Blade bush high-temperature friction and wear test device and test method

Abstract

The application provides a high-temperature friction and wear test device and method for a blade shaft sleeve. The high-temperature friction and wear test device for the blade shaft sleeve comprises a torsion pendulum device connected to a blade sample, the blade sample comprising a blade body and an upper shaft neck of the blade, a bushing sample being arranged on the outside of the upper shaft neck of the blade, the torsion pendulum device being configured to control one side of the blade body to face upward and drive the blade sample to reciprocatingly rotate around the axis of the upper shaft neck, the torsion pendulum device further comprising a torsion pendulum controller and a torque sensor; a load device for steplessly loading a set load on the bushing sample, the load device further comprising a load controller and a force sensor; a high-temperature device for providing a high-temperature cavity, the high-temperature device further comprising a temperature controller and a temperature sensor; and a terminal control device receiving signals of the torque sensor, the force sensor and the temperature sensor and controlling the torsion pendulum controller, the load controller and the temperature controller to apply a set test condition.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and in particular relates to a high-temperature friction and wear test device for blade bushing moving pair under high temperature (e.g., 1000℃) conditions and a test method using the test device. Background Technology

[0002] As a core aerodynamic component of aero-engines, blades play a crucial role in energy conversion and transfer, and their number accounts for a significant proportion of the total number of engine parts. In modern aero-engines, a large number of blades are assembled and fixed to the main engine structure through bushing connections.

[0003] In actual operation, the blade bushing mating surfaces are subjected to harsh working conditions such as high temperature, variable amplitude loads, and multi-dimensional stress states, and their wear failure modes exhibit characteristics significantly different from those of conventional friction pairs. Current experimental research methods for the friction and wear performance of blade bushings have obvious limitations: existing test equipment mostly uses simplified contact modes and constant load application methods, making it difficult to realistically reproduce the complex stress history and dynamic load changes experienced by the blade bushing during engine operation; the test conditions lack consideration for the axial and radial multi-dimensional load coupling effects under actual blade operating conditions, failing to accurately reflect the true friction and wear behavior of the kinematic pair interface.

[0004] For example, Reference 1 reports a friction and wear testing machine specifically designed for testing the wear performance of bushings in stator blade (VSV) mechanisms. This machine employs a sinusoidal reciprocating rotation and a constant radial load, specifically targeting the particular contact configuration of the bushing-main shaft in the VSV adjustment mechanism. However, the motion mode of this method is a regular reciprocating rotation within a preset angle range, and the load application method is a single radial load. This cannot simulate the multi-directional coupled loads and random vibration excitation experienced by the blade bushing under complex operating conditions in aero-engines, and therefore cannot accurately reflect the true friction and wear behavior of the blade bushing.

[0005] Therefore, there is an urgent need to establish a specialized friction and wear testing device and method that can simulate the actual service conditions of blade bushings and achieve precise control of dynamic loads, so as to conduct in-depth research on their wear mechanism and performance evolution law, and provide a scientific basis for the selection of blade bushing materials, optimization of surface treatment processes, and quantitative assessment of service life.

[0006] Reference 1:

[0007] Chen S, Yin N, Yu Q, et al. A novel tribometer for investigating bushing wear[J]. Wear, 2019, 430: 263-271. Summary of the Invention

[0008] To address at least one of the technical problems mentioned in the background art, this application provides a test apparatus and test method for high-temperature friction and wear of blade bushings.

[0009] The blade bushing high-temperature friction and wear testing apparatus according to an embodiment of this application includes: a torsion pendulum device for connecting a blade sample, the blade sample including a blade body and a blade upper journal, a bushing sample disposed on the outer side of the blade upper journal, the torsion pendulum device being configured to control one side of the blade body to face upwards and drive the blade sample to reciprocate around the axis of the blade upper journal, the torsion pendulum device further including a torsion pendulum controller for controlling the torsion pendulum process of the blade sample and a torque sensor for detecting the torque between the blade sample and the bushing sample; a load device for steplessly applying a set load to the bushing sample, the load device further including a load controller for controlling the loading force and a force sensor for detecting the loading force; a high-temperature device for providing a high-temperature chamber with controllable temperature, the high-temperature chamber for accommodating the blade sample and the bushing sample, the high-temperature device further including a temperature controller for controlling the temperature inside the high-temperature chamber and a temperature sensor for detecting the temperature inside the high-temperature chamber; and a terminal control device for receiving signals from the torque sensor, the force sensor and the temperature sensor and controlling the torsion pendulum controller, the load controller and the temperature controller to apply the set test conditions.

[0010] In at least one embodiment, the torsion pendulum device can drive the upper journal of the blade to extend into the high-temperature cavity in the form of a cantilever, and the load device can apply a load to the bushing sample in a direction perpendicular to the axis of the upper journal of the blade, so that the upward side of the upper journal of the blade is always in contact with the bushing sample.

[0011] In at least one embodiment, the torsion device further includes a first rotating shaft and a coupling, wherein the lower journal of the blade sample is connected to the first rotating shaft via the coupling, the lower journal of the blade is insertable into the coupling, the coupling and the lower journal of the blade are circumferentially positioned by a slit, the coupling includes a first part and a second part defining a receiving space for accommodating the lower journal of the blade, the radial distance between the first part and the second part of the coupling is set to be adjustable, the coupling is insertable into the first rotating shaft, the coupling and the first rotating shaft are circumferentially positioned by a slit, the first rotating shaft includes a limiting hole, and a limiting screw can be inserted into the limiting hole to abut against and fix the coupling.

[0012] In at least one embodiment, the loading device further includes a bushing clamp and a loading shaft, the bushing sample being fixed to the bushing clamp, and one end of the loading shaft being ball-jointed to the bushing clamp, such that when the force of the loading shaft is transmitted to the bushing clamp, the bushing clamp is always subjected to a force along the axis pointing from the diameter of the upper journal of the blade to the upper journal of the blade.

