubbing component 1. The test part 201 on the simulated specimen 2 is in a plate-shaped structure, and the axis of the test part 201 and the rubbing component 1 are in the same plane. During the rubbing test, the test part 201 on the simulated specimen 2 makes a linear displacement towards the direction of the rubbing surface 102 until a collision occurs with the matching mass block 106 but no friction occurs with the rubbing surface 102. After the collision occurs, the matching mass block 106 produces a small displacement and recovers under the action of the elastic beam 107, thereby realizing the simulation of the collision test in the internal extrusion rubbing.

[0069] The sixth way is as Figure 9As shown in the figure, in this embodiment, the rubbing member 1 only has a first rubbing surface 102. The rubbing member 1 is a disc-shaped structure. Transmission shafts for connecting the driving assembly are arranged at the center positions of both ends of the rubbing member 1. The first rubbing surface 102 is the side wall surface of the rubbing member 1. The rubbing member 1 has a friction ring 108, a number of matching mass blocks 106 and elastic beams 107. Both the number of matching mass blocks 106 and elastic beams 107 is four and they correspond to each other one by one. The elastic beams 107 and the matching mass blocks 106 are both four in number. The matching mass blocks 106 are sector-shaped columnar structures with the same curvature as the first rubbing surface 102 and the friction ring 108. The first ends of the four elastic beams 107 are connected to the first rubbing surface 102 at equal intervals, and the second ends are all located on the radial extension line of the rubbing member 1 and are connected to the inner wall surface of the friction ring 108 at equal intervals. The short arc wall surface of the sector of the matching mass block 106 is connected to the outer wall surface of the friction ring 108. The center of the long arc wall surface of the sector of the matching mass block 106 is located on the radial extension line of the rubbing member 1, and the matching mass block 106 and the corresponding elastic beam 107 are located on the same radial line of the friction ring 108. The test part 201 on the simulation specimen 2 is a plate-shaped structure, and the axis of the test part 201 and the rubbing member 1 are in the same plane. During the rubbing test, the test part 201 on the simulation specimen 2 makes a linear displacement towards the direction of the first rubbing surface 102 until it collides with the matching mass block 106 and at the same time can also generate friction with the outer wall surface of the friction ring 108. After the collision occurs, the matching mass block 106 and the friction ring 108 generate a small displacement and recover under the action of the elastic beam 107, thereby realizing the simulation of both rubbing and friction tests in the internal extrusion rubbing.

[0070] In the specific implementation process, the rubbing member 1 is rotationally connected to the base frame through a transmission shaft 402. Specifically, the base frame includes a bottom plate 4 and a first bracket 401. The bottom end of the first bracket 401 is fixedly connected to the bottom plate 4 by bolts, and the top end extends vertically up and down. The top end of the first bracket 401 is rotationally connected with a first bearing 403. One end of the transmission shaft 402 is fixedly fitted with the inner ring of the first bearing 403, and the other end is fixedly connected to the rubbing member 1. Moreover, a high-speed motor (not shown in the figure) is also arranged on the first bracket 401. Driven by the high-speed motor, the rubbing member 1 rotates at a high speed with the transmission shaft 402 as the axis, thereby completing the rubbing test between the rubbing member 1 and the test part 201.

[0071] In this embodiment, the driving assembly further includes an installation platform 5. The installation platform 5 is slidably connected to the base frame longitudinally, and the base 3 is slidably connected to the installation platform 5 transversely.

[0072] In this embodiment, a plurality of first support rods 404 are arranged at intervals along the horizontal direction on the bottom plate 4, and the length direction of the first support rods 404 is parallel to the longitudinal direction, and both ends of each first support rod 404 are rotatably connected to the bottom plate 4 through the first support seat 405. The mounting platform 5 has first sliding holes corresponding to the first support rods 404 one by one and penetrating the mounting platform 5 along the longitudinal direction, that is, the mounting platform 5 is slidably connected to the bottom plate 4 along the longitudinal direction through the cooperation between the first support rods 404 and the first sliding holes. Furthermore, a first driver 406 is provided on the base plate 4, and a first driving rod 407 capable of manual or electric rotation is provided on the first driver 406, and a first worm gear structure is provided inside the first driver 406, and the first driving rod 407 is transmission-connected to at least one first support rod 404 through the first worm gear structure, and the first support rod 404 transmission-connected to the first driving rod 407 is a threaded rod, and the corresponding first sliding hole is a threaded hole, that is, the first support rod 404 is driven to rotate by the first driving rod 407, and then the mounting platform 5 is driven to make longitudinal linear motion, and finally the test part 201 on the simulated specimen is aligned with the friction groove 101.

