Aerospace engine adjustable static vane bushing multi-physical field coupling wear test device

Abstract

This application discloses a multi-physics field coupled wear testing device for adjustable stator bushings of aero-engines, belonging to the field of aero-engine rotor wear testing technology. To address the problems of existing test benches being unable to accurately simulate complex stress conditions of bushings, difficulty in decoupling load components, and insufficient equipment adaptability, this application includes a support unit, a test spindle unit, and a test housing unit. Both the test spindle unit and the test housing unit are mounted on the support unit. The bushing specimen to be tested is placed between the test spindle unit and the test housing unit. The relative motion between the test spindle unit and the test housing unit simulates the working state of the bushing specimen. The test spindle unit integrates a loading component for simulating the working conditions of the bushing specimen, and the test housing unit integrates an environmental simulation component for simulating the working environment of the bushing specimen. This application is mainly used as a device for wear testing of adjustable stator bushings of aero-engines.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine rotor wear testing technology, specifically relating to a multi-physics field coupled wear testing device for adjustable stator bushings of aero-engines. Background Technology

[0002] The variable stator vane (VSV) adjustment mechanism is a key system in modern aero-engine compressors for controlling the flow field and improving surge margin. Under actual engine operating conditions, the friction pair formed by the blade journal and the casing bushing is in an extremely complex mechanical environment. Due to the aerodynamic forces acting on the blade body, the bushing not only bears radial loads (FR) and axial loads (FA), but also a huge bending moment (MB) generated by load offset, resulting in a non-uniform compressive stress distribution at the bushing edge.

[0003] Most existing bushing wear testing devices employ a single mechanical static loading method, which struggles to simulate the coupling effect of axial thrust and dynamic vibration loads under real aerodynamic conditions. This results in significant discrepancies between the wear morphology obtained from tests and actual damage. Furthermore, bushings undergo extreme cold to extreme heat during service, and traditional equipment often struggles to integrate high-precision temperature control field simulation within a compact space. Moreover, existing devices are typically designed for specific models and cannot accommodate bushings of various specifications, leading to high development costs and poor versatility. Therefore, developing a testing device capable of decoupled three-dimensional load loading, possessing wide-temperature-range simulation capabilities, and allowing for rapid reconfiguration of the installation inner diameter is of significant engineering value for improving the overall performance of aero-engines. Summary of the Invention

[0004] In order to solve the problems that existing test benches cannot accurately simulate the complex stress conditions of bushings, the load components are difficult to decouple, and the equipment is not adaptable enough, this invention provides a multi-physics field coupled wear test device for adjustable stator bushings of aero-engines.

[0005] A multi-physics field coupled wear test device for adjustable stator bushings of aero-engines is disclosed. The wear test device includes a support unit, a test spindle unit, and a test housing unit. The test spindle unit and the test housing unit are both mounted on the support unit. The bushing specimen to be tested is placed between the test spindle unit and the test housing unit. The working state of the bushing specimen to be tested is simulated by the relative motion between the test spindle unit and the test housing unit. The test spindle unit integrates a loading component for simulating the working conditions of the bushing specimen to be tested, and the test housing unit integrates an environmental simulation component for simulating the working environment of the bushing specimen to be tested.

[0006] Furthermore, the support unit includes a base and two brackets. The two brackets are arranged opposite each other on the top of the base along the center line of the base length direction, and each bracket is detachably connected to the base. The test spindle unit is supported and fixed by the two brackets, and the test housing unit is supported and fixed by the base.

[0007] Furthermore, the test spindle unit includes a power drive motor and a test spindle. The power drive motor is mounted on the top of a bracket and is detachably connected to the bracket. One end of the test spindle is connected to the power output shaft of the power drive motor via a coupling. A bearing support is mounted on the other end of the test spindle, and the test spindle and the bearing support are rotatably connected via a bearing. The bearing support is mounted on the top of another bracket and is detachably connected to the bracket. The loading component is integrated on the test spindle.

