Pull rod rotor experimental device capable of constructing radial temperature gradient

Abstract

The invention provides a pull rod rotor experiment device capable of constructing a radial temperature gradient, which comprises a base, a tested assembly, an air supply assembly, a heating element and a measuring assembly, and is characterized in that the tested assembly is rotatably connected to the top of the base and is provided with two adjacent connecting shafts, and the adjacent end surfaces of the two connecting shafts abut against and are matched to form a contact end surface; the tested assembly is provided with an axial flow cavity, and an air inlet and an air outlet which are communicated with the flow cavity and are respectively positioned at two sides of the contact end surface; the air supply assembly is rotationally arranged on the periphery of the connecting shaft in a sleeving manner; the heating piece is arranged on the air supply assembly and located on the periphery of the contact end face; the measuring assembly is used for measuring the radial displacement and the rotating speed of the measured assembly. According to the pull rod rotor experiment device capable of constructing the radial temperature gradient, the technical problem that an existing pull rod rotor dynamic test platform cannot construct a real and controllable radial temperature gradient environment on a rotor contact end face can be solved.

Description

Technical Field

[0001] This invention belongs to the field of rotating machinery testing technology, and more specifically, relates to a tie-rod rotor experimental device capable of constructing a radial temperature gradient. Background Technology

[0002] Tie-rod rotor structures, as key components in high-speed rotating machinery such as gas turbines and turboshaft engines, are widely used in the energy, aviation, and power equipment sectors. These rotors connect multiple discs into a single unit via a central tie rod that provides preload. The contact surfaces (typically curved or planar teeth) bear the primary function of force and torque transmission. During the operation of rotating machinery, the dynamic characteristics of the tie-rod rotor are highly sensitive to the stiffness of the contact interface, which in turn is influenced by factors such as preload, temperature field distribution, material thermal expansion, and fretting behavior. Currently, research institutions at home and abroad have developed a variety of tie rod rotor test platforms, which are mainly divided into two categories: one is a room temperature dynamic test bench for tie rod rotors, which studies the influence of parameters such as tie rod preload, loosening, and machining morphology on rotor dynamics to achieve critical speed testing and vibration response research; the other is a rotor thermal bending test bench under local heating or overall thermal load conditions, which studies the influence of thermal bending on dynamic characteristics by applying overall heating or local thermal shock to the rotor. This type of test bench can simulate certain working conditions (such as local overheating caused by rubbing) and study vibration anomalies caused by overall thermal bending.

[0003] However, in the existing technology, the test platform for rod rotor dynamics can generally only be tested under normal temperature or overall heating conditions. It is impossible to build a real and controllable radial temperature gradient environment on the rotor contact end face, which makes it impossible to study the coupled behavior of tooth surface thermal fretting, contact stiffness change and dynamic characteristics of equipment such as gas turbines during start-up and shutdown. Summary of the Invention

[0004] This invention provides a tie-rod rotor experimental device capable of constructing a radial temperature gradient. By combining external annular heating with internal cold air circulation, a temperature distribution with a higher outer temperature and a lower inner temperature is formed on the contact end face of the tie-rod rotor, thereby constructing a controllable radial temperature gradient. This enables the simulation and testing of the coupled behavior of tooth surface thermal fretting, contact stiffness changes, and dynamic characteristics of equipment such as gas turbines during startup and shutdown.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: A tie-rod rotor experimental device capable of constructing a radial temperature gradient is provided, comprising a base, a tested component, an air supply component, a heating element, and a measuring component. The tested component is rotatably connected to the top of the base and has two adjacent connecting shafts. The adjacent end faces of the two connecting shafts abut against each other to form a contact end face. The tested component has an axial flow cavity. The tested component is provided with an air inlet and an air outlet communicating with the flow cavity and located on both sides of the contact end face, respectively. The air supply component is rotatably sleeved on the outer periphery of the connecting shafts and is used to supply air into the air inlet. The heating element is disposed on the air supply component and is used to heat the air on the outer periphery of the contact end face. The measuring component is disposed on the top of the base and is disposed opposite to the outer peripheral wall of the tested component. The measuring component includes a displacement measuring element for measuring the radial displacement of the tested component and a rotational speed measuring element for measuring the rotational speed of the tested component.

[0006] In one possible implementation, the air supply assembly includes an air circulation sleeve and an air delivery component. The air circulation sleeve is disposed on the top of the base and rotatably sleeved on the outer periphery of the connecting shaft. The air circulation sleeve and the connecting shaft have an air inlet chamber corresponding to the air inlet and an air outlet chamber corresponding to the air outlet. The outer peripheral wall of the air circulation sleeve is respectively provided with an air delivery hole communicating with the air inlet chamber and an air vent communicating with the air outlet chamber. The air delivery component is disposed on one side of the base, and the air delivery component is connected to the air delivery hole through a transparent flexible tube.

[0007] In some embodiments, a heating cavity is located on the outer periphery of the contact end face between the air circulation sleeve and the connecting shaft. The heating cavity is located between the air inlet cavity and the air outlet cavity, and the heating element is located inside the heating cavity.

[0008] In some embodiments, the air circulation sleeve has two heat insulation plates located on both sides of the heating element, with a heating cavity formed between the two heat insulation plates.

[0009] In some embodiments, the air supply component includes an air tank and an air compressor. The air tank is located on one side of the base, and an air outlet pipe is provided on the outer peripheral wall of the air tank. The air outlet pipe is connected to the air supply hole through a transparent flexible tube, and a filter is provided on the air outlet pipe. The air compressor is located on one side of the base and is connected to the air tank through an air supply pipe.

[0010] In some embodiments, a bearing seat is slidably connected to the top of the base, and both ends of the component under test and the air circulation sleeve are mounted on the base via the bearing seat. The bearing seat and the base are slidably connected along the axial direction of the component under test, and the bearing seat is fixed to the base by a fastener.

[0011] In one possible implementation, several displacement measuring elements are spaced apart along the axial direction of the component being measured. Each displacement measuring element includes two fixed seats and two displacement sensors. The two fixed seats are mounted on a base and located on opposite sides of the component being measured. The two displacement sensors are mounted on the two fixed seats in a one-to-one correspondence, with one displacement sensor located above the component being measured and the other displacement sensor located on one side of the component being measured.

[0012] In some embodiments, the fixing base is a magnetic base that is attracted to the base. The top of the fixing base is rotatably connected to a first swing rod that can swing vertically. The outer end of the first swing rod is radially threaded with a locking member. The outer periphery of the locking member is rotatably sleeved with a second swing rod. The locking member can rotate and lock the second swing rod onto the first swing rod. The outer end of the second swing rod is rotatably connected to a fixing rod. A displacement sensor is disposed on the fixing rod.

[0013] In one possible implementation, a rotor disk is fixedly fitted around the outer periphery of the component under test, and a disk screw hole for installing a balancing screw is provided axially through the rotor disk to balance the center of gravity.