[0013] In at least one embodiment, the bushing clamp includes a first clamping arm, a second clamping arm, and an adjusting member. One end of the first clamping arm and the second clamping arm are connected, and the other end is separated. The bushing sample is used to be disposed between the first clamping arm and the second clamping arm. The adjusting member can adjust the degree of separation of the other end of the first clamping arm and the second clamping arm to adjust the degree of clamping of the bushing sample.

[0014] In at least one embodiment, the bushing clamp is provided with a washer having an opening, the opening of the washer being spaced apart from the opening formed between the first clamping arm and the second clamping arm in the circumferential direction of the bushing sample.

[0015] In at least one embodiment, the bushing clamp includes a first conical groove, one end of the loading shaft includes a second conical groove, and the loading device further includes a hinged ball that simultaneously abuts against the inner wall of the first conical groove and the inner wall of the second conical groove.

[0016] In at least one embodiment, a cooling device is further included, comprising at least one of (a) to (f) below: (a) a first water-cooling device for water-cooling the shaft of the torsion device; (b) a second water-cooling device for water-cooling the shaft of the load device; (c) a first air-cooling device for air-cooling the torque sensor; (d) a second air-cooling device for air-cooling the force sensor; (e) a first heat insulation sheet for being disposed between the torque sensor and the high-temperature device; and (f) a second heat insulation sheet for being disposed between the force sensor and the high-temperature device.

[0017] The blade bushing high-temperature friction and wear test method according to the embodiments of this application uses the aforementioned blade bushing high-temperature friction and wear test apparatus.

[0018] In at least one embodiment, the test method includes: the terminal control device controlling the load controller and the temperature controller to simulate the actual working conditions of the friction and wear process between the blade sample and the bushing sample according to the set load spectrum and temperature change curve; the terminal control device controlling the torsion controller to make the blade sample oscillate cyclically according to the set angular velocity and angular displacement, and the blade sample and the bushing sample move relative to each other for a set time.

[0019] In summary, this application achieves friction and wear testing of blade bushings at high temperatures through the integrated design of a torsion device, a load device, a high-temperature device, and a terminal control device. Torque, load, and temperature can be dynamically adjusted to simulate the real working conditions of the blade bushing and accurately reflect the actual friction and wear behavior of the blade bushing under complex engine conditions. Attached Figure Description

[0020] Figure 1 A schematic diagram of the structure of a blade bushing high-temperature friction and wear testing device according to an embodiment of this application is shown.

[0021] Figure 2 A test system diagram of a blade bushing high-temperature friction and wear test apparatus according to an embodiment of this application is shown.

[0022] Figure 3 A perspective view of a blade bushing high-temperature friction and wear testing apparatus according to an embodiment of this application is shown.

[0023] Figure 4 A perspective view of the blade bushing high-temperature friction and wear test apparatus according to an embodiment of this application is shown.

[0024] Figure 5 A perspective view of a torsion pendulum device according to an embodiment of this application is shown.

[0025] Figure 6 A perspective view of a blade sample and a bushing sample according to an embodiment of this application is shown.

[0026] Figure 7 A partially enlarged view of a bushing sample mounted on a blade sample according to an embodiment of this application is shown.

[0027] Figure 8 A perspective view of a blade sample and a bushing sample in an installed state according to an embodiment of this application is shown.

[0028] Figure 9 A cross-sectional view of a blade sample and a bushing sample in an installed state according to an embodiment of this application is shown.

[0029] Figure 10 A perspective view of a load device according to an embodiment of this application is shown.

[0030] Figure 11 A perspective view of a bushing clamp according to an embodiment of this application is shown.

[0031] Figure 12 A perspective view of a loading shaft and bushing clamp according to an embodiment of this application is shown.

[0032] Figure 13 A cross-sectional view of a blade sample and a bushing sample in an installed state according to an embodiment of this application is shown.

[0033] Figure 14 A perspective view of a high-temperature apparatus according to an embodiment of this application is shown.

[0034] Figure 15 A schematic flowchart of a high-temperature friction and wear test method for blade bushings according to an embodiment of this application is shown.

[0035] Figure 16 The temperature load spectrum of the blade bushing friction and wear test according to an embodiment of this application is shown.

[0036] Figure 17 The friction torque-time curve of the blade bushing friction and wear test process according to an embodiment of this application is shown.

[0037] Figure 18 The friction coefficient torque-time curve of the blade bushing friction and wear test process according to an embodiment of this application is shown.

[0038] Explanation of reference numerals in the attached figures

[0039] 1. Blade sample;

[0040] 11. Leaf blade;

[0041] 12. Upper journal of the blade;

[0042] 13. Lower journal of the blade;

[0043] 2. Bushing sample;

[0044] 21. Bushing flange;

[0045] 3. Torsional pendulum device;

[0046] 31. Torsional controller;

[0047] 32 Torque sensors;

[0048] 33. Servo motor for the torsion swing device;

[0049] 34 First pivot;

[0050] 341 Limiting hole;

[0051] 35 Second pivot;

[0052] 36. Couplings;

[0053] 361 Coupling Part 1;

[0054] 362 Coupling Part 2;

[0055] 37. Gear reducer;

[0056] 371 Gearbox bracket;

[0057] 38 bearings;

[0058] 39. Coupling;

[0059] 4. Loading device;

[0060] 41. Load controller;

[0061] 42 Force sensors;

[0062] 43. Bushing clamps;

[0063] 431 First clamping arm;

[0064] 432 Second clamping arm;

[0065] 433 Adjustment component;

[0066] 434 First conical groove;

[0067] 435 gasket;

[0068] 4351 Washer edge guard;

[0069] 44 Load axis;

[0070] 441 Second conical groove;

[0071] 45. Articulated ball;

[0072] 46. ​​Servo motor for load device;

[0073] 47. Lead screw guide rail;

[0074] 48 sliders;

[0075] 5. High-temperature equipment;

[0076] 51. High-temperature cavity;

[0077] 52 Temperature controller;

[0078] 53 Temperature sensor;

[0079] 6. Terminal control device;

[0080] 7. Cooling device;

[0081] 71. First water-cooling equipment;

[0082] 72. Second water-cooling equipment;

[0083] 73. First air-cooled equipment;

[0084] 74 Second air-cooled equipment;

[0085] 75 First heat insulation sheet;

[0086] 76. Second heat insulation sheet;

[0087] 8. Displacement device;

[0088] 81. Lead screw guide rail;

[0089] 82 sliders;

[0090] 83. Handwheel;

[0091] 84 support Detailed Implementation

[0092] Exemplary embodiments of this application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are for teaching those skilled in the art how to implement this application only, and are not intended to exhaustively describe all possible methods of this application, nor to limit the scope of this application.