[0008] Furthermore, the loading component is a three-dimensional decoupled loading system, which includes a radial force loading module, a pneumatic axial loading module, and a dynamic bending moment simulation module. The radial force loading module and the dynamic bending moment simulation module are both mounted on the test spindle. The pneumatic axial loading module is located on the outside of the test spindle. A high-pressure gas inlet is machined on the end of the test spindle away from the power drive motor. The gas output end of the pneumatic axial loading module is connected to the high-pressure gas inlet.

[0009] Furthermore, the test spindle is a combined spindle structure, comprising a stepped shaft section and an end connecting shaft section. The end connecting shaft section is coaxially inserted into one end of the stepped shaft section and is threadedly detached from the stepped shaft section. A high-pressure gas inlet is machined in the end connecting shaft section along its axial extension direction. A high-pressure gas inlet hole is machined in the end of the stepped shaft section connected to the end connecting shaft section along its axial extension direction, and one end of the high-pressure gas inlet hole is connected to the high-pressure gas inlet. Multiple radial pressure distribution holes are machined equidistantly along the circumferential direction on the inner wall of the other end of the high-pressure gas inlet hole. One end of the radial pressure distribution hole is connected to the high-pressure gas inlet hole, and the other end of the radial pressure distribution hole is connected to the sealed cavity constructed between the test spindle and the test housing unit.

[0010] Furthermore, the radial force loading module includes two radial force loading components, which are respectively arranged on both sides of the test housing unit, and both radial force loading components are mounted on the test spindle. The radial force loading component includes a radial loading hanger, which is mounted on the test spindle and rotatably connected to the test spindle through a bearing. A suspended weight is hung on the radial loading hanger.

[0011] Furthermore, the dynamic bending moment simulation module includes a bending moment loading rod mounting bracket and a bending moment loading rod. The bending moment loading rod mounting bracket is sleeved on the test spindle and rotatably connected to the test spindle through a bearing. The bending moment loading rod is mounted on the bending moment loading rod and connected to an external vibrator through the bending moment loading rod.

[0012] Furthermore, the test housing unit includes an insulation shell, a simulated housing base, and a cooling module. The insulation shell is fitted over the outside of the test spindle, and the bottom of the insulation shell is detachably connected to the base via a bracket. The simulated housing base is installed inside the insulation shell and fitted over the outside of the test spindle. The bushing specimen to be tested is placed between the simulated housing base and the test spindle. The cooling module is installed in the insulation shell and fitted over the outside of the test spindle. The cooling module is connected to an external cooling device via a pipe and transfers the cooling energy to the test spindle to simulate the low-temperature operating conditions of the test spindle. The insulation shell is machined with a heat input hole, which is connected to an external heat device via a pipe and transfers the heat to the test spindle to simulate the high-temperature operating conditions of the test spindle.

[0013] Furthermore, the cooling module includes a positioning sleeve, which is fitted over the outside of the test spindle and installed on the insulation shell. A cold energy input connector is detachably connected to the positioning sleeve, and the cold energy input connector is connected to an external cold energy device through a pipe.

[0014] Furthermore, an end cap is provided on the end of the insulation shell away from the power drive motor. The end cap is detachably connected to the insulation shell by bolts, and a sealing ring is installed between the end cap and the test spindle.

[0015] The beneficial effects of this application compared to the prior art are:

[0016] 1. This application provides a multi-physics coupled wear testing device for adjustable stator bushings of aero-engines. Through the physical isolation design of the three-dimensional load loading system, it achieves complete decoupling of radial force, axial pressure differential load, and dynamic bending moment. During the test, the proportion of each load component can be dynamically adjusted according to actual working conditions. Combined with the reciprocating motion of the main shaft and the combined effect of the temperature control field, it achieves accurate reproduction of the bushing wear characteristics.