[0073] In this embodiment, a plurality of second support rods 501 are arranged at intervals along the longitudinal direction on the mounting platform 5, and the length direction of the second support rods 501 is parallel to the transverse direction, and both ends of each second support rod 501 are rotatably connected to the mounting platform 5 through the second support seat 502. The base 3 has second sliding holes corresponding to the second support rods 501 and penetrating the base 3 in the transverse direction, that is, the base 3 is slidably connected to the mounting platform 5 in the transverse direction through the cooperation between the second support rods 501 and the second sliding holes. Furthermore, a second driver 503 is provided on the mounting platform 5, and a second driving rod 504 which can be rotated manually or electrically is provided on the second driver 503, and a second worm gear structure is provided inside the second driver 503, and the second driving rod 504 is transmission-connected to at least one second support seat 502 through the second worm gear structure, and the second support seat 502 transmission-connected to the second driving rod 504 is a threaded rod, and the corresponding second sliding hole is a threaded hole, that is, the second support seat 502 is driven to rotate by the second driving rod 504, and then the base 3 is driven to make a lateral linear motion, so that the test part 201 gradually feeds into the friction groove 101, and finally the friction test between the friction part 1 and the test part 201 is realized.

[0074] In this embodiment, a load simulation mechanism is provided on the mounting platform 5 for applying bending stress load and / or torsional stress load and / or tensile stress load to the simulated specimen 2, so that the rubbing test is closer to the actual situation.

[0075] Specifically, the load simulation mechanism includes a first driving assembly, a first rotating shaft 301, a connecting assembly and a loading lever 6. The first rotating shaft 301 is rotatably connected to the base 3, and the length direction of the first rotating shaft 301 is parallel to the horizontal direction. The bottom end of the connecting assembly is fixedly connected to the first rotating shaft 301, and the top end of the connecting assembly extends vertically upward. The loading lever 6 is arranged horizontally, and one end of the loading lever 6 is fixedly connected to the top end of the connecting assembly, and the other end is fixedly connected to the top end of the simulation specimen 2. The first driving assembly is connected to the first rotating shaft 301 in a transmission manner, and is used to drive the first rotating shaft 301 to rotate, and drive the connecting assembly and the loading lever 6 to rotate around the first rotating shaft 301, thereby applying a bending stress load to the simulation specimen 2.

[0076] In the specific implementation process, the first drive assembly includes a second bracket 302, a third drive rod 303, a first worm 304 and a first worm wheel 305. The bottom end of the second bracket 302 is fixedly connected to the base 3 by bolts, and the third drive rod 303 is rotatably connected to the top of the second bracket 302 through a second bearing 306, and the length direction of the third drive rod 303 is parallel to the longitudinal direction. The first worm 304 is fixedly sleeved on the third drive rod 303, and the first worm wheel 305 is a fan-shaped structure, and the worm gear of the first worm wheel 305 is located in the arc segment of the fan-shaped structure. The tip of the first worm wheel 305 is provided with a first mounting hole corresponding to the first rotating shaft 301, that is, the first worm wheel 305 is fixedly connected to the first rotating shaft 301 through the key of the first mounting hole, and the first worm 304 and the first worm wheel 305 are meshed with each other. The third driving rod 303 can rotate under manual or electric drive, and then under the transmission of the first worm 304 and the first worm wheel 305, the first rotating shaft 301 rotates around itself, and drives the connecting assembly and the loading lever 6 to rotate around the first rotating shaft 301, thereby applying a bending stress load to the simulated specimen 2. In this embodiment, a first hand wheel 307 is provided at the end of the third driving rod 303 for manually driving the third driving rod 303 to rotate.

[0077] More specifically, the load simulation mechanism further includes a second driving assembly. The connecting assembly includes a connecting cylinder 7 and a second rotating shaft 701, the bottom end of the connecting cylinder 7 is fixedly connected to the first rotating shaft 301, the bottom end of the second rotating shaft 701 is rotationally connected to the connecting cylinder 7 through a third bearing 702, and the loading lever 6 is fixedly connected to the top of the second rotating shaft 701. The second driving assembly is transmission-connected to the second rotating shaft 701, and is used to drive the second rotating shaft 701 to rotate, and drive the loading lever 6 to rotate around the second rotating shaft 701, thereby applying a torsional stress load to the simulated specimen 2.