[0093] For ease of understanding, the elements shown in the various figures may include elements expressed differently from actual dimensions and scales. Furthermore, in the detailed description of the embodiments, for the sake of brevity, this specification does not describe all features of the embodiments in detail.

[0094] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by those skilled in the art to which this application pertains. The terms "first," "second," and similar words used in the description and claims of this application do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The term "and / or" includes any one or more of the terms listed in connection with the application, and all combinations thereof. Words such as "comprising" or "including" indicate that the components or objects preceding "comprising" or "including" encompass the components or objects listed following "comprising" or "including" and their equivalents, and do not exclude other components or objects. Words such as "connected" or "linked" are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0095] In this application, "approximately" means that the conditions described herein can be considered to be met within a reasonable margin of error recognized by a person skilled in the art, and the following description uses this expression to convey a similar meaning.

[0096] Bushing connections can be categorized into two typical application scenarios: the first is adjustable blade systems, which use a drive mechanism to generate active relative motion to optimize airflow angles, adapting to performance requirements under different flight conditions and achieving dynamic control of engine efficiency; the second is blade-structural component mating pairs, which are subjected to multiple excitations during engine operation, including complex aerodynamic loads, centrifugal force fields, and mechanical vibrations, resulting in relative motion between the blade shaft and the corresponding bushing interface. These blade-shoulder friction pairs need to operate in high-temperature environments for extended periods, enduring the combined effects of high temperatures, loads, and complex environments. Their friction and wear performance directly affects the overall system's operational reliability and service life.

[0097] For example, in engine component evaluation tests, it is generally necessary to develop a test load spectrum based on service conditions to simulate the changes in external working conditions throughout the component's life cycle and realistically reflect the component failure process. However, existing aero-engine blade bushing friction and wear test methods generally adopt constant temperature and simple load modes, which cannot effectively simulate the complex operating conditions faced by blade bushings in actual engine operation, such as wide temperature ranges, time-varying temperatures, and dynamic loads. The experimental equipment also has limitations such as complex structure, excessive specialization, and difficulty in adapting to the testing needs of different types of blade bushings, making it difficult to accurately reflect the real friction and wear behavior of blade bushings under complex engine operating conditions.

[0098] Based on this, this application provides a high-temperature friction and wear test device and method for blade bushings, which can simulate friction and wear tests of aero-engine blade bushings with a wide temperature range and time-varying temperature loads. It has a relatively simple structure and can comprehensively evaluate the friction and wear behavior of blade bushings under a wide temperature range and time-varying temperature conditions, providing a reliable and repeatable device and method for friction and wear testing of blade bushings.

[0099] See Figure 1 , Figure 2 , Figure 3 , Figure 4 The blade bushing high-temperature friction and wear test device according to the embodiments of this application may include a torsion pendulum device 3, a load device 4, a high-temperature device 5 and a terminal controller 6, for conducting friction and wear tests on blade sample 1 and bushing sample 2.

[0100] In some non-limiting embodiments, see Figure 1 The torsion pendulum device 3 is connected to the blade sample 1 and drives the blade sample 1 to rotate. Further, see... Figure 6 The blade sample 1 may include a blade body 11 and a blade journal 12, and the torsion device 3 is configured to control one side of the blade body 11 to face upwards (e.g., Figure 8 As shown, the wider blade surface is generally facing upwards, causing the blade sample 1 to reciprocate around the axis of the upper journal 12. See also Figure 7 The bushing sample 2 can be set on the radial outer side of the journal 12 on the blade, and the bushing sample 2 can have a bushing flange 21 to define the relative position of the bushing sample 2 and the blade sample 1.

[0101] See Figure 1 , Figure 5 The torsion device 3 may also include a torsion controller 31 that controls the torsion process of the blade sample 1. For example, the torsion device 3 includes a torsion device servo motor 33, and the torsion controller 31 controls the torsion device servo motor 33 to control the torsion attitude of the blade sample 1 so that it moves according to the set angular displacement and angular velocity.

[0102] See Figure 1 , Figure 5 The torsion pendulum device 3 may further include a torque sensor 32 for detecting the torque between the blade sample 1 and the bushing sample 2. For example, the torsion pendulum device 3 may include a first rotating shaft 34 and a second rotating shaft 35. The first rotating shaft 34 is connected to the blade sample 1, and the second rotating shaft 35 is connected to or forms the output shaft of the torsion pendulum device servo motor 33. A torque sensor 32 is disposed between the first rotating shaft 34 and the second rotating shaft 35. The torque sensor 32 can measure the frictional torque acting on the blade sample 1 in real time, with a sampling frequency up to 100Hz and a minimum detectable torque of 0.001 N·m. See also... Figure 2The terminal controller 6 can receive the frictional torque measured by the torque sensor 32 and control the servo motor 33 of the torsion device to apply reciprocating torque.

[0103] See Figure 8 , Figure 9 The torsion pendulum device 3 may also include a coupling 36, which is disposed at the end of the first rotating shaft 34. The blade sample 1 may also include a blade lower journal 13, which is connected to the first rotating shaft 34 via the coupling 36.

[0104] The lower journal 13 of the blade can be inserted into the coupling 36. The coupling 36 and the lower journal 13 of the blade are circumferentially positioned by cutting edges. The coupling 36 includes a first part 361 and a second part 362 that define a receiving space for accommodating the lower journal 13 of the blade. The radial distance between the first part 361 and the second part 362 of the coupling is set to be adjustable, thereby controlling the tightness of the lower journal 13 of the blade.