[0017] 2. This application provides a multi-physics coupled wear testing device for adjustable stator bushings of aero-engines. By combining decoupled mechanical loading, aerodynamic differential pressure actuation, and a reconfigurable simulated casing structure, it resolves the contradiction between independent adjustment and complex stress simulation. The device boasts advantages such as compact structure, high load loading accuracy, and wide operating condition coverage. By employing aerodynamic loading instead of the traditional mechanical pushing method, it effectively eliminates parasitic friction errors introduced by the loading mechanism, significantly improving the accuracy of bushing friction torque monitoring and wear assessment. This provides an efficient and reliable technical solution for the reliability assessment of the VSV mechanism of next-generation aero-engines. Attached Figure Description

[0018] Figure 1 This is an axial side view of a multi-physics field coupled wear test device for adjustable stator bushings of aero-engines as described in this application;

[0019] Figure 2 This is a schematic diagram of the main cross section of a multi-physics field coupled wear test device for adjustable stator bushings of aero-engines as described in this application;

[0020] Figure 3 This is a schematic diagram of the composition of the test casing unit in the multi-physics field coupled wear test device for adjustable stator bushings of aero-engines described in this application;

[0021] Figure 4 This is an internal schematic diagram of a multi-physics field coupled wear test device for adjustable stator bushings of aero-engines as described in this application;

[0022] In the diagram: 101 - base, 102 - power drive motor, 103 - coupling, 104 - bracket; 201 - test spindle, 202 - radial loading hanger, 203 - suspended weight, 204 - high-pressure gas inlet, 205 - radial air pressure distribution hole, 206 - bending moment loading rod; 301 - insulation shell, 302 - heat input hole, 303 - cold input connector, 304 - simulated casing base, 305 - test bushing specimen, 306 - sealing ring, 307 - end cap. Detailed Implementation

[0023] Specific implementation method one: Combining Figures 1 to 4 This embodiment describes a multi-physics field coupled wear test device for adjustable stator bushings of aero-engines. The wear test device includes a support unit, a test spindle unit, and a test housing unit. The test spindle unit and the test housing unit are both mounted on the support unit. The bushing specimen 305 to be tested is placed between the test spindle unit and the test housing unit. The working state of the bushing specimen 305 to be tested is simulated by the relative motion between the test spindle unit and the test housing unit. The test spindle unit integrates a loading component for simulating the working conditions of the bushing specimen 305 to be tested, and the test housing unit integrates an environmental simulation component for simulating the working environment of the bushing specimen 305 to be tested.

[0024] The support unit includes a base 101 and two brackets 104. The two brackets 104 are arranged opposite each other on the top of the base 101 along the center line of the length direction of the base 101, and each bracket 104 is detachably connected to the base 101. The test spindle unit is supported and fixed by the two brackets 104, and the test housing unit is supported and fixed by the base 101.

[0025] The test spindle unit includes a power drive motor 102 and a test spindle 201. The power drive motor 102 is mounted on the top of a bracket 104 and is detachably connected to the bracket 104. One end of the test spindle 201 is connected to the power output shaft of the power drive motor 102 via a coupling 103. A bearing support is mounted on the other end of the test spindle 201, and the test spindle 201 and the bearing support are rotatably connected via a bearing. The bearing support is mounted on the top of another bracket 104 and is detachably connected to the bracket 104. The loading component is integrated on the test spindle 201.

[0026] The test housing unit includes an insulation shell 301, a simulation housing base 304, and a cooling module. The insulation shell 301 is fitted over the outside of the test spindle 201, and the bottom of the insulation shell 301 is detachably connected to the base 101 via a bracket. The simulation housing base 304 is installed inside the insulation shell 301 and fitted over the outside of the test spindle 201. The test bushing specimen 305 is placed between the simulation housing base 304 and the test spindle 201. The cooling module is installed in the insulation shell 301 and fitted over the outside of the test spindle 201. The cooling module is connected to an external cooling device through a pipe and transfers the cooling energy to the test spindle 201 to simulate the low temperature condition of the test spindle 201. The insulation shell 301 is machined with a heat input hole 302, which is connected to an external heat device through a pipe and transfers the heat to the test spindle 201 to simulate the high temperature condition of the test spindle 201.