[0014] In one possible implementation, the top of the base is provided with a rotary drive member located near the end of the component under test. The rotary drive member has a drive shaft that extends toward the component under test and is coaxial with the component under test. The end of the component under test near the rotary drive member and the outer end of the drive shaft are both provided with couplings, and the two couplings are connected by a rope.

[0015] This embodiment provides a tie-rod rotor experimental device capable of constructing a radial temperature gradient. Compared with existing technologies, the adjacent end faces of the two connecting shafts abut against each other to form a contact end face, providing a basic interface for constructing the temperature gradient. An internal gas flow channel is constructed through the flow cavity formed between the connecting shaft and the long tie rod, as well as the inlet and outlet holes radially penetrating the outer peripheral wall of the connecting shaft, providing a structural basis for internal cavity cooling.

[0016] By rotating the gas supply assembly around the outer circumference of the connecting shaft, a stable gas supply to the inlet is achieved during rotation, ensuring continuous gas flow during the experiment. A heating element, positioned on the gas supply assembly and located on the outer circumference of the contact surface, provides directional heating to the outer periphery of the contact surface, creating a high-temperature thermal boundary condition in the outer ring.

[0017] By setting the displacement measuring device on the top of the base and positioning it opposite to the outer peripheral wall of the component being measured, accurate measurement of the radial displacement of the component being measured is achieved, providing data support for dynamic characteristic analysis.

[0018] By integrating equipment such as rotation speed measuring devices, data acquisition instruments, and computers, a complete data acquisition and analysis system was constructed, realizing the correlation testing of temperature gradient, contact stiffness, and dynamic response.

[0019] This design enables the construction of a controllable radial temperature gradient on the contact end face of the component under test, making the outer ring temperature of the rotor end face significantly higher than the internal temperature. This results in a stable, adjustable, and measurable radial temperature gradient at the contact interface, providing an experimental basis for studying the influence of temperature gradient on contact stiffness and dynamic characteristics. Through the synergistic effect of the above technical features, the controllable construction of an externally heated and internally cooled radial temperature gradient at the contact interface of the tie rod rotor is achieved for the first time. This allows the experimental device to realistically simulate and test the coupled behavior of tooth surface thermal fretting, contact stiffness changes, and dynamic characteristics that occur during the start-up and shutdown of equipment such as gas turbines. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 A schematic diagram of a tie-rod rotor experimental device capable of constructing a radial temperature gradient is provided for an embodiment of the present invention (the rope is not shown). Figure 2 Another structural schematic diagram of a tie-rod rotor experimental device capable of constructing a radial temperature gradient, provided as an embodiment of the present invention (rope not shown). Figure 3 This is an embodiment of the present invention. Figure 2 A schematic diagram of the structure of the tie rod rotor, air circulation sleeve, heating element, measuring assembly, bearing housing, rotor disk, and rotary drive component (rope not shown). Figure 4 This is an embodiment of the present invention. Figure 2 Another structural schematic diagram of the tie rod rotor, air circulation sleeve, heating element, measuring assembly, bearing housing, rotor disk, and rotary drive component (rope not shown). Figure 5 This is an embodiment of the present invention. Figure 3 Schematic diagram of the displacement measuring component; Figure 6 This is an embodiment of the present invention. Figure 3 A front sectional view of the central tie rod rotor, air circulation sleeve, heating element, bearing housing, and rotor disc.

[0022] The following are the labeling elements in the figure: 10. Base; 20. Component under test; 21. Long pull rod; 22. Connecting shaft; 23. Contact end face; 24. Flow chamber; 25. Air inlet; 26. Air outlet; 30. Air supply assembly; 31. Air circulation sleeve; 311. Air inlet chamber; 312. Air outlet chamber; 313. Air delivery port; 314. Vent port; 315. Heating chamber; 32. Air delivery component; 321. Transparent flexible hose; 322. Air tank; 323. Air outlet pipe; 324. Filter; 325. 1. Air compressor; 326. Air supply pipe; 40. Heating element; 41. Heat insulation plate; 50. Measuring component; 51. Displacement measuring component; 511. Fixing base; 512. Displacement sensor; 513. First swing arm; 514. Locking component; 515. Second swing arm; 516. Fixing rod; 52. Speed ​​measuring component; 60. Bearing housing; 61. Fixing component; 70. Rotor disc; 71. Disc screw hole; 80. Rotary drive component; 81. Drive shaft; 90. Coupling. Detailed Implementation

[0023] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0024] It should be noted that when an element is referred to as being "set on" another element, it can be directly on or indirectly on the other element. It should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the invention, "a number" means two or more, unless otherwise explicitly specified.

[0025] Please see Figures 1 to 6The present invention will now describe a tie-rod rotor experimental device capable of constructing a radial temperature gradient. The tie-rod rotor experimental device capable of constructing a radial temperature gradient includes a base 10, a test component 20, an air supply component 30, a heating element 40, and a measuring component 50. The test component 20 is rotatably connected to the top of the base 10 and has two adjacent connecting shafts 22. The adjacent end faces of the two connecting shafts 22 abut against each other to form a contact end face 23. The test component 20 has an axial flow cavity 24. The test component 20 is provided with air inlets 25 communicating with the flow cavity 24 and located on both sides of the contact end face 23. Air outlet 26; air supply component 30 is rotatably sleeved on the outer periphery of connecting shaft 22 for supplying air into air inlet 25; heating element 40 is disposed on air supply component 30 and located on the outer periphery of contact end face 23 for heating air on the outer periphery of contact end face 23; measuring component 50 is disposed on the top of base 10 and is disposed opposite to the outer peripheral wall of the component under test 20. The measuring component 50 includes displacement measuring element 51 for measuring radial displacement of component under test 20 and rotational speed measuring element 52 for measuring rotational speed of component under test 20.

[0026] Furthermore, the tested component 20 also includes two rotor shafts and a long tie rod 21. The two rotor shafts are axially spaced and fixedly sleeved on the outer periphery of the long tie rod 21. Two connecting shafts 22 are axially spaced and fixedly sleeved on the outer periphery of the long tie rod 21 and located between the two rotor shafts. The connecting shafts 22 abut against the adjacent rotor shafts. There is a flow cavity 24 between the connecting shafts 22 and the long tie rod 21. An air inlet 25 communicating with the flow cavity 24 is radially penetrating on the outer peripheral wall of one of the connecting shafts 22, and an air outlet 26 communicating with the flow cavity 24 is radially penetrating on the outer peripheral wall of the other connecting shaft 22.

[0027] Furthermore, the rotation speed measuring component 52 is a laser tachometer.