[0105] The coupling 36 can be inserted into the first rotating shaft 34. The coupling 36 and the first rotating shaft 34 are circumferentially positioned by cutting the edges. The first rotating shaft 34 includes a limiting hole 341. The limiting screw can be inserted into the limiting hole to abut against and fix the coupling 36, thereby adjusting the tightness of the connection between the coupling 36 and the first rotating shaft 34.

[0106] The torsion device 3 can drive the journal 12 on the blade to extend into the high-temperature device 5 in a cantilever form. For example, the first rotating shaft 34, the coupling 36, and the blade sample 1 can extend horizontally into the high-temperature device 5 in a cantilever form. Accordingly, the materials of the first rotating shaft 34 and the coupling 36 can be high-temperature resistant stainless steel, alloys, etc.

[0107] Because the operating characteristics of aero-engine blades require the blade body to maintain a specific angle with the airflow direction, the contact area between the blade shaft and the bushing is relatively fixed under actual operating conditions (the top of the blade journal contacts the bushing), and this area is also the part with the most severe friction and wear. This application uses coupling 36 to precisely control the blade's attitude in the test environment, ensuring that the area of ​​the blade journal with the most severe actual friction and wear faces upwards and directly contacts the bushing under load, thus realizing the reflection of the friction and wear process under actual operating conditions through testing.

[0108] See Figure 1 , Figure 5 The torsion device 3 may also include a reducer 37, which is connected to the output shaft of the torsion device servo motor 33. The second rotating shaft 35 is connected to the output shaft of the torsion device servo motor 33 via the reducer 37. A coupling 39 may be provided between the second rotating shaft 35 and the reducer 37. The reducer 37 may be connected to the slider 82 (described later) via a reducer bracket 371.

[0109] See Figure 1 The torque sensor 32 may also include multiple bearings 38, which support the first shaft 34 and the second shaft 35.

[0110] In some non-limiting embodiments, see Figure 1 , Figure 10 The load device 4 is used to steplessly apply a set load to the bushing sample 2. For example, the load device 4 includes a load device servo motor 46, a lead screw guide rail 47, a slider 48, and a loading shaft 44. The load device servo motor 46 drives the lead screw in the lead screw guide rail 47 to rotate, and drives the slider 48 connected to the lead screw to output linear motion. One end of the loading shaft 44 is connected to the slider 48, and the other end applies the load to the bushing sample 2. Of course, other structures can also be used to apply the load steplessly, and this application does not limit its specific structure. Compared with the traditional fixed load form, this application proposes stepless loading, which can more accurately simulate the real load.

[0111] See Figure 8 , Figure 9 The loading device 4 can apply a load to the bushing sample 2 in a direction perpendicular to the axis of the upper journal 12 of the blade, ensuring that the upward-facing side of the upper journal 12 of the blade is always in contact with the bushing sample 2. For example, the loading shaft 44 extends vertically into the high-temperature device 5 and applies a load to the bushing sample 2. Accordingly, the material of the loading shaft 44 can be high-temperature resistant stainless steel or alloy, etc.

[0112] See Figure 10 The load device 4 also includes a load controller 41 that controls the loading force. The load controller 41 controls the magnitude of the loading force by controlling the load device servo motor 46. The load device 4 also includes a force sensor 42 that detects the loading force. The force sensor 42 can be positioned between the loading shaft 44 and the slider 48. In one example, the force sensor can measure the force in three directions along the x, y, and z axes, with a sampling frequency of up to 50 Hz, and can record the changes in force on the sample in each direction during the test. See also... Figure 2 The terminal controller 6 can receive the load signal fed back by the force sensor 42 and apply the load according to the load spectrum through the load device servo motor.

[0113] See Figure 11 , Figure 12 , Figure 13 The loading device 4 may also include a bushing clamp 43, to which the bushing sample 2 is fixed. One end of the loading shaft 44 is ball-jointed to the bushing clamp 43, such that when the force of the loading shaft 44 is transmitted to the bushing clamp 43, the bushing clamp 43 is always subjected to a force along the axis pointing from the diameter of the upper journal 12 of the blade to the upper journal 12 of the blade.

[0114] See Figure 11The bushing clamp 43 includes a first clamping arm 431, a second clamping arm 432, and an adjusting member 433. One end of the first clamping arm 431 is connected to one end of the second clamping arm 432, while the other ends are separate. The bushing sample 2 is clamped between the first clamping arm 431 and the second clamping arm 432. For example, when the first clamping arm 431 and the second clamping arm 432 are clamped together, they form a through hole that limits the bushing sample 2, and the bushing sample 2 is fixed in the through hole.

[0115] The adjusting member 433 can adjust the separation degree of the other end of the first clamping arm 431 and the other end of the second clamping arm 432 to adjust the clamping degree of the bushing sample 2. For example, the adjusting member 433 can be a bolt, and the first clamping arm 431 or the second clamping arm 432 is provided with a threaded hole. The tightness between the first clamping arm 431 or the second clamping arm 432 can be adjusted by the tightening degree of the bolt.

[0116] See Figure 11 A washer 435 with an opening can be provided in the bushing clamp 43. The opening of the washer 435 and the opening formed between the first clamping arm 431 and the second clamping arm 432 are spaced apart from the opening of the washer 435 in the circumferential direction (e.g., at a 90° interval). The washer 435 can reduce the deformation effect of lateral shrinkage on the thin-walled bushing, and protect the coating or plating layer on the surface of the bushing parts.

[0117] Furthermore, the end of the washer 435 has a washer retainer 4351. After the washer 435 is inserted into the bushing clamp 43, the washer retainer 4351 abuts against the end face of the bushing clamp 43, thereby fixing the position of the washer 435 in the axial direction. The material of the washer 435 can be a high-temperature alloy.

[0118] See Figure 12 , Figure 13 The bushing clamp 43 includes a first conical groove 434, one end of the loading shaft 44 includes a second conical groove 441, and the load device 4 also includes a hinge ball 45, which simultaneously abuts against the inner wall of the first conical groove 434 and the inner wall of the second conical groove 441.