[0027] The simulated housing base 304 has a bore diameter reconstruction function, and an adapter ring can be coaxially installed on the inner wall of its mounting hole. By replacing the adapter ring with different wall thicknesses, the device can flexibly adjust the effective mounting inner diameter of the simulated housing, thereby realizing compatibility testing of bushing test pieces 305 with various diameter specifications and mounting positions;

[0028] An end cap 307 is provided on the end of the insulation shell 301 away from the power drive motor 102. The end cap 307 is detachably connected to the insulation shell 301 by bolts. A sealing ring 306 is installed between the end cap 307 and the test spindle 201.

[0029] The loading component is a three-dimensional decoupled loading system, which includes a radial force loading module, a pneumatic axial loading module, and a dynamic bending moment simulation module. The radial force loading module and the dynamic bending moment simulation module are both mounted on the test spindle 201. The pneumatic axial loading module is located on the outside of the test spindle 201. A high-pressure gas inlet 204 is machined on the end of the test spindle 201 away from the power drive motor 102. The gas output end of the pneumatic axial loading module is connected to the high-pressure gas inlet 204.

[0030] In this embodiment, the support unit is mainly used to support the test spindle unit, which is used to simulate the rotor working conditions in an aero-engine. The test spindle 201 in the test spindle unit serves as the main load application component of the loading assembly. Through the physical isolation design of the radial force loading module, the aerodynamic axial loading module, and the dynamic bending moment simulation module, the independent loading and precise decoupling of radial force, axial aerodynamic pressure differential load, and dynamic bending moment are achieved from the structural root, completely solving the defects of traditional devices such as load coupling interference and inability to be individually controlled. During the test, the load ratio of each direction can be dynamically matched according to the actual working conditions of the engine, accurately replicating the composite stress state of the bushing during operation, so that the mechanical simulation is highly consistent with the actual service conditions. The test casing unit integrates a dual system of high-temperature heating and low-temperature cooling. The heat source is connected to the heat input hole of the insulation shell to simulate extreme high temperature, and the cold source is connected to the cold energy connector of the cooling module to simulate extreme low temperature, thus constructing a wide temperature range and high-precision temperature field. At the same time, combined with the coupled loading of the three-dimensional mechanical load in the spindle, the coupled simulation of the temperature field and the mechanical field is realized, which fully covers the full-cycle service environment of the bushing from extreme cold to high temperature, making up for the shortcomings of traditional equipment that cannot integrate multi-field simulation.

[0031] In this embodiment, a heat circulation pipeline is added inside the insulation shell 301. The heat input hole 302 is connected to the heat circulation pipeline, which is wound around the outside of the simulation casing base 304 to ensure heat conduction. Simultaneously, the insulation shell 301 is machined with a heat loss outlet hole adapted to the heat input hole 302. This outlet hole is also connected to the heat circulation pipeline and, through a pipeline, to a heat recovery unit. The heat recovery unit is used to recover the flowing medium that loses heat after flowing through the heat circulation pipeline. Commonly used external heating devices are hot water tanks and pumps, using high-temperature hot water as the heat transfer medium, which is introduced into the insulation shell 301 through the pump and associated pipelines. When the high-temperature hot water flows through the heat circulation pipeline, it transfers heat to the insulation shell 301, raising the working environment temperature of the bushing. The cooled hot water then enters the heat recovery unit through the heat loss outlet hole and associated pipelines.

[0032] Another heating method is electric heating, which can raise the working environment temperature of the bushing. This method requires integrating electric heating wires within the insulation housing 301. The heating wires can be woven into a mesh and arranged around the outside of the simulator housing 304. In this case, the heat input hole 302 serves as the connector outlet for the heating wires. The socket of the heating wires within the insulation housing 301, in conjunction with the connector, extends to the outside of the insulation housing through the heat input hole 302. The external heating device is a power supply structure that supplies power to the heating wires to raise their temperature, thereby increasing the working environment temperature of the bushing.