[0028] Furthermore, a data acquisition device is provided on one side of the base 10. The data acquisition device is connected to the displacement measuring component 51 and the laser tachometer via wires; the data acquisition device is connected to the computer via wires; the data acquisition device is connected to the socket via wires; and the socket is connected to the main power switch via a 220V wire. This application provides a tie-rod rotor experimental device capable of constructing a radial temperature gradient. In actual use, the base 10 provides a rigid reference and mounting interface; the long tie rod 21 of the tested component 20 transmits axial preload; the two rotor shafts and the two connecting shafts 22 together constitute a combination with axial segmentation and radial gradient response characteristics. The air inlet 25 and the air outlet 26 define the starting and ending points of the cold airflow path, forming a closed-loop air path in conjunction with the air supply component 30. The air supply component 30 continuously supplies constant pressure cold air to the air inlet 25 while rotating. After the airflow enters the flow chamber 24, it is driven by centrifugal force and pressure difference to flow along the annular channel and is discharged from the air outlet 26, thereby achieving forced convection cooling of the inner circumferential area of ​​the connecting shaft 22. The heating element 40 forms an annular heat source on the outer periphery of the contact end face 23. The heat is mainly applied to the surface layer of the end face through radiation and convection. Due to the heat insulation structure, the heat diffusion inward is continuously suppressed by the cold airflow, thus forming a temperature decreasing distribution in the radial direction of the end face. Displacement measuring device 51 and speed measuring device 52 synchronously collect the radial vibration response and speed parameters of the rotor under different temperature gradients, providing raw data for subsequent dynamic analysis; As an information hub, the data acquisition instrument completes the time-synchronous acquisition, format conversion, and preliminary filtering of multi-source heterogeneous signals, and uploads the data to the computer in real time for storage and visualization analysis via wired communication.

[0029] This embodiment provides a tie-rod rotor experimental device capable of constructing a radial temperature gradient. Compared with existing technologies, the adjacent end faces of the two connecting shafts 22 abut against each other to form a contact end face 23, providing a basic interface for constructing the temperature gradient. An internal gas flow channel is constructed through the flow cavity 24 formed between the connecting shaft 22 and the long tie rod 21, and the air inlet 25 and air outlet 26 radially penetrating the outer peripheral wall of the connecting shaft 22, providing a structural basis for internal cavity cooling.

[0030] The gas supply assembly 30 is rotatably sleeved on the outer periphery of the connecting shaft 22, enabling stable gas supply to the air inlet 25 during rotation, thus ensuring the continuity of gas flow during the experiment. The heating element 40 is set on the gas supply assembly 30 and located on the outer periphery of the contact end face 23, achieving directional heating of the outer periphery of the contact end face 23, forming a high-temperature thermal boundary condition in the outer ring.

[0031] By setting the displacement measuring element 51 on the top of the base 10 and opposite to the outer peripheral wall of the rotor shaft, the radial displacement of the rotor shaft can be accurately measured, providing data support for dynamic characteristic analysis.

[0032] By integrating equipment such as the rotation speed measuring device 52, data acquisition instrument, and computer, a complete data acquisition and analysis system was constructed, realizing the correlation test of temperature gradient, contact stiffness and dynamic response.

[0033] This design enables the construction of a controllable radial temperature gradient on the contact end face 23 of the component under test 20, making the outer ring temperature of the rotor end face significantly higher than the internal temperature. This results in a stable, adjustable, and measurable radial temperature gradient at the contact interface, providing an experimental basis for studying the influence of the temperature gradient on contact stiffness and dynamic characteristics. Through the synergistic effect of the above technical features, the controllable construction of an externally hot and internally cold radial temperature gradient at the contact interface of the component under test 20 is achieved for the first time. This allows the experimental device to realistically simulate and test the coupled behavior of tooth surface thermal fretting, contact stiffness changes, and dynamic characteristics that occur during the start-up and shutdown of equipment such as gas turbines.

[0034] In one possible implementation, the aforementioned gas supply assembly 30 adopts, as shown in... Figures 1 to 4 and Figure 6 The structure shown is described in the following document. Figures 1 to 4 and Figure 6 The air supply assembly 30 includes an air circulation sleeve 31 and an air delivery component 32. The air circulation sleeve 31 is disposed on the top of the base 10 and rotatably sleeved on the outer periphery of the connecting shaft 22. The air circulation sleeve 31 and the connecting shaft 22 have an air inlet chamber 311 corresponding to the air inlet 25 and an air outlet chamber 312 corresponding to the air outlet 26. The outer peripheral wall of the air circulation sleeve 31 is respectively provided with an air delivery hole 313 communicating with the air inlet chamber 311 and a vent hole 314 communicating with the air outlet chamber 312. The air delivery component 32 is disposed on one side of the base 10, and the air delivery component 32 and the air delivery hole 313 are connected by a transparent flexible tube 321.

[0035] Specifically, the air supply assembly 30 adopts a dynamic-static separation dual-chamber annular structure design. The air circulation sleeve 31 achieves dynamic sealing coupling between the rotating components and the stationary air supply system, solving common problems such as easy leakage, uncontrollable path, and large pressure fluctuations in directional gas delivery under high-speed rotation. Its core lies in constructing a physically isolated, clearly defined, and interface-visible dual-channel inlet / outlet system, ensuring precise injection of cold air into the flow chamber 24 and stable discharge, providing a controllable flow field basis for the formation of a radial temperature gradient.

[0036] The air circulation sleeve 31 is an annular cylindrical component with an inner diameter slightly larger than the outer diameter of the connecting shaft 22, forming a coaxial clearance fit structure. The clearance width is 0.15–0.3 mm, which satisfies both smooth rotation and can be used with the subsequently installed pressure rotary shaft seal (such as the C787 type) to achieve effective dynamic sealing. The air circulation sleeve 31 is made of aluminum alloy or stainless steel, taking into account both lightweight and pressure resistance. Its axial length covers the total span of the area where the air inlet 25 and air outlet 26 are located on the connecting shaft 22, and extends to both ends by 5-10 mm to ensure the cavity sealing. The air circulation sleeve 31 is fixed to the top of the base 10 by means of a flange at the bottom, which is connected to the T-slot slider pre-embedded in the base 10 by four hexagonal socket bolts. After installation, the position can be finely adjusted and locked along the axis of the component under test 20, thereby adapting to the arrangement of connecting shafts 22 with different axial spacings.

[0037] The air supply component 32 provides a stable pressurized air source, which enters the air intake chamber 311 through the air supply port 313 of the air circulation sleeve 31 via the transparent hose 321. Under pressure, the gas in the air intake chamber 311 is injected into the flow chamber 24 between the connecting shaft 22 and the long tie rod 21 through the circumferentially distributed air intake port 25, forming an axially continuous and circumferentially uniform forced convection cooling flow field. The heat-exchanged gas enters the exhaust chamber 312 from the flow chamber 24 through the exhaust port 26, and is then discharged to the atmosphere or the recovery system through the vent port 314. Throughout the process, the air circulation sleeve 31 acts as a rotating intermediary, reliably connecting the stationary air supply system with the high-speed rotating internal flow chamber 24. The dual-chamber isolation design prevents the mixing of inlet and outlet air, and the transparent hose 321 gives the operator the ability to intuitively judge the airflow status.