[0119] The hinge ball 45 is designed to adaptively adjust the relative position of the loading shaft 44 and the bushing clamp 43, ensuring that the relative movement of the bushing sample 2 and the blade sample 1 is not affected by installation deviations or other errors. The hinge ball 45 can be made of ceramic to reduce the impact of thermal expansion on the load. Compared to using a metal hinge ball 45, using a ceramic material avoids adhesion between the metal hinge ball and the metal bushing clamp 43 (first conical groove 434) and the loading shaft 44 (second conical groove 441), thus preventing the hinge ball from affecting the adaptive effect.

[0120] It should be understood that Figure 12 , Figure 13 The loading axis 44 being tilted is an extreme case; under normal circumstances, the loading axis 44 should be as follows: Figure 8 , Figure 9 As shown, it extends along the vertical direction. However, regardless of whether it is tilted, the design of the hinge ball 45 can always transmit a force to the bushing clamp 43 along the axis pointing from the diameter of the blade upper journal 12 to the blade upper journal 12, so that the bushing sample 2 and the blade upper journal 12 have uniform contact and the test can proceed smoothly.

[0121] In some non-limiting embodiments, see Figure 1 , Figure 14 The high-temperature device 5 provides a high-temperature chamber 51 with controllable temperature regulation. The high-temperature chamber 51 accommodates the blade sample 1 and the bushing sample 2. The high-temperature device 5 also includes a temperature controller 52 for controlling the temperature within the high-temperature chamber 51 and a temperature sensor 53 for detecting the temperature within the chamber, such as a thermocouple. It should be understood that... Figure 14 The text only schematically indicates that the high-temperature device 5 has a temperature controller 52 and a temperature sensor 53, without limiting their specific locations. The high-temperature device 5 can be a heating furnace, such as a muffle furnace. See also... Figure 2 The terminal controller 6 can receive the temperature signal fed back by the temperature sensor 53 and control the high-temperature cavity 51 to apply a corresponding temperature field through the temperature controller 52.

[0122] In some non-limiting embodiments, see Figure 2 The terminal control device 6 can simultaneously receive signals from the torque sensor 32, force sensor 42, and temperature sensor 53, and simultaneously control the torsion controller 31, load controller 41, and temperature controller 52 to apply set test conditions and simulate the movement of the blade under actual working conditions. For example, the terminal controller can be a computer.

[0123] In some non-limiting embodiments, see Figure 1 , Figure 5 , Figure 10 The test apparatus also includes a cooling device 7, which may include a first water cooling device 71, a second water cooling device 72, a first air cooling device 73, a second air cooling device 74, a first heat insulation sheet 75, and a second heat insulation sheet 76.

[0124] The first water-cooling device 71 is used for the shaft of the water-cooled torsion device 3. For example, the first water-cooling device 71 includes a copper coil that is wound around the first rotating shaft 34. The copper coil is connected to an external cold source to effectively cool the first rotating shaft 34.

[0125] The second water-cooling device 72 is used to cool the shaft of the water-cooled load device 4. For example, the second water-cooling device 72 includes a copper coil that is wound around the load shaft 44. The copper coil is connected to an external cold source to effectively cool the load shaft 44.

[0126] The first air-cooling device 73 is used to cool the torque sensor 32. For example, the first air-cooling device 73 includes multiple fans arranged opposite to each other to form an air field, covering part of the torque sensor 32 and part of the first connecting shaft 34 and the second connecting shaft 35.

[0127] The second air-cooling device 74 is used for the air-cooling force sensor 42. For example, the second air-cooling device 74 includes multiple fans arranged opposite each other to form an air field, covering the force sensor 42 (e.g. Figure 4 (As shown).

[0128] The first heat insulation sheet 75 can be positioned between the first rotating shaft 34 and the torque sensor 32 to prevent high temperatures from affecting the torque sensor 32. The first heat insulation sheet 75 can be made of ceramic.

[0129] The second heat insulation plate 76 can be placed between the loading shaft 44 and the force sensor 42 to prevent high temperature from affecting the force sensor 42. The second heat insulation plate 76 can be made of ceramic.

[0130] The cooling device 7 can protect the torque sensor, force sensor 32 and force sensor 42 as a whole, ensuring that the test can be carried out stably for a long time.

[0131] In some non-limiting embodiments, see Figure 1 , Figure 3 , Figure 4 The testing apparatus also includes a displacement device 8, which may include a lead screw guide rail 81, a slider 82, a handwheel 83, and a bracket 84. A torsion pendulum device 3 is connected to the slider 82; exemplarily, the torsion pendulum device 3 can be connected to the slider 82 via a bearing 38. The handwheel 83 drives the lead screw in the lead screw guide rail 81 to rotate. The slider 82 and the lead screw form a lead screw-slider mechanism, which in turn drives the slider 82 to slide on the lead screw guide rail 81, thereby causing the torsion pendulum device 3 to slide. The lead screw-slider mechanism has good self-locking performance, ensuring that the relative axial position of the blade test 1 and the bushing sample 2 on the journal 12 of the blade remains unchanged during the test. The lead screw guide rail 81 is mounted on the bracket 84, ensuring that the height of the torsion pendulum device 3 is consistent with the inlet height of the high-temperature device 5.

[0132] The high-temperature friction and wear test method for blade bushings according to the embodiments of this application can be used to test the high-temperature friction and wear test device for blade bushings. The steps of the test method may include: the terminal control device 6 controls the load controller 41 and the temperature controller 52 to simulate the actual working conditions of the friction and wear process between the blade sample 1 and the bushing sample 2 according to the set load spectrum and temperature change curve; the terminal control device 6 controls the torsion controller 31 to make the blade sample 1 oscillate cyclically according to the set angular velocity and angular displacement, and the blade sample 1 and the bushing sample 2 move relative to each other for a set time.

[0133] More specifically, see Figure 15 The test method may include the following steps:

[0134] (S10) Provides a test apparatus, which includes a load device 4, a torsion device 3, a high temperature device 5, and in particular a torque sensor 32 and a force sensor 42, as well as actual blades and bushings.

[0135] (S20) Installation and cooling steps: Install the blades through the coupling 36, install the bushings through the bushing clamp 43, fit the upper journal of the blades with the bushings, and then install the bushing clamp 43 with the loading shaft 44. After installation, turn on the water cooling equipment and fan assembly of the cooling device 7.