[0033] Specific Implementation Method Two: Combining Figures 1 to 4This embodiment further defines the specific embodiment one. The test spindle 201 is a combined spindle structure. The test spindle 201 includes a stepped shaft section and an end connecting shaft section. The end connecting shaft section is coaxially inserted into one end of the stepped shaft section and is threadedly detached from the stepped shaft section. A high-pressure gas inlet 204 is machined in the end connecting shaft section along its axial extension direction. A high-pressure gas inlet hole is machined in the end of the stepped shaft section connected to the end connecting shaft section along its axial extension direction. One end of the high-pressure gas inlet hole is connected to the high-pressure gas inlet 204. Multiple radial pressure distribution holes 205 are machined equidistantly in the circumferential direction on the inner wall of the other end of the high-pressure gas inlet hole. One end of the radial pressure distribution hole 205 is connected to the high-pressure gas inlet hole. The other end of the radial pressure distribution hole 205 is connected to the sealed cavity constructed between the test spindle 201 and the test housing unit.

[0034] The radial force loading module includes two radial force loading components, which are respectively arranged on both sides of the test housing unit. Both radial force loading components are mounted on the test spindle 201. The radial force loading component includes a radial loading hanger 202, which is mounted on the test spindle 201 and rotatably connected to the test spindle 201 through a bearing. A suspended weight 203 is hung on the radial loading hanger 202.

[0035] The dynamic bending moment simulation module includes a bending moment loading rod mounting bracket and a bending moment loading rod 206. The bending moment loading rod mounting bracket is sleeved on the test spindle 201 and rotatably connected to the test spindle 201 via bearings. The bending moment loading rod 206 is mounted on the mounting bracket and connected to an external vibrator via the bending moment loading rod 206. Other components and connection methods are the same as in Specific Implementation Method 1.

[0036] The structural optimization of the test spindle 201 in this embodiment is a key inventive point of this application. By setting a high-pressure gas inlet 204 and a high-pressure gas inlet hole on the test spindle 201, pneumatic axial loading is achieved. This application uses pneumatic axial loading to replace traditional mechanical pushing loading. High-pressure gas is uniformly introduced into the sealed cavity through the gas passage inside the test spindle 201 to form an axial load, completely eliminating parasitic friction errors caused by mechanical loading and significantly improving the accuracy of bushing friction torque monitoring and wear assessment. At the same time, the test spindle 201 adopts a combined stepped shaft section and a threaded connection to the end connecting shaft section. With the detachable simulation housing 304, the heat insulation shell 301 and the bracket, the installation inner diameter can be quickly reconstructed to adapt to multiple specifications and models of adjustable stationary blade bushing specimens. No special equipment needs to be customized, which significantly reduces the research and development and testing costs. The device has a compact layout and modular assembly, which facilitates parts replacement, working condition switching and maintenance, and its flexibility of use far exceeds that of traditional special testing equipment.

[0037] The radial force loading module adopts the traditional heavy object loading mode. In this embodiment, the radial force loading module includes two radial force loading components, which are respectively set on both sides of the test housing unit to ensure the stability of the test spindle 201 under radial load. The operator can replace the heavy objects of different weights to simulate the load under different working conditions. The loading method is simple.

[0038] The dynamic bending moment module is set between a radial force loading component and the test casing unit. It relies on an external vibrator to restore the engine vibration condition, so that the test wear morphology and damage characteristics are completely matched with the actual damage, and the test data are more valuable for engineering reference.

[0039] Specific implementation method three: Combining Figures 1 to 4 This embodiment further defines the first embodiment. The cooling module includes a positioning sleeve, which is fitted over the outside of the test spindle 201 and mounted on the insulation shell 301. A cooling input connector 303 is detachably connected to the positioning sleeve, and the cooling input connector 303 is connected to an external cooling device through a pipe. Other components and connection methods are the same as in the second embodiment.

[0040] In this embodiment, a cold air circulation pipeline is machined inside the positioning sleeve, and this pipeline is wound around the outside of the simulator housing 304. The cold air input connector 303 is connected to an external refrigerator, which introduces low-temperature cold air into the cold air circulation pipeline inside the positioning sleeve through the pipeline and the cold air input connector 303. The positioning sleeve is also machined with a cold air loss outlet. The cold air that has lost temperature is discharged from the positioning sleeve through the cold air loss outlet and the matching pipeline, and flows into the cold air recovery tank for centralized treatment.