[0038] The above technical solution enables directional air supply and exhaust functions to achieve stable, controllable, and visual monitoring of the inner cavity of the connection interface under high-speed rotation of the tested component 20. Because the air circulation sleeve 31 and the connecting shaft 22 form a rotational fit relationship, and an air inlet chamber 311 and an air outlet chamber 312 are constructed between them and isolated from each other, gas leakage and path confusion caused by traditional direct-connection air supply can be avoided. Because the air inlet 313 and the air outlet 314 correspond to the air inlet chamber 311 and the air outlet chamber 312 respectively and are staggered, airflow interference can be suppressed and pressure control accuracy can be improved. Because the air supply component 32 is connected to the air inlet 313 through the transparent hose 321, it supports real-time visual judgment of gas flow rate, moisture content, abnormal blockage and other states during the experiment, which significantly improves the reliability and repeatability of data acquisition. In summary, without introducing additional external constraints, the specific technical problem of "easy leakage of air supply structure and uncontrollable airflow path in rotational state" mentioned in the background technology is solved, and the comprehensive technical effect of stable air transmission, precise flow field control and visualization of operation status is achieved.

[0039] Furthermore, two thermocouple temperature sensors are provided on the outer peripheral wall of the air circulation sleeve 31, one of which extends into the air inlet chamber 311 and the other extends into the air outlet chamber 312.

[0040] Furthermore, each connecting shaft 22 is fitted with a set of pressure rotary shaft seals on its outer periphery. The pressure rotary shaft seals are located inside the air circulation sleeve 31. Each set of pressure rotary shaft seals includes two pressure rotary shaft seals arranged opposite each other. One set of pressure rotary shaft seals forms an air inlet chamber 311, and the other set of pressure rotary shaft seals forms an air outlet chamber 312.

[0041] In some embodiments, see Figure 6 The air circulation sleeve 31 and the connecting shaft 22 have a heating cavity 315 located on the outer periphery of the contact end face 23. The heating cavity 315 is located between the air inlet cavity 311 and the air outlet cavity 312, and the heating element 40 is located inside the heating cavity 315.

[0042] Specifically, through a spatially confined cavity layout and a multi-point collaborative temperature measurement structure, a physically isolated, thermally controllable, and parameter-traceable heating region is constructed on the outer periphery of the contact end face 23 of the component under test 20. This enables synchronous, independent, and in-situ monitoring of the temperature states of the heating region, the inlet cooling region, and the outlet heat exchange region. This scheme does not rely on overall heating or external thermal radiation; instead, it uses the geometric position of the cavity as a constraint to precisely anchor the thermal effect to the annular sensitive area of ​​the contact end face 23, while ensuring spatial separation between the cold airflow path and the thermal effect area. This supports the stable formation and quantitative characterization of the radial temperature gradient.

[0043] The air circulation sleeve 31 is equipped with three thermocouple temperature sensors, which extend into the heating chamber 315, the air inlet chamber 311 and the air outlet chamber 312 respectively. This means that the air circulation sleeve 31 has three sets of through holes along the radial or axial direction on its shell, and a temperature sensor probe is embedded in each set of holes. The front end of each probe extends into the corresponding cavity, and the distance between the sensitive element of the probe and the cavity wall is 1mm-5mm, so as to avoid interference from heat conduction on the wall and to accurately reflect the gas or ambient temperature inside the cavity.

[0044] The location of the heating cavity 315 (located on the outer periphery of the contact end face 23) determines the target area of ​​the heat effect; its axially centered arrangement (located between the inlet cavity 311 and the outlet cavity 312) establishes the basis for decoupling the airflow path and the thermal field; the cavity embedding method of the heating element 40 ensures the spatial sealing and controllability of the heat input; the in-situ arrangement of the three thermocouple temperature sensors in the cavity realizes the closed-loop monitoring of the entire chain of heat source intensity (temperature of heating cavity 315), cold source status (temperature of inlet cavity 311), and heat exchange result (temperature of outlet cavity 312).

[0045] Through the above technical solution, this application achieves physical confinement and parameterized monitoring of the thermal effect area on the outer periphery of the contact end face 23 of the tested component 20. When the device is running, the heating element 40 is energized and heated, forming a stable high-temperature ring within the heating chamber 315. The heat acts on the outer periphery of the contact end face 23 through thermal conduction and thermal radiation. After entering through the air inlet chamber 311, the cold air flows along the annular gap between the outer wall of the connecting shaft 22 and the inner wall of the air circulation sleeve 31. Its main path avoids the front of the heating chamber 315, and only undergoes limited heat exchange through the edge of the end face. Subsequently, the airflow enters the air outlet chamber 312 and is discharged, carrying away some of the heat.

[0046] During this process, the three thermocouple temperature sensors provide real-time feedback on the temperature data of their respective cavities: if the temperature of the heating cavity 315 is significantly higher than that of the inlet cavity 311 and the outlet cavity 312, and the temperature of the outlet cavity 312 is higher than that of the inlet cavity 311 but lower than that of the heating cavity 315, it indicates that the radial temperature gradient has been effectively established; the gradient amplitude can be quantified by the difference between the temperature of the heating cavity 315 and the temperature of the outlet cavity 312, and the gradient stability can be evaluated by the time-series fluctuation standard deviation of the temperature difference of the three cavities.

[0047] This scheme does not introduce additional mechanical constraints or change the rotor body structure. It achieves precise control of the thermal field by reconstructing the gap between the air circulation sleeve 31 and the connecting shaft. This solves the technical problems in the background technology, such as the uncontrollable, unmeasurable, and unreproducible temperature gradient caused by the diffusion of the heating area, severe cold and heat interference, and inaccurate temperature measurement points. This makes the study of the stiffness evolution and dynamic response of the contact interface of the tested component 20 under real thermal loads experimentally feasible.

[0048] Furthermore, a thermocouple temperature sensor extending into the heating chamber 315 is also provided on the outer peripheral wall of the air circulation sleeve 31.

[0049] In some embodiments, see Figure 6 The air circulation sleeve 31 has two heat insulation plates 41 located on both sides of the heating element 40, and a heating cavity 315 is formed between the two heat insulation plates 41.

[0050] Specifically, the two heat insulation plates 41 are annular thin plate structures symmetrically arranged on both sides of the heating element 40, and are respectively referred to as the first heat insulation plate 41 and the second heat insulation plate 41; both heat insulation plates 41 are made of aerogel composite material.

[0051] The inner side of the first heat insulation plate 41 is adjacent to the upstream end of the heating element 40 (the side near the air inlet chamber 311), and the inner side of the second heat insulation plate 41 is adjacent to the downstream end of the heating element 40 (the side near the air outlet chamber 312). The two heat insulation plates completely clamp the heating element 40 in the middle area in the axial direction, forming an annular space, namely the heating chamber 315.

[0052] The air circulation sleeve 31 serves as a load-bearing and heat conduction carrier, supporting the spatial layout of the heating element 40 and the heat insulation plate 41, and guiding some of the radial heat to the contact end face 23 through its own metal structure. The heating element 40 provides a controllable heat source, and its heat mainly diffuses radially outward to the surface of the adjacent connecting shaft 22. The two heat insulation plates 41 form an axial thermal barrier, which significantly inhibits the axial conduction of heat from the heating element 40 towards the air inlet chamber 311 and the air outlet chamber 312.