[0136] (S30) Heating loading step: The terminal controller 6 controls the high temperature device 5 and the load device 4 to make the test conditions change according to the set load spectrum and temperature curve, thereby simulating the actual working conditions of the blade and bushing friction and wear process.

[0137] (S40) Torque swing step: clear the torque sensor 32 to zero, use the terminal controller 6 to control the torsion swing device 3 to make the blade swing cyclically at the set angular velocity and angular displacement under time-varying working conditions, and the blade bushing moves relative to each other for a preset time.

[0138] (S50) Data acquisition and processing steps: Torque sensor 32 measures the friction torque of the blade bushing, and based on the calculation formula, obtains the friction coefficient-time curve, thereby evaluating the friction and wear performance of the blade bushing under different temperature and load conditions.

[0139] Below, this application also provides a specific experimental embodiment.

[0140] S10 provides a test apparatus, which includes a load device 4, a torsion device 3, a high-temperature device 5, and in particular a torque sensor 32 and a force sensor 42, as well as actual blades and bushings.

[0141] This application simulates the temperature environment and load conditions of components under real-world operating conditions, reproducing the actual relative motion between the blade and the bushing, and assessing the ability to evaluate the friction and wear performance of the blade bushing. In this embodiment, for the friction and wear testing requirements of an adjustable blade bushing for an aero-engine, both the blade and the bushing are made of high-temperature alloys.

[0142] In addition, before the test, the blade and bushing samples can be ultrasonically cleaned for 10 minutes each with acetone, anhydrous ethanol and deionized water, respectively. After cleaning, they should be dried and ready for installation to remove the influence of surface impurities on the test results.

[0143] S20, Installation and Cooling Steps: Install the blades via coupling 36, install the bushings via bushing clamp 43, fit the blade journals with the bushings, then install the bushing clamp 43 with the loading shaft 44, and after installation, turn on the water cooling equipment and fan assembly of the cooling device 7.

[0144] S21, Blade Installation and Attitude Adjustment. Due to the operational characteristics of aero-engine blades, the blade body must maintain a specific angle with the airflow direction. This results in a relatively fixed contact area between the blade journal and the bushing under actual operating conditions, which is also the area experiencing the most severe friction and wear. This application precisely controls the blade's attitude in the test environment, ensuring that the area of ​​the blade journal experiencing the most severe actual friction and wear faces upwards, directly contacting the bushing under load. This allows for the experimental reflection of the blade-shoulder friction and wear process under actual operating conditions.

[0145] First, the blade is fed into the inner hole of the coupling 36 along the axial direction. During the process, the blade can be rotated along the axial direction so that its tangent edge is tightly fitted with the stepped surface of the inner hole of the coupling 36, and the blade and the coupling 36 cannot move relative to each other.

[0146] Then, tighten the bolts to close the inner hole of the coupling 36 and fix it completely to the blade. At this time, the coupling 36 and the blade form a whole and their relative positions are determined.

[0147] The slit shaft at the rear end of coupling 36 is inserted into the axial hole of the first rotating shaft 34. The two are engaged by the slits to transmit torque and rotation. The coupling 36 and the first rotating shaft 34 are fixed by tightening the bolts from both sides of the slits.

[0148] S22, Bushing Installation. To study the friction and wear performance of the blade bushing at high temperatures, it is necessary to ensure that the two move relative to each other at a set angular velocity and angular displacement. Therefore, the bushing must remain stationary in space during the test. To facilitate load application, bushing clamp 43 is used to install and fix the bushing.

[0149] After the bushing is placed inside the washer 435, it is pushed into the through hole of the bushing clamp 43. The washer flange 4351 mates with the surface of the bushing clamp 4351 to determine the position of the bushing. At this time, tightening the bolts clamps the first clamping arm 431 and the second clamping arm 432. Under the clamping force, the washer 435 tightens circumferentially, distributing the clamping force on both sides to a certain extent to the entire circumference, clamping the bushing while avoiding excessive deformation of the bushing. Through this multi-level structural coordination mechanism, the coaxial assembly of the blade and the bushing can be effectively ensured, avoiding uneven circumferential stress and non-ideal contact conditions. This design is of great significance for improving the accuracy and repeatability of test data, especially in friction and wear tests that are sensitive to contact stress under high temperature and high load conditions.

[0150] S23, Blade and Bushing Assembly. After the blades and bushings are installed separately, the blades and bushings must be assembled to ensure that the relative positions of the blades and bushings match the actual operating conditions.

[0151] First, the bushing clamp 43 and the bushing can be fixed in the heating furnace of the high-temperature device 5 using a fixing device. The torsion pendulum device 3 is moved horizontally by the displacement device 8, and the first rotating shaft 34 sends the blade into the heating furnace of the high-temperature device 5. The spatial position of the blade is determined by calculation and on-site debugging. The scale value corresponding to the torsion pendulum device 3 on the lead screw slide rail 81 of the displacement device 8 is recorded at this time. Subsequently, when installing blades of the same model, this scale value can be used as a reference to find the optimal position.

[0152] Subsequently, with the side of the bushing clamp 43 with the first conical groove 434 facing upwards, the bushing is pushed in along the blade axial direction to complete the assembly. At this time, the loading shaft 44 and the bushing clamp 43 are assembled by means of a hinge ball 45, ensuring that the loading shaft 44 and the bushing clamp 43 are as coaxial as possible. The hinge ball 45 is provided between the bushing clamp 43 and the loading shaft 44 to adaptively adjust the relative position of the loading shaft 44 and the bushing clamp 43, compensate for positional deviations during the assembly process, ensure that the load can be transmitted to the blade bushing contact surface along the diameter of the bushing specimen 2, and avoid additional torque affecting the accuracy of the test data.

[0153] S24, turn on cooling device 7. After the blades and bushings are assembled, turn on cooling device 7. First, turn on the water cooling system to allow cooling water at, for example, 26°C to pass through the copper coils, effectively cooling the first rotating shaft 34 and the loading shaft 44. Combined with ceramic heat insulation sheets, this effectively protects the force sensor 42 and torque sensor 32, preventing overheating and equipment damage. Second, turn on the fan groups near the torque sensor 32 and force sensor 42 to form a heat dissipation airflow, improving the heat exchange efficiency near the two sensors, further reducing their temperature, and ensuring the stability of load control and the accuracy of friction torque data recording.