[0078] In the specific implementation process, the second drive assembly includes a third bracket 703, a fourth drive rod 704, a second worm 705 and a second worm wheel 706. One end of the third bracket 703 is coaxially fixedly installed with the connecting tube 7 at the top through a fixed sleeve, and the fourth drive rod 704 is rotatably connected to the other end of the third bracket 703 through a fourth bearing 707, and the length direction of the third drive rod 303 is parallel to the longitudinal direction. The second worm 705 is fixedly installed on the fourth drive rod 704, and the second worm wheel 706 is a fan-shaped structure, and the worm gear teeth of the second worm wheel 706 are located in the arc segment of the fan-shaped structure. The fan-shaped root of the second worm wheel 706 is provided with a second mounting hole corresponding to the second rotating shaft 701, that is, the second worm wheel 706 is fixedly connected to the second rotating shaft 701 through the cooperation of the key of the second mounting hole, and the second worm 705 and the second worm wheel 706 are meshed with each other. The fourth driving rod 704 can rotate under manual or electric drive, and then under the transmission of the second worm 705 and the second worm wheel 706, the second rotating shaft 701 rotates around itself, and drives the loading lever 6 to rotate around the second rotating shaft 701, thereby applying a torsional stress load to the simulated specimen 2. In this embodiment, a second hand wheel 708 is provided at the end of the fourth driving rod 704 for manually driving the fourth driving rod 704 to rotate.

[0079] More specifically, the load simulation mechanism further includes a third driving component, a tension plate 601 and a guide rod 602. The top of the guide rod 602 is fixedly connected to the loading lever 6, and the bottom of the guide rod 602 extends vertically downward. A tensile loading protrusion 204 is provided on the simulated specimen 2, one end of the tension plate 601 is vertically slidably connected to the guide rod 602, and the other end extends in the direction of the simulated specimen 2 and is located directly below the tensile loading protrusion 204. The third driving member is transmission-connected to the tension plate 601, and is used to drive the tension plate 601 to slide along the guide rod 602, thereby applying a tensile stress load to the simulated specimen 2.

[0080] In the specific implementation process, the third driving member includes a fifth driving rod 603, the top end of which is rotatably connected to the loading lever 6, the bottom end of which is a threaded rod, and a threaded hole corresponding to the fifth driving rod 603 is provided on the stretching plate 601. The fifth driving rod 603 can be rotated under manual or electric drive, so that the stretching plate 601 can make vertical linear motion along the guide rod 602, and at the same time, the stretching plate 601 cooperates with the stretching loading protrusion 204 to stretch the simulated specimen 2 upward, thereby applying a tensile stress load to the simulated specimen 2. In this embodiment, a third hand wheel 604 is provided at the end of the fifth driving rod 603, which is used to manually drive the fifth driving rod 603 to rotate.

[0081] As a preferred embodiment, the number of the tensile loading bumps 204 is two, and the two tensile loading bumps 204 are symmetrically located on both sides of the simulated specimen 2 along the thickness direction of the simulated specimen 2. An embedding groove is provided at one end of the tensile plate 601 facing the loading lever 6. After the simulated specimen 2 is located in the embedding groove, both ends of the tensile plate 601 are simultaneously located directly below the two tensile loading bumps 204. Further, during the upward displacement of the tensile plate 601, tensile stress loads can be applied to the simulated specimen 2 through the two tensile loading bumps 204 at the same time, so that the simulated specimen 2 can be stretched more stably, making the rubbing test closer to the actual situation.

[0082] It should be noted that the bottom end of the simulated specimen 2 is fixedly arranged on the base 3 through the multi-parameter sensor 8 to measure the bending stress load and / or torsional stress load and / or tensile stress load of the simulated specimen 2 and the rubbing load in the rubbing test. Furthermore, the input of the bending stress load and / or torsional stress load and / or tensile stress load can be controlled to complete the rubbing test under different working conditions.

[0083] It should be noted that the specific configurations and installation forms of the base 3, the installation platform 5, the second bracket 302, and the third bracket 703 in this embodiment are not limited to Figures 1-2 the form shown, and Figures 10-12 the form shown can also be adopted.

[0084] In this embodiment, the number of the test parts 201 on the simulated specimen 2 is two, and the two test parts 201 are vertically spaced and located on the side of the simulated specimen 2, which is easy to ensure the dynamic balance of the rubbing parts and can complete two groups of rubbing tests at the same time.

[0085] Based on the above rubbing test of the aviation turbine engine fireproof coating test and evaluation system, a method for testing and evaluating the aviation turbine engine fireproof coating is also disclosed in this embodiment, specifically:

[0086] Make the simulated specimen 2 reach the preset tensile stress value, deflection value, and torsion value through the load loading mechanism;

[0087] Start the high-speed motor to make the rubbing part 1 reach the preset rubbing rotation speed value;

[0088] Make the rubbing part 1 rub against the test part 201 at a set step length, and adjust the step length of the rubbing assembly according to the rubbing stress to ensure the stability of the test working condition;

[0089] Measure the load data of relevant characteristic points and the temperature data of the characteristic parts of the simulated specimen during the test process;

[0090] When failures such as the peeling of the fireproof coating, the fracture of the simulated specimen, or ignition occur or after reaching the preset time, the test ends.