[0041] The working principle of this application is explained in conjunction with specific implementation methods one through three:

[0042] The wear testing apparatus in this application uses a base 101 as the overall support foundation. Two brackets 104 are symmetrically fixed and support the test spindle 201. The test housing unit is connected to the base through the brackets to form a stable test frame. The power drive motor 102 serves as the power source, driving the test spindle 201 to rotate via a coupling 103. This causes the test bushing 305, which is mounted on the spindle, to generate relative frictional motion with the test spindle 201 and the simulated housing base 304, replicating the actual relative motion state between the blade journal and the bushing in an engine, thus providing the basic motion conditions for the wear test.

[0043] The wear testing device in this application adopts a three-dimensional physically isolated loading design of radial force, axial aerodynamic pressure difference, and dynamic bending moment. Each load is applied independently and precisely decoupled to completely restore the composite stress state of the bushing.

[0044] Radial force loading is achieved by connecting the radial loading hangers 202 on both sides of the test housing unit to the test spindle 201 via bearings. Weights 203 are suspended on the hangers, and the radial load is applied precisely by gravity. The symmetrical arrangement on both sides ensures that the radial force on the spindle is balanced. By changing the weights of different weights, the radial load can be flexibly adjusted. Furthermore, the bearing connection method does not interfere with the spindle movement or generate additional friction interference.

[0045] Pneumatic axial loading involves high-pressure gas entering the test spindle 201 through the high-pressure gas inlet 204, and then being evenly injected into the sealed cavity formed by the spindle and the casing through the high-pressure gas inlet hole and the circumferentially distributed radial air pressure distribution holes 205. The gas pressure difference is used to form a stable axial load, replacing the traditional mechanical pushing load, eliminating parasitic friction errors caused by the mechanical structure from the root, and ensuring accurate and interference-free axial load loading.

[0046] The specific simulation process for aerodynamic axial loading includes the following steps:

[0047] Step 1: Pressure chamber construction: Inside the insulation shell 301, a sealed pressure chamber is constructed between the sealing ring 306, the end cap 307 and the stepped surface of the test spindle 201;

[0048] Step 2: High-pressure gas input: Connect an external high-pressure gas source to the high-pressure gas input port 204 at the end of the test spindle 201, and the gas enters the center of the spindle along the axial air intake channel;

[0049] Step 3: Differential pressure load generation: High-pressure gas enters the pressure chamber through the radial pressure distribution hole 205. Since the gas pressure in the pressure chamber is higher than the ambient pressure, the high-pressure gas acts on the axial pressure surface of the test spindle 201 to generate axial thrust, thereby simulating the axial load F borne by the bushing. A

[0050] Step 4: Dynamic load adjustment: By adjusting the air supply pressure at the air inlet 204, the magnitude of the axial load can be changed in real time to match different test conditions.

[0051] In step 3 above, the axial load F A The following conditions must be met:

[0052]

[0053] In the above formula, P is the air pressure value in the pressure chamber, D is the outer diameter of the pressure surface of the test spindle 201 in the sealed chamber, and d is the effective diameter of the sealing contact. By precisely controlling the air intake pressure, the axial force can be simulated.

[0054] Dynamic bending moment simulation is achieved by connecting an external vibrator to the bending moment loading rod 206. The dynamic alternating load output by the vibrator is transmitted to the main shaft through the loading rod to simulate the dynamic bending moment generated by load offset during engine operation. The three loads are independent of each other, and the magnitude and frequency of each load can be adjusted individually according to the actual working conditions to achieve precise matching of complex stress conditions.

[0055] The wear testing device in this application integrates a high-temperature, low-temperature, and sealed pneumatic environment simulation system through a test casing unit to construct a wide-temperature-range, highly realistic service environment.

[0056] The high-temperature environment simulation involves an external heating device transferring heat to the interior of the insulation shell 301 through the heat input hole 302. The heat is then evenly conducted through the circulation pipes surrounding the simulated engine housing 304. Combined with the insulation effect of the insulation shell 301, this simulates the high-temperature operating conditions of the engine. It can use either hot water circulation heating or electric heating to meet different high-temperature test requirements.