[0053] Through the above technical solution, a radial temperature field with high spatial locality, strong gradient amplitude, and good repeatability is constructed on the outer periphery of the contact end face 23 of the connecting shaft 22. Since the two heat insulation plates 41 are precisely configured on both sides of the heating element 40 and enclose an independent heating cavity 315, their low thermal conductivity effectively blocks the diffusion path of heat along the axial direction to the inlet cavity 311 and the outlet cavity 312, thereby avoiding the preheating of cold air in the inlet cavity 311, temperature measurement distortion in the outlet cavity 312, and a decrease in cooling efficiency; at the same time, it reduces the axial conduction of heat to precision support components such as the bearing seat 60 and angular contact bearings, ensuring the thermal stability and measurement accuracy of the rotating system; ultimately, the temperature distribution in the heating cavity 315 is more concentrated, the gradient change is steeper, and the spatial positioning is more accurate, providing a reliable structural basis and reproducible thermal environment conditions for studying the thermally induced micromotion behavior of the contact interface induced by small temperature gradient changes.

[0054] In some embodiments, see Figure 1 and Figure 2 The air supply component 32 includes an air tank 322 and an air compressor 325. The air tank 322 is located on one side of the base 10. An air outlet pipe 323 is provided on the outer peripheral wall of the air tank 322. The air outlet pipe 323 is connected to the air supply hole 313 through a transparent flexible tube 321. A filter 324 is provided on the air outlet pipe 323. The air compressor 325 is located on one side of the base 10 and is connected to the air tank 322 through an air supply pipe 326.

[0055] Specifically, the air tank 322 is connected to the air compressor 325 via the air supply pipe 326; the air compressor 325 continuously fills the air tank 322 with air, and the tank acts as a pressure stabilizing buffer unit to absorb the exhaust pulsation of the air compressor 325, so that the pressure fluctuation of the outlet pipe 323 is controlled within a predetermined value; the filter 324 performs graded purification of the compressed air to ensure that the cleanliness of the gas entering the transparent hose 321 and the subsequent air outlet 313 is improved.

[0056] Through the above technical solution, this application achieves the following: during the test of the component 20, cooling gas is continuously, stably, and cleanly supplied to the air inlet chamber 311 of the air circulation sleeve 31. Since the air tank 322 eliminates the pressure pulsation of the air compressor 325, the airflow velocity fluctuation entering the air inlet chamber 311 is significantly reduced, ensuring the constant forced convection heat transfer coefficient in the flow chamber 24, thereby maintaining the stable spatial distribution of the radial temperature gradient on the contact end face 23. Because the filter 324 effectively traps moisture, oil, and particulate impurities, it avoids the risk of clogging the air inlet 25, ensuring that cold air forms a uniform and continuous cooling flow field in the annular flow cavity 24 between the long tie rod 21 and the connecting shaft 22. Because the transparent hose 321 combines sealing and visibility, operators can visually identify abnormalities in the air path (such as condensate accumulation or intermittent bubbles) during the experiment and intervene in a timely manner, improving the robustness of the experimental process and the reliability of data acquisition. Because the air compressor 325 and the air tank 322 are arranged separately and the interface is standardized, it is convenient to replace the air tank 322 with different capacities according to the needs of the experimental cycle, or switch to other air source forms, enhancing the adaptability of the device to multi-condition testing.

[0057] Furthermore, the main power switch is connected to the air compressor 325 via a 380V power cord.

[0058] In some embodiments, see Figures 1 to 4 A bearing seat 60 is slidably connected to the top of the base 10. Both ends of the component under test 20 and the air circulation sleeve 31 are set on the base 10 through the bearing seat 60. The bearing seat 60 and the base 10 are slidably connected along the axial direction of the component under test 20. The bearing seat 60 is fixed to the base 10 by the fastener 61.

[0059] Specifically, the top of the base 10 is provided with a guide structure extending along the axial direction of the component under test 20. The guide structure is a T-slot, dovetail groove or linear guide rail, and a sliding pair is formed by combining a T-slot working platform and a T-bolt slider. The bottom of the bearing seat 60 is provided with a matching slider. The bearing seat 60 and the slider can achieve axial free sliding in a pre-tightened but not locked state through fasteners 61 such as internal hexagonal head screws.

[0060] The sliding connection structure gives the bearing housing 60 axial adjustability, enabling it to be precisely positioned according to the actual length of the long tie rod 21, the distance between the two connecting shafts 22, and the preload setting value. After positioning, the fixing member 61 applies sufficient clamping force to rigidly anchor the bearing housing 60 to the base 10, eliminating the slight movement caused by running vibration. As a result, the axial relative position of the support points at both ends of the tested component 20 and the air circulation sleeve 31 can be accurately reproduced and maintained for a long time, which not only ensures the stability of the cross-sectional dimensions of the flow cavity 24, but also allows the preload of the contact end face 23 to be quantitatively controlled through axial fine adjustment.

[0061] Through the above technical solution, this application achieves the following: without changing the main structure of the base 10, it can flexibly adapt to the configuration of the tested component 20 with different axial dimensions (such as replacing the long tie rod 21 of different lengths, increasing or decreasing the number of rotor discs 70, and replacing the straight / arc tooth connecting shaft) by only axial sliding and locking operations of the bearing seat 60. At the same time, it supports fine adjustment of the preload of the contact end face 23, thereby affecting the starting threshold and evolution path of thermally induced micro-motion under the action of temperature gradient. Since the air circulation sleeve 31 and the tested component 20 share the same bearing seat 60 support, the cavity geometry between it and the connecting shaft can be reproduced with high consistency, providing a structural basis for the stable thermal-fluid coupling of the heating cavity 315, the air inlet cavity 311 and the air outlet cavity 312, and ultimately ensuring the repeatability and controllability of the radial temperature gradient construction.

[0062] In one possible implementation, the displacement measuring element 51 described above adopts the following... Figures 1 to 4 The structure shown is described in the following document. Figures 1 to 4 The displacement measuring element 51 is provided at intervals along the axial direction of the component under test 20. The displacement measuring element 51 includes two fixed seats 511 and two displacement sensors 512. The two fixed seats 511 are disposed on the base 10 and are located on both sides of the component under test 20 respectively. The two displacement sensors 512 are disposed on the two fixed seats 511 in a one-to-one correspondence. One displacement sensor 512 is located above the component under test 20, and the other displacement sensor 512 is located on one side of the component under test 20.

[0063] Specifically, the displacement measuring component 51 is provided with three components. The measuring axis of the upper displacement sensor 512 is vertically downward and orthogonal to the axis of the component under test 20. It is used to measure the radial displacement of the journal of the component under test 20 in the Y direction (vertical direction). The measuring axis of the side displacement sensor 512 is horizontally pointing to the axis of the component under test 20. It is orthogonal to the axis of the component under test 20 and perpendicular to the measuring axis of the Y-axis sensor. It is used to measure the radial displacement in the X direction (horizontal direction). The measuring planes of the two components are perpendicular to each other and intersect at the axis of the component under test 20, forming an orthogonal measuring reference plane in the right-hand coordinate system.