[0091] The above are only the preferred embodiments of the present invention, and do not limit the patent scope of the present invention accordingly. Any equivalent structural transformation made by using the content of the specification and drawings of the present invention under the inventive concept of the present invention, or any direct / indirect application in other related technical fields shall be included within the patent protection scope of the present invention.

Claims

1. An aviation turbine engine fireproof coating test and evaluation system, characterized in that It includes a base frame, friction parts, simulated test pieces and drive components; One end of the friction member is rotatably connected to the base frame, and the other end is provided with a friction groove of a circular ring structure; The driving assembly comprises a base, the base has a lateral movement stroke on the base frame, the simulation specimen has a fireproof coating, the bottom end of the simulation specimen is fixed on the base, and the top end of the simulation specimen extends vertically upward; The side of the simulation specimen is provided with a test part, and the test part is treated with a fire retardant coating according to the test requirements to simulate the rubbing end of the aircraft turbine engine with a fire retardant coating component; The test part faces the friction groove, so that the test part gradually penetrates into the friction groove along with the lateral movement of the base, and completes the friction test with the rotating friction member; The drive assembly also includes a mounting platform; The mounting platform is connected to the base frame in a longitudinal sliding manner, and the base is connected to the mounting platform in a transverse sliding manner; The mounting platform is provided with a load simulation mechanism for applying bending stress load, torsional stress load and tensile stress load to the simulated specimen; The load simulation mechanism includes a first driving assembly, a first rotating shaft, a connecting assembly and a loading lever; The first rotating shaft is rotatably connected to the base, and the length direction of the first rotating shaft is parallel to the horizontal direction, the bottom end of the connecting component is fixedly connected to the first rotating shaft, and the top end of the connecting component extends vertically upward; The loading lever is arranged horizontally, and one end of the loading lever is fixedly connected to the top of the connecting assembly, and the other end of the loading lever is fixedly connected to the top of the simulation specimen; The first driving assembly is connected to the first rotating shaft in a transmission manner, and is used to drive the first rotating shaft to rotate, and drive the connecting assembly and the loading lever to rotate around the first rotating shaft, thereby applying a bending stress load to the simulated specimen; The load simulation mechanism further includes a second drive assembly; The connecting assembly includes a connecting cylinder and a second rotating shaft, the bottom end of the connecting cylinder is fixedly connected to the first rotating shaft, the bottom end of the second rotating shaft is rotatably connected to the connecting cylinder, and the loading lever is fixedly connected to the top end of the second rotating shaft; The second driving assembly is connected to the second rotating shaft in a transmission manner, and is used to drive the second rotating shaft to rotate, and drive the loading lever to rotate around the second rotating shaft, thereby applying a torsional stress load to the simulated specimen; The load simulation mechanism also includes a third driving assembly, a stretching plate and a guide rod; The top end of the guide rod is fixedly connected to the loading lever, and the bottom end of the guide rod extends vertically downward; The simulation specimen is provided with a tensile loading protrusion, one end of the tensile plate is vertically slidably connected to the guide rod, and the other end extends toward the simulation specimen and is located directly below the tensile loading protrusion; The third driving assembly is transmission-connected to the stretching plate and is used to drive the stretching plate to slide along the guide rod, thereby applying a tensile stress load to the simulation specimen.

2. The aviation turbine engine fireproof coating test and evaluation system according to claim 1, characterized in that, The bottom end of the simulated specimen is fixedly arranged on the base through a multi-parameter sensor for measuring the bending stress load and / or torsional stress load and / or tensile stress load of the simulated specimen and the rubbing load in the rubbing test.

3. The aviation turbine engine fireproof coating test and evaluation system according to claim 1 or 2, characterized in that The test part has a first test surface and a second test surface perpendicular to each other, which are used to respectively simulate the rubbing end face and the rubbing side face of the rubbing end of the component with a fireproof coating of an aero-turbine engine; The rubbing groove has a first rubbing surface and a second rubbing surface perpendicular to each other. After the test part is embedded in the rubbing groove, the first rubbing surface is parallel to the first test surface and there is a first rubbing margin therebetween, and the second rubbing surface is parallel to the second test surface and there is a second rubbing margin therebetween.

4. The aviation turbine engine fireproof coating test and evaluation system according to claim 3, characterized in that, A plurality of first grooves are arranged at equal intervals along the circumferential direction of the rubbing groove on the first rubbing surface; and / or A plurality of second grooves are arranged at equal intervals along the circumferential direction of the rubbing groove on the second rubbing surface.

5. A method for experimental evaluation of a fireproof coating for an aero-turbine engine, characterized in that, The rubbing test under the service condition load simulation is carried out by using the aero-turbine engine fireproof coating test and evaluation system according to any one of claims 1 to 4.

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