[0154] S30, using terminal control device 6 to control high temperature device 5 and load device 4, so that experimental conditions change according to the set load spectrum and temperature curve, thereby simulating the actual working conditions of the blade and bushing friction and wear process.

[0155] During the operation of an aero-engine, the ambient temperature of the blade bushing changes over time, and the loads they experience are also cyclical. To simulate the friction and wear process of the blade bushing under actual operating conditions as closely as possible, this application establishes a high-temperature friction and wear test system for the blade bushing.

[0156] Under the control of the terminal control device 6, the high-temperature device 5 changes according to the set temperature curve, and the heating rate can reach 50℃ per minute. The maximum heating temperature is 1000℃, which can meet the actual working temperature of most blade bushings in aero engines. It has good heat preservation performance. The temperature near the blade and bushing mating area is measured by the temperature sensor 52 (e.g., thermocouple) to form a closed loop control and realize stable friction and wear test with variable temperature.

[0157] Under the control of the terminal control device 6, the loading shaft 44 moves within a certain height range. The force sensor 42 can measure the load on the loading shaft 44, forming a closed-loop control with the servo motor of the load device. This allows for the application of varying and stable loads to the contact area between the blade and the bushing according to a set load spectrum. For example, applying a load such as... Figure 16 The temperature and load changes are shown.

[0158] S40, the torque sensor 32 is reset to zero, and the terminal control device 6 is used to control the torsion device 3 to make the blades oscillate cyclically at the set angular velocity and angular displacement under time-varying conditions, and the blade bushings move relative to each other until the preset time is reached.

[0159] First, the torque sensor 32 is zeroed to eliminate the initial value and the cooling device 7 is put into operation.

[0160] Subsequently, the blade rotation program is set via terminal control device 6. Information such as the blade rotation angular displacement curve, angular velocity, number of cycles, or running time is determined, and the time intervals for applying different temperature ranges and loads are set to enable continuous high-temperature friction and wear testing of the blade bushing under varying temperature and load conditions.

[0161] After the test conditions are preset, the temperature is maintained for 3 minutes after reaching the required temperature. Then, the load device 4 is run to gradually apply the set load. After stabilization, the load is maintained for 20 seconds.

[0162] At this point, the control program is activated, and the servo motor of the torsional pendulum device 3 drives the blade to perform torsional cyclic motion according to a predetermined motion pattern, thereby simulating the experimental study of blade bushing friction and wear under actual working conditions. In a specific embodiment of this application, the journal diameter of the blade is 8mm, the torsional angular displacement is set to 30°, the angular velocity is 10rpm, and the single relative motion time is set to 2min.

[0163] S50, torque sensor 32 measures the frictional torque of the blade bushing, and based on the calculation formula, obtains the friction coefficient-time curve, thereby evaluating the friction and wear performance of the blade bushing under different temperature and load conditions.

[0164] Before starting the experiment, the torque sensor 32 was turned on to record the frictional torque during the process, and the sampling frequency was set to 100Hz. The results are as follows. Figure 17As shown. After the test, based on the collected torque data and the set loading force, the friction coefficient μ can be calculated using the following formula: .

[0165] Where f is the frictional force (N), P is the test load (N), M is the frictional torque measured by the torque sensor (N·m), and r is the radius of the journal on the blade (m). Figure 18 The friction coefficient-time curve is shown.

[0166] In summary, this application, through the integrated design of the torsion pendulum device 3, the load device 4, the high-temperature device 5, and the terminal control device 6, realizes the friction and wear test of the blade bushing in a temperature range of, for example, 1000℃. During the high-temperature test, the temperature control is stable, the heating rate can reach 50℃ per minute, and the structural components exhibit good strength and stability.

[0167] This application utilizes a high-precision servo motor-driven torsion pendulum device 3 to achieve precise reciprocating motion control of the blade under set angular displacement and angular velocity. Combined with a torque sensor with a sampling frequency of 100Hz and a force sensor with a sampling frequency of 50Hz, it can accurately capture transient torque changes during the friction and wear process of the blade bushing at high temperature, providing reliable experimental data for quantitative evaluation of friction coefficient and wear rate, and providing a reasonable evaluation system for the friction and wear performance of the blade bushing.

[0168] This application provides a dedicated installation method for mechanical limiting of couplings and bushing clamps, suitable for friction and wear testing of blades and bushing samples of different sizes and specifications. The coupling uses mechanical limiting function to precisely control the blade's attitude (such as blade angle) in the test environment, ensuring that the area of ​​most severe actual friction and wear on the blade journal faces upward, ensuring that the attitude is consistent with the actual working conditions, and achieving a reliable connection between the blade and the coupling through edge fitting and bolt fixing.

[0169] This invention achieves dynamic simulation of variable temperature and load conditions through a terminal controller, overcoming the limitations of constant temperature and simple load modes in existing technologies. It establishes a test process for variable temperature and load, and coordinates the torsion device, load device and high temperature device through the terminal controller to realize a complete test cycle of variable temperature-heat preservation-loading-torsion, which realistically simulates the complex working conditions of blade bushings in engine operation, and provides a scientific basis for blade bushing material selection, surface treatment process optimization and service life assessment.

[0170] The heat dissipation design, which combines ceramic heat insulation sheets with water and air cooling, ensures that key components such as torque sensors and force sensors are kept within the allowable operating temperature range.

[0171] The above are preferred embodiments of this application. It should be noted that, for those skilled in the art, corresponding improvements and modifications can be made without departing from the principles of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

[0172] It is understood that some of the components, structures, and constituent parts described above may be omitted without affecting the achievement of one or more objectives of this application. Different embodiments, examples, or aspects may be appropriately combined, as long as they do not contradict or conflict with each other.