[0064] Two fixed bases 511 provide a stable, adjustable, and orthogonal spatial mounting reference for two displacement sensors 512; the two displacement sensors 512 above and to the side respectively capture vibration components in two mutually perpendicular directions within the same cross section; the multiple displacement measuring elements 51 are arranged at intervals along the axial direction, so that the system can simultaneously acquire X / Y two-dimensional vibration data at different axial positions; thus, the data output by a single measuring element can be synthesized into the axis trajectory of the cross section, and the data of multiple measuring elements can be jointly inverted to retrieve the overall mode shape curve of the rotor; when the measured component 20 experiences a local stiffness decrease due to the temperature gradient of the contact end face 23, the axial displacement amplitude in this area will increase significantly, and the X / Y phase difference will shift, thus exhibiting characteristics such as increased ellipticity and changed precession direction in the axis trajectory, providing a direct basis for identifying the position and degree of thermally induced micro-motion.

[0065] Through the above technical solution, this application realizes multi-section, bidirectional, and synchronized measurement of the radial vibration of the tested component 20. Because several displacement measuring elements 51 are spaced apart in the axial direction, they can cover the key stress area of ​​the rotor and identify the spatial distribution characteristics of the bending mode. Because each measuring element is equipped with two fixed seats 511 placed on both sides of the rotor and displacement sensors 512 located on the top and one side respectively, orthogonal X-direction and Y-direction displacement components can be obtained in any axial section, thereby synthesizing the shaft center trajectory and calculating the whirl direction and precession frequency. The above arrangement does not depend on the rotor rotation phase triggering and is suitable for steady-state and transient vibration recording under continuous acceleration / deceleration conditions.

[0066] Therefore, this embodiment effectively overcomes the technical defect that single-point unidirectional measurement cannot reflect the complex deformation morphology of the rotor, and provides a reliable data basis for quantitative analysis of the axial non-uniform evolution of contact stiffness caused by radial temperature gradient.

[0067] In some embodiments, see Figures 1 to 5 The fixed base 511 is a magnetic base that is attracted to the base 10. The top of the fixed base 511 is rotatably connected to a first swing rod 513 that can swing vertically. The outer end of the first swing rod 513 is radially threaded with a locking member 514. The outer periphery of the locking member 514 is rotatably sleeved with a second swing rod 515. The locking member 514 can rotate to lock the second swing rod 515 onto the first swing rod 513. The outer end of the second swing rod 515 is rotatably connected to a fixed rod 516. The displacement sensor 512 is disposed on the fixed rod 516.

[0068] Specifically, the magnetic base provides basic positioning and quick assembly / disassembly; the first swing arm 513 and the fixed base 511 are in the form of a ball joint; the first swing arm 513 and the second swing arm 515 realize coarse adjustment of height and radial distance; the fixed rod 516 realizes fine adjustment of probe normal. The four components work together to enable the displacement sensor 512 to achieve continuous, stepless, and repeatable precise positioning in three-dimensional space, and all adjustment actions do not change the original state of the base 10, avoiding the introduction of installation stress.

[0069] Through the above technical solution, this application achieves the following: during the experiment of the tested component 20, in response to the need for differentiated arrangement, only five actions are required: magnetic seat adsorption / release, first swing rod 513 pitch, locking member 514 tightening / loosening, second swing rod 515 rotation, and fixing rod 516 slight tilting. This allows for the quick completion of the installation, alignment, and locking of a single displacement sensor 512.

[0070] Because the various degrees of freedom of adjustment are decoupled from each other and there is no motion interference, adjusting one dimension will not disturb the parameters of other dimensions that have been set, thus ensuring the spatial consistency and data comparability of multi-point displacement measurements. This structure significantly improves the efficiency of experimental preparation and measurement repeatability, and solves the problems in the background technology, such as large radial displacement measurement error, long working condition switching time, and high data dispersion caused by high sensor installation rigidity and insufficient adjustment degrees of freedom.

[0071] In one possible implementation, the tested component 20 adopts, as follows: Figures 1 to 4 and Figure 6 The structure shown is described in the following document. Figures 1 to 4 and Figure 6 The outer periphery of the component under test 20 is fixedly fitted with a rotor wheel 70, and the rotor wheel 70 is axially provided with a wheel screw hole 71 for installing a balancing screw, which is used to balance the center of gravity.

[0072] Specifically, the rotor disk 70 provides a mass-bearing platform, and the disk screw holes 71 form a standardized balancing interface array. The balancing screws, as variable mass units, change the overall mass moment distribution of the rotor system when screwed into different screw hole positions and depths, thereby offsetting the initial centroid shift caused by material density deviations, machining shape and position errors, or cumulative assembly errors. This balancing mechanism does not rely on external additional structures and is completely built into the rotor body, avoiding increased aerodynamic drag or disruption of thermal field uniformity. It is also compatible with the axial preload structure of the measured component 20 and does not affect the construction and measurement of the temperature gradient at the contact end face 23.

[0073] Through the above technical solution, high-precision, reproducible, and reversible adjustment of the initial imbalance of the tested component 20 system is achieved. Under experimental conditions, when the tested component 20 is running stably, if the fundamental frequency vibration amplitude measured by the three lateral displacement sensors 512 exceeds the predetermined threshold, the operator can select the corresponding phase angle wheel screw hole 71 based on the vibration phase information output by the data acquisition instrument, and screw in an appropriate amount of balancing screws to shrink the center of mass trajectory into the allowable envelope. This significantly suppresses the fundamental frequency imbalance response, improves the test signal-to-noise ratio, and allows the weak dynamic characteristics such as subharmonics, second harmonics, and shaft trajectory distortion caused by the weak change in contact stiffness induced by the temperature gradient to be clearly identified, ensuring the data reliability and analytical effectiveness of the study on the temperature-stiffness-vibration coupling relationship.

[0074] In one possible implementation, the aforementioned base 10 adopts as follows: Figures 1 to 4 The structure shown is described in the following document. Figures 1 to 4 The top of the base 10 is provided with a rotary drive 80 located near one end of the component under test 20. The rotary drive 80 has a drive shaft 81 extending toward the component under test 20 and coaxially arranged with the component under test 20. The end of the component under test 20 near the rotary drive 80 and the outer end of the drive shaft 81 are both provided with couplings 90. The two couplings 90 are connected by ropes.

[0075] Specifically, the tested component 20 is provided with a first coupling 90 at one end near the rotary drive component 80. The first coupling 90 is an elastic sleeve pin coupling 90 with radial floating compensation function. Its inner hole is interference-fitted with the shaft end of the tested component 20, and a through hole is provided for rope winding and positioning. The outer end of the drive shaft 81 is provided with a second coupling 90, which has the same structure as the first coupling 90. The two are arranged in a mirror symmetrical manner to ensure that the force is uniform when the rope is tensioned.