[0057] Low temperature environment simulation involves an external cooling device supplying a cold source to the cooling module through a cold input connector 303. The cold energy is then uniformly cooled by circulating through the positioning sleeve around the simulated casing 304, simulating an extremely low temperature service environment and achieving full temperature range coverage from extreme cold to high temperature.

[0058] The sealed pneumatic environment is formed by the end cover 307 and the sealing ring 306, which seal the cavity between the main shaft and the casing. With the high-pressure gas loaded by pneumatic axial loading, it simulates the pneumatic pressure environment inside the engine and realizes the coupling of multiple physical fields such as temperature field, aerodynamic field and mechanical field.

[0059] The decoupling logic of the wear testing device in this application includes:

[0060] Pneumatic axial loading: The test spindle 201 is optimized to be a hollow structure. An external high-pressure air source allows high-pressure gas to enter the pressure chamber through the radial pressure distribution hole 205. Because the air pressure inside the pressure chamber is higher than the ambient pressure, the high-pressure gas acts on the axial pressure surface of the test spindle 201, generating an axial thrust, thereby simulating the axial load F borne by the bushing. A；

[0061] Static radial loading: Radial loading hangers 202 are set up symmetrically on both sides of the test spindle 201 using brackets 104. By increasing or decreasing the mass of the suspended weight 203, a constant radial load F is generated by gravity. R ;

[0062] Dynamic bending moment application: The external vibrator is hinged to the bending moment loading rod 206 at the end of the test spindle 201. The high-frequency reciprocating force generated by the vibrator simulates the bending moment M generated by the blade shaft due to aerodynamic offset. B ;

[0063] Temperature field construction: Activate the heating or cooling unit inside the insulation shell 301 to form a stable closed temperature control space in conjunction with the external insulation structure;

[0064] Motion coupling: Start the power drive motor 102 to drive the test spindle 201 to perform reciprocating rotational motion, so as to realize continuous wear test under specific temperature and triaxial load coupling conditions.

[0065] The simulated housing 304 in this application can be compatible with bushing test pieces of various specifications by replacing different internal compensation units. The specific operation steps are as follows:

[0066] Step A: Specification matching: Select a matching ring with the corresponding wall thickness according to the outer diameter of the bushing specimen 305 to be tested;

[0067] Step B: In-situ installation: The adapter ring is coaxially embedded into the reserved large-diameter mounting hole of the simulation housing 304, and axially limited and fixed.

[0068] Step C: Specimen Installation: Press or slide the bushing specimen 305 to be tested into the inner hole of the adapter ring, ensuring that the center line of the bushing and the center line of the test spindle 201 meet the preset coaxiality or eccentricity requirements.

[0069] The present invention has been disclosed above with preferred embodiments, but it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed structure and technical content to create equivalent embodiments without departing from the scope of the present invention. However, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A multi-physics field coupled wear test device for adjustable stator bushings of aero-engines, characterized in that: The wear testing device includes a support unit, a test spindle unit, and a test housing unit. The test spindle unit and the test housing unit are both mounted on the support unit. The bushing test piece (305) to be tested is placed between the test spindle unit and the test housing unit. The working state of the bushing test piece (305) to be tested is simulated by the relative motion between the test spindle unit and the test housing unit. The test spindle unit is equipped with a loading component for simulating the working condition of the bushing test piece (305), and the test housing unit is equipped with an environmental simulation component for simulating the working environment of the bushing test piece (305).

2. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 1, characterized in that: The support unit includes a base (101) and two brackets (104). The two brackets (104) are arranged opposite each other on the top of the base (101) along the center line of the length direction of the base (101), and each bracket (104) is detachably connected to the base (101). The test spindle unit is supported and fixed by the two brackets (104), and the test housing unit is supported and fixed by the base (101).

3. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 2, characterized in that: The test spindle unit includes a power drive motor (102) and a test spindle (201). The power drive motor (102) is mounted on the top of a bracket (104) and is detachably connected to the bracket (104). One end of the test spindle (201) is connected to the power output shaft of the power drive motor (102) via a coupling (103). A bearing support is mounted on the other end of the test spindle (201), and the test spindle (201) and the bearing support are rotatably connected via a bearing. The bearing support is mounted on the top of another bracket (104) and is detachably connected to the bracket (104). The loading component is integrated on the test spindle (201).

4. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 3, characterized in that: The loading component is a three-dimensional decoupled loading system, which includes a radial force loading module, a pneumatic axial loading module and a dynamic bending moment simulation module. The radial force loading module and the dynamic bending moment simulation module are both mounted on the test spindle (201). The pneumatic axial loading module is set on the outside of the test spindle (201). A high-pressure gas inlet (204) is machined on the end of the test spindle (201) away from the power drive motor (102). The gas output end of the pneumatic axial loading module is connected to the high-pressure gas inlet (204).

5. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 4, characterized in that: The test spindle (201) is a combined shaft structure. The test spindle (201) includes a stepped shaft section and an end connecting shaft section. The end connecting shaft section is coaxially inserted into one end of the stepped shaft section and is threadedly connected to the stepped shaft section. A high-pressure gas inlet (204) is machined in the end connecting shaft section along its axial extension direction. A high-pressure gas inlet hole is machined in the end of the stepped shaft section connected to the end connecting shaft section along its axial extension direction. One end of the high-pressure gas inlet hole is connected to the high-pressure gas inlet (204). Multiple radial pressure distribution holes (205) are machined equidistantly along the circumference on the inner wall of the other end of the high-pressure gas inlet hole. One end of the radial pressure distribution hole (205) is connected to the high-pressure gas inlet hole. The other end of the radial pressure distribution hole (205) is connected to the sealed cavity constructed between the test spindle (201) and the test housing unit.

6. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 5, characterized in that: The radial force loading module includes two radial force loading components, which are respectively set on both sides of the test housing unit and both radial force loading components are mounted on the test spindle (201). The radial force loading component includes a radial loading hanger (202), which is mounted on the test spindle (201) and rotatably connected to the test spindle (201) through a bearing. A suspended weight (203) is hung on the radial loading hanger (202).

7. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 6, characterized in that: The dynamic bending moment simulation module includes a bending moment loading rod mounting bracket and a bending moment loading rod (206). The bending moment loading rod mounting bracket is sleeved on the test spindle (201) and rotatably connected to the test spindle (201) through a bearing. The bending moment loading rod mounting bracket is equipped with a bending moment loading rod (206) and is connected to an external vibrator through the bending moment loading rod (206).

8. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 7, characterized in that: The test housing unit includes an insulation shell (301), a simulation housing base (304), and a cooling module. The insulation shell (301) is fitted onto the outside of the test spindle (201), and the bottom of the insulation shell (301) is detachably connected to the base (101) via a bracket. The simulation housing base (304) is installed inside the insulation shell (301) and fitted onto the outside of the test spindle (201). The bushing specimen (305) to be tested is placed between the simulation housing base (304) and the test spindle (201). The cooling module is installed in the insulation shell (301) and sleeved on the outside of the test spindle (201). The cooling module is connected to the external cooling device through a pipe and transfers the cooling energy to the test spindle (201) to simulate the low temperature condition of the test spindle (201). The insulation shell (301) is machined with a heat input hole (302). The heat input hole (302) is connected to the external heat device through a pipe and transfers the heat to the test spindle (201) to simulate the high temperature condition of the test spindle (201).

9. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 8, characterized in that: The cooling module includes a positioning sleeve, which is fitted outside the test spindle (201) and installed on the insulation shell (301). A cold energy input connector (303) is detachably connected to the positioning sleeve, and the cold energy input connector (303) is connected to an external cold energy device through a pipe.

10. The multi-physics field coupled wear test device for adjustable stator bushings of aero-engines according to claim 9, characterized in that: An end cap (307) is provided on the end of the insulation shell (301) away from the power drive motor (102). The end cap (307) is detachably connected to the insulation shell (301) by bolts. A sealing ring (306) is installed between the end cap (307) and the test spindle (201).

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