[0173] The foregoing has described exemplary embodiments and variations of this application; however, it should be understood that various modifications may be made. For example, if the described techniques are performed in a different order and / or if components in the described system, architecture, device, or circuit are combined in different ways and / or replaced or supplemented by other components or their equivalents, achieving the same, similar, or other suitable results, these changes or modifications also fall within the scope of the claims.

Claims

1. A high-temperature friction and wear testing device for blade bushings, characterized in that, include: A torsion pendulum device (3) is used to connect a blade sample (1), the blade sample (1) including a blade body (11) and a blade upper journal (12), a bushing sample (2) is provided on the outside of the blade upper journal (12), the torsion pendulum device (3) is configured to control one side of the blade body (11) to face upwards and drive the blade sample (1) to reciprocate around the axis of the blade upper journal (12), the torsion pendulum device (3) also includes a torsion pendulum controller (31) for controlling the torsion pendulum process of the blade sample (1) and a torque sensor (32) for detecting the torque between the blade sample (1) and the bushing sample (2). The load device (4) is used to continuously apply a set load to the bushing sample (2). The load device (4) also includes a load controller (41) for controlling the loading force and a force sensor (42) for detecting the loading force. A high-temperature device (5) is used to provide a high-temperature cavity (51) whose temperature can be controlled and regulated. The high-temperature cavity (51) is used to accommodate the blade sample (1) and the bushing sample (2). The high-temperature device (5) also includes a temperature controller (52) for controlling the temperature inside the high-temperature cavity (51) and a temperature sensor (53) for detecting the temperature inside the high-temperature cavity (51). The terminal control device (6) receives signals from the torque sensor (32), the force sensor (42) and the temperature sensor (53) and controls the torsion controller (31), the load controller (41) and the temperature controller (52) to apply the set test conditions.

2. The high-temperature friction and wear testing device for blade bushings according to claim 1, characterized in that, The torsion device (3) can drive the upper journal (12) of the blade to extend into the high-temperature cavity (51) in the form of a cantilever. The load device (4) can apply a load to the bushing sample (2) in a direction perpendicular to the axis of the upper journal (12) of the blade, so that the upward side of the upper journal (12) of the blade is always in contact with the bushing sample (2).

3. The high-temperature friction and wear testing device for blade bushings according to claim 2, characterized in that, The torsion device (3) further includes a first rotating shaft (34) and a coupling (36), wherein the lower journal (13) of the blade sample (1) is connected to the first rotating shaft (34) via the coupling (36). The lower journal (13) of the blade can be inserted into the coupling (36). The coupling (36) and the lower journal (13) of the blade are circumferentially positioned by a mitered edge. The coupling (36) includes a first part (361) and a second part (362) defining a receiving space for accommodating the lower journal (13) of the blade. The radial distance between the first part (361) and the second part (362) of the coupling is set to be adjustable. The coupling (36) can be inserted into the first rotating shaft (34). The coupling (36) and the first rotating shaft (34) are circumferentially positioned by cutting the edges. The first rotating shaft (34) includes a limiting hole (341). The limiting screw can be inserted into the limiting hole (341) to abut against and fix the coupling (36).

4. The high-temperature friction and wear testing device for blade bushings according to claim 1, characterized in that, The load device (4) further includes a bushing clamp (43) and a loading shaft (44). The bushing sample (2) is fixed to the bushing clamp (43). One end of the loading shaft (44) is ball-jointed to the bushing clamp (43), so that when the force of the loading shaft (44) is transmitted to the bushing clamp (43), the bushing clamp (43) is always subjected to a force along the axis of the blade upper journal (12) pointing to the blade upper journal (12) along the diameter of the blade upper journal (12).

5. The high-temperature friction and wear testing device for blade bushings according to claim 4, characterized in that, The bushing clamp (43) includes a first clamping arm (431), a second clamping arm (432), and an adjusting member (433). One end of the first clamping arm (431) and the second clamping arm (432) are connected, and the other end is separated. The bushing sample (2) is used to be placed between the first clamping arm (431) and the second clamping arm (432). The adjusting member (433) can adjust the degree of separation of the other end of the first clamping arm (431) and the second clamping arm (432) to adjust the degree of clamping of the bushing sample (2).

6. The high-temperature friction and wear testing device for blade bushings according to claim 5, characterized in that, The bushing clamp (43) is provided with a washer (435) having an opening. The opening of the washer (435) and the opening formed between the first clamping arm (431) and the second clamping arm (432) are separated from the opening of the washer (435) in the circumferential direction of the bushing sample (2).

7. The high-temperature friction and wear testing device for blade bushings according to claim 4, characterized in that, The bushing clamp (43) includes a first conical groove (434), one end of the loading shaft (44) includes a second conical groove (441), and the load device (4) also includes a hinge ball (45), which simultaneously abuts against the inner wall of the first conical groove (434) and the inner wall of the second conical groove (441).

8. The high-temperature friction and wear testing device for blade bushings according to claim 1, characterized in that, It also includes a cooling device (7), which comprises at least one of (a) to (f) below: (a) A first water-cooling device (71) for water-cooling the shaft of the torsion device (3); (b) A second water-cooling device (72) for water-cooling the shaft of the load device (4); (c) A first air-cooling device (73) for air-cooling the torque sensor (32); (d) A second air-cooling device (74) for air-cooling the force sensor (42); (e) A first heat insulation sheet (75) is provided between the torque sensor (32) and the high-temperature device (5); (f) A second heat insulation sheet (76) is used to be disposed between the force sensor (42) and the high temperature device (5).

9. A method for testing high-temperature friction and wear of blade bushings, characterized in that, The blade bushing high-temperature friction and wear test apparatus according to any one of claims 1 to 8.

10. The method for high-temperature friction and wear testing of blade bushings according to claim 9, characterized in that, The test method includes: The terminal control device (6) controls the load controller (41) and the temperature controller (52) to simulate the actual working conditions of the friction and wear process between the blade sample (1) and the bushing sample (2) according to the set load spectrum and temperature change curve. The terminal control device (6) controls the torsion controller (31) to make the blade sample (1) swing cyclically according to the set angular velocity and angular displacement, and the blade sample (1) and the bushing sample (2) move relative to each other for a set time.

Images