[0076] The transmission relationship formed by the connection between the rotary drive component 80 and the component under test 20 via ropes creates a flexible coupling structure between the drive system and the rotor system. When there is slight installation eccentricity or axial displacement caused by thermal deformation of the drive shaft 81, the ropes, with their axial extensibility and bending flexibility, automatically absorb the resulting angular misalignment and axial movement, preventing the additional bending moment and torsional pulsation from being directly transmitted to the component under test 20. At the same time, the ropes themselves have damping characteristics, which significantly suppress the transmission of background noise such as electromagnetic vibration of the drive motor and bearing vibration to the rotor system.

[0077] The rotary drive component 80 outputs rotational motion, which is transmitted to the second coupling 90 via the drive shaft 81. The rope flexibly transmits this motion to the first coupling 90, thereby driving the entire tested component 20 to rotate around its own centerline. During this process, the coaxially arranged drive shaft 81 and the tested component 20 minimize static misalignment, while the rope connection dynamically compensates for dynamic misalignment caused by thermal expansion differences, support settlement, or bearing clearance during operation. Together, they ensure the pure rotational motion of the rotor system within a wide temperature range and a wide speed range.

[0078] Furthermore, the main power switch is connected to the rotary drive unit 80 via a 380V wire.

[0079] The specific usage method of this device is as follows: Experimental Condition 1: Keep the rated speed of the tested component 20 constant and measure the effect of temperature change on the vibration displacement of the tested component 20.

[0080] 1) All switches in the experimental setup are in the off state. The entire tested component 20, the vibration table, has been connected using bolts, nuts, and other parts. The data acquisition unit, computer, and socket are all placed on the table. First, connect the three longitudinal displacement sensors 512, the three lateral displacement sensors 512, and the three thermocouple temperature sensors to specific locations on the experimental setup. Then, connect all sensors to the data acquisition unit via wires, connect the data acquisition unit to the computer via wires, connect the data acquisition unit to the socket via wires, connect the socket to the main power switch via a 220V wire, connect the air compressor 325 to the main power switch via a 380V wire, and connect the rotary drive component 80 to the main power switch via a 380V wire. Next, connect the air tank 322 to the air compressor 325 via an air supply pipe 326, connect the air circulation sleeve 31 to the air tank 322 via a transparent flexible hose 321, and simultaneously use ropes to sequentially connect and fix the two couplings 90 through the through holes. At this point, the experimental setup is complete.

[0081] 2) Turn on the main power switch, and then turn on the computer, data acquisition instrument, three longitudinal displacement sensors 512, three lateral displacement sensors 512, three thermocouple temperature sensors, and laser tachometer in sequence. Ensure that the computer can display the temperature, displacement, and other indicators of each sensor normally. Turn on the control switch of the air compressor 325 and start the air compressor 325 to fill the air tank 322 until the pressure inside the tank reaches the experimental standard pressure of 6MPa. After maintaining the pressure stability, proceed to the subsequent experimental steps.

[0082] 3) After the pressure reaches the experimental standard pressure and stabilizes, start the rotating drive component 80 and observe the displacement data collected by the computer in real time. If the displacement value exceeds the rated threshold, it indicates that the center of gravity of the rotor disk 70 is not in its center. Immediately stop the rotating drive component 80 and install the balance screw through the disk screw hole 71 to correct the center of gravity. After the correction is completed, restart the rotating drive component 80 for testing. Repeat the adjustment until the displacement data collected by the three longitudinal displacement sensors 512 and the three lateral displacement sensors 512 are always within the rated threshold range, indicating that the rotor disk 70 has reached the balance requirement.

[0083] 4) After confirming that the rotor disk 70 is balanced, restart the rotary drive 80. The rotor disk 70 will start to rotate. By adjusting the input voltage of the rotary drive 80, the rotational speed of the rotor disk 70 is controlled to increase in increments of 1000 r / min. When the vibration frequency exceeds the natural frequency of the T-slot working platform, the displacement change collected by the displacement sensor 512 is the rotor's stable vibration data. The displacement change collected by the computer is observed and recorded in real time until the rotor disk 70 reaches the rated speed of 3000 r / min and is kept running at this speed.

[0084] 5) After the rotor disk 70 reaches 3000 r / min and operates at rated speed for 10 seconds, and the displacement data collected by the computer stabilizes, the gas in the gas storage tank 322 is introduced into the flow chamber 24 through the gas path to create a cooling flow field for the contact end face 23 of the tested component 20. Next, the control switch of the heating element 40 is turned on to heat the outer periphery of the contact end face 23 of the tested component 20, forming a temperature distribution that is higher on the outside and lower on the inside. During this process, the temperature changes of the thermocouple temperature sensor, the numerical changes of the three longitudinal displacement sensors 512 and the transverse displacement sensor 512 are collected and monitored in real time, and the correlation between temperature rise and displacement change is recorded. When the temperature of the thermocouple temperature sensor reaches the experimental standard temperature of 300℃, the start / stop state of the heating element 40 is adjusted to maintain this temperature stably for 10 seconds. In short, the dynamic changes of key indicators such as displacement and temperature are recorded synchronously throughout the entire process, both during the temperature rise and stabilization phases.

[0085] 6) After data recording is complete, turn off the control switch of the heating element 40 to stop heating; stop the acquisition of signals such as displacement, temperature, and rotation speed; turn off the control switch of the rotary drive element 80; after the rotation speed of the tested component 20 drops to 0 r / min, observe the temperature of the thermocouple temperature sensor. If the temperature drops to room temperature, close the gas outlet valve of the gas storage tank 322, turn off the air compressor 325 switch, and turn off the computer, data acquisition instrument, and socket; open the vent valve of the gas storage tank 322 to release the gas inside the tank. After the gas inside the tank drops to normal atmospheric pressure, remove the gas supply pipe 326 and the transparent hose 321. After all experimental devices, connectors, and tools are organized, return them to the designated storage location. Take all sensors, computers, and data acquisition instruments back with you. This experiment is now complete.

[0086] Experimental Condition 2: Keep the temperature gradient constant and measure the effect of acceleration and deceleration of the tested component 20 on the vibration displacement of the tested component 20.

[0087] 1) All switches in the experimental setup are in the off state. The entire tested component 20, the vibration table, has been connected using bolts, nuts, and other parts. The data acquisition unit, computer, and socket are all placed on the table. First, connect the three longitudinal displacement sensors 512, the three lateral displacement sensors 512, and the three thermocouple temperature sensors to specific locations on the experimental setup. Then, connect all sensors to the data acquisition unit via wires, connect the data acquisition unit to the computer via wires, connect the data acquisition unit to the socket via wires, connect the socket to the main power switch via a 220V wire, connect the air compressor 325 to the main power switch via a 380V wire, and connect the rotary drive component 80 to the main power switch via a 380V wire. Next, connect the air tank 322 to the air compressor 325 via an air supply pipe 326, connect the air circulation sleeve 31 to the air tank 322 via a transparent flexible hose 321, and simultaneously use ropes to sequentially connect and fix the two couplings 90 through the through holes. At this point, the experimental setup is complete.

[0088] 2) Turn on the main power switch, and then turn on the computer, data acquisition instrument, three longitudinal displacement sensors 512, three lateral displacement sensors 512, three thermocouple temperature sensors, and laser tachometer in sequence. Ensure that the computer can display the temperature, displacement, and other indicators of each sensor normally. Turn on the control switch of the air compressor 325 and start the air compressor 325 to fill the air tank 322 until the pressure inside the tank reaches the experimental standard pressure of 6MPa. After maintaining the pressure stability, proceed to the subsequent experimental steps.

[0089] 3) After the pressure reaches the experimental standard pressure and stabilizes, start the rotating drive component 80 and observe the displacement data collected by the computer in real time. If the displacement value exceeds the rated threshold, it indicates that the center of gravity of the rotor disk 70 is not in its center. Immediately stop the rotating drive component 80 and install the balance screw through the disk screw hole 71 to correct the center of gravity. After the correction is completed, restart the rotating drive component 80 for testing. Repeat the adjustment until the displacement data collected by the three longitudinal displacement sensors 512 and the three lateral displacement sensors 512 are always within the rated threshold range, indicating that the rotor disk 70 has reached the balance requirement.

[0090] 4) After confirming that the rotor disk 70 is balanced, open the gas outlet valve to allow the gas in the gas storage tank 322 to enter the flow chamber 24 through the gas path, creating a cooling flow field for the contact interface of the component under test 20. Next, turn on the control switch of the heating element 40 to heat the outer periphery of the contact end face 23 of the component under test 20, forming a temperature distribution that is higher on the outside and lower on the inside. Record the temperature rise at the heating chamber 315. When the temperature of the thermocouple temperature sensor reaches the experimental standard temperature of 300℃, adjust the start / stop state of the heating element 40 to maintain stable operation at this temperature. Start the rotation drive 80, and the rotor disk 70 begins to rotate. By adjusting the input voltage of the rotation drive 80, control the rotation speed of the rotor disk 70 to increase in increments of 300 r / min. Observe and record the displacement changes collected by the computer in real time until the rotation speed of the rotor disk 70 reaches the rated speed of 3000 r / min, and maintain this speed stably for 10 seconds.

[0091] 5) After the rotor disk 70 reaches 3000r / min and runs at rated speed for 10s, the input voltage of the rotary drive component 80 is adjusted to control the speed of the rotor disk 70 to decrease by 300r / min. The displacement changes collected by the computer are observed and recorded in real time until the speed of the rotor disk 70 decreases to 0r / min.

[0092] 6) After data recording is complete, stop the data acquisition process of the data acquisition instrument, turn off the control switch of the heating element 40 to stop heating, observe the temperature of the thermocouple temperature sensor displayed on the computer, and wait for the temperature to return to room temperature. Then, close the gas outlet valve of the gas storage tank 322, turn off the air compressor 325, and turn off the computer, data acquisition instrument, and socket. Open the vent valve of the gas storage tank 322 to release the gas in the tank. After the gas in the tank drops to normal atmospheric pressure, remove the gas inlet pipe 326 and the transparent hose 321, disconnect the connecting wires of all devices, and put all experimental devices, connectors, and tools back in the designated storage location. Take all sensors, computers, and data acquisition instruments back with you. This experiment is now complete.

[0093] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A tie-rod rotor experimental apparatus capable of constructing a radial temperature gradient, characterized in that, include: Base; The component under test is rotatably connected to the top of the base and has two adjacent connecting shafts. The adjacent end faces of the two connecting shafts abut against each other to form a contact end face. The component under test has an axial flow cavity. The component under test is provided with an air inlet and an air outlet that communicate with the flow cavity and are located on both sides of the contact end face, respectively. An air supply assembly is rotatably sleeved on the outer periphery of the connecting shaft and is used to supply air into the air inlet. A heating element is disposed on the air supply assembly and is used to heat the air around the outer periphery of the contact end face; as well as A measuring component is disposed on the top of the base and opposite to the outer peripheral wall of the component under test. The measuring component includes a displacement measuring element for measuring the radial displacement of the component under test and a rotational speed measuring element for measuring the rotational speed of the component under test.

2. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 1, characterized in that, The gas supply assembly includes: An air circulation sleeve is disposed on the top of the base and rotatably sleeved on the outer periphery of the connecting shaft. The air circulation sleeve and the connecting shaft have an air inlet chamber corresponding to the air inlet hole and an air outlet chamber corresponding to the air outlet hole. The outer peripheral wall of the air circulation sleeve is respectively provided with an air supply hole communicating with the air inlet chamber and an air vent hole communicating with the air outlet chamber; and An air supply component is disposed on one side of the base, and the air supply component is connected to the air supply port through a transparent flexible tube.

3. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 2, characterized in that, The air circulation sleeve and the connecting shaft have a heating cavity located on the outer periphery of the contact end face. The heating cavity is located between the air inlet cavity and the air outlet cavity, and the heating element is located inside the heating cavity.

4. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 3, characterized in that, The air circulation sleeve has two heat insulation plates located on both sides of the heating element, and the heating cavity is formed between the two heat insulation plates.

5. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 2, characterized in that, The gas transmission component includes: A gas storage tank is disposed on one side of the base. An outlet pipe is provided on the outer peripheral wall of the gas storage tank. The outlet pipe is connected to the gas inlet via the transparent flexible tube. A filter is provided on the outlet pipe. An air compressor is installed on one side of the base and connected to the air tank via an air supply pipe.

6. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 2, characterized in that, A bearing seat is slidably connected to the top of the base. Both ends of the component under test and the air circulation sleeve are mounted on the base via the bearing seat. The bearing seat and the base are slidably connected along the axial direction of the component under test. The bearing seat is fixed to the base by a fastener.

7. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 1, characterized in that, The displacement measuring elements are arranged at intervals along the axial direction of the component being measured, and the displacement measuring elements include: Two mounting brackets are disposed on the base and located on either side of the component under test; and Two displacement sensors are respectively installed on the two fixed bases, one of which is located above the component under test, and the other is located on one side of the component under test.

8. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 7, characterized in that, The fixed base is a magnetic base that is attracted to the base. The top of the fixed base is rotatably connected to a first swing rod that can swing vertically. The outer end of the first swing rod is radially threaded with a locking member. The outer circumference of the locking member is rotatably sleeved with a second swing rod. The locking member can rotate and lock the second swing rod onto the first swing rod. The outer end of the second swing rod is rotatably connected to a fixed rod. The displacement sensor is disposed on the fixed rod.

9. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 1, characterized in that, The outer periphery of the component under test is fixedly fitted with a rotor wheel disk, and the rotor wheel disk has an axially penetrating wheel disk screw hole for installing a balancing screw, which is used to balance the center of gravity.

10. The experimental apparatus for constructing a radial temperature gradient using a tie-rod rotor as described in claim 1, characterized in that, The base has a rotary drive component located at the top near one end of the component under test. The rotary drive component has a drive shaft that extends toward the component under test and is coaxial with the component under test. The component under test has couplings at one end near the rotary drive component and at the outer end of the drive shaft. The two couplings are connected by a rope.

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