Aero-engine shaft parts composite static and fatigue tester

Abstract

The application provides an aero-engine shaft part composite static and fatigue tester, which comprises a bearing frame, a torque loading device, a shaft clamp device, a loading actuator, a torque limiting device, an axial force and bending moment loading device and a test shaft, the shaft clamp device comprises a lower connecting shaft, a deep groove ball bearing and a lower bearing section, is used for connecting and fixing the test shaft and connecting the torque loading device and the axial force and bending moment loading device, and transmits the loading load to the bearing frame; the torque limiting device and the axial force and bending moment loading device are used for loading the required axial force and rotating bending moment of the test on the test shaft, and decouple the loading of the axial force and the rotating bending moment, the shaft clamp device is connected with the torque loading device, the shaft clamp device is provided with the lower connecting shaft, the deep groove ball bearing and the lower bearing section, and the axial force and the rotating bending moment are loaded by using the same set of loading devices; and the tester is suitable for the test of aero-engine shaft parts with different load requirements.

Description

Technical Field

[0001] This invention relates to the field of composite static and fatigue testing of aero-engine shaft components, and in particular to a composite static and fatigue testing apparatus for aero-engine shaft components. Background Technology

[0002] When an aero-engine is operating, shaft components are subjected to working loads including torque, axial force, vibration torque, and bending moment. These complex loads have a significant impact on the fatigue life of shaft components. Taking an aero-engine fan shaft as an example, through analysis of the boundary constraints and load conditions of the fan shaft, it is found that four types of loads—torque, axial force, vibration torque, and bending moment—act on the fan rotor and are then transmitted to the fan shaft.

[0003] Currently, there are two main methods for loading the rotational bending moment of fan shafts: rotating eccentric counterweight discs and hydraulic motors. The rotating eccentric counterweight disc method suffers from the problem that the tension of the motor pulley can exert an eccentric force on the load. Furthermore, the magnitude and frequency of the rotational bending moment are limited by the weight of the counterweight and the motor speed. At higher motor speeds, the unbalanced high-speed counterweight disc cannot guarantee loading accuracy and safety. The hydraulic motor method requires a specially designed hydraulic and electrical interface rotating device, resulting in high maintenance costs and a large workload. Additionally, the stability of the hydraulic components during high-speed rotation needs further verification.

[0004] Currently, the method of loading vibration torque on the fan shaft has the problem that the vibration torque and the main torque are implemented by using different actuators, and they both act on the same torque arm, which will cause coupling with the main torque, resulting in limited loading frequency and safety risks.

[0005] In summary, the existing testing equipment has the following shortcomings: (1) Different testing equipment is required for loading torque, axial force, vibration torque and bending moment, which is complicated and costly. (2) Due to design defects, additional forces were introduced into the rotational bending moment load loading, and the rotational bending moment and axial force were not completely decoupled, thus failing to ensure the accurate loading of each load. (3) The main torque and vibration torque are loaded by two sets of actuators, which makes the control system complex and increases the test cost; (4) Due to the differences in the test objects they are designed for, the load types, loading capacity and loading actuators of existing shaft testers are not entirely applicable to different types of shaft parts, and thus have certain limitations in their applicability. Summary of the Invention

[0006] The purpose of this invention is to provide a composite static and fatigue tester for aero-engine shaft parts, which reduces the complexity of the loading mechanism of the composite static and fatigue tester for aero-engine shaft parts, reduces the number of actuators for loading rotational bending moment and axial force, reduces the number of actuators for loading main torque and vibration torque, reduces the manufacturing cost and energy consumption of this type of tester, and saves test costs.

[0007] To achieve the above objectives, the technical solution adopted by the present invention is: a composite static and fatigue testing apparatus for aero-engine shaft parts, comprising a load-bearing frame, a torque loading device, a shaft clamping device, a loading actuator, a torque limiting device, an axial force and bending moment loading device, and a test shaft. The load-bearing frame is provided with a torque loading device, and the torque loading device is provided with two loading actuators that apply torque in the horizontal direction. The torque loading device is connected to the shaft clamping device in the vertical direction. The shaft clamping device includes a lower connecting shaft, a deep groove ball bearing, and a lower bearing section. The upper end of the lower connecting shaft is connected to the test shaft, and the lower end of the lower connecting shaft is connected to the torque loading device. A deep groove ball bearing is provided on the outer surface of the middle part of the lower connecting shaft. The deep groove ball bearing is installed on the lower bearing section, and the lower bearing section is connected to the load-bearing frame. The torque limiting device is used for torque transmission of the torque loading device, transmitting the force of the torque loading device to the bearing frame. It includes a torque limiting disc, a torque limiting rod connected to the torque limiting disc, and a mounting base connected to the torque limiting rod. The mounting base is connected to the bearing frame. The axial force and bending moment loading device is connected to the torsion limiting disc of the torsion limiting device, and is used to load the axial force and rotational bending moment required for the test onto the test shaft, and to decouple the loading of axial force and rotational bending moment.

[0008] Preferably, the load-bearing frame includes vertical columns, horizontal connecting beams connecting the vertical columns, horizontal top beams connecting the horizontal connecting beams, and horizontal load-bearing beams disposed within the load-bearing frame.

[0009] Preferably, the outer ring surface of the torque loading device has two radially protruding and symmetrical torque arms, which are connected to the loading actuator cylinder.

[0010] Preferably, the shaft clamping device further includes a cylindrical roller bearing, an upper bearing section, and an upper connecting shaft. The cylindrical roller bearing is disposed between the outer surface of the upper end of the test shaft and the upper connecting shaft. The upper end of the upper bearing section is connected to the upper surface of the axial force and bending moment loading device. The lower end of the upper bearing section is connected to the test shaft. The upper end of the upper connecting shaft is connected to the load-bearing frame.

[0011] Preferably, the loading actuator includes two cylinders, each of which is provided with a front connecting flange and a rear connecting flange; the front connecting flange of one of the loading actuators is connected to two radially protruding and symmetrical torque arms of the torque loading device, and the rear connecting flange is connected to the horizontal connecting beam of the bearing frame. The other loading actuator's front connecting flange is connected to the axial force and bending moment loading device, and its rear connecting flange is connected to the horizontal load-bearing beam of the load-bearing frame.

[0012] Preferably, each loading actuator cylinder is also provided with a load sensor. One end of the loading actuator cylinder is connected to one end of the load sensor through a flange, and the other end of the load sensor is connected to the torque arm of the torque loading device or the axial force and bending moment loading device through a ball joint.

[0013] Preferably, the torsion limiting device further includes connecting ears; the torsion limiting disk is evenly provided with a plurality of connecting ears along the circumference; both ends of the torsion limiting rod are provided with single ears whose length can be adjusted along the axial direction of the torsion limiting rod; the single ear at one end of the torsion limiting rod is connected to the connecting ears evenly provided along the circumference of the torsion limiting disk; the single ear at the other end of the torsion limiting rod is connected to the mounting base; and the mounting base is connected to the vertical column of the bearing frame.

[0014] Preferably, the axial force and bending moment loading device includes an adapter lug, a connecting pin, a double cross trunnion, a loading disk, an upper cross annular bushing, and a lower cross annular bushing; the connecting pin connects the adapter lug, the double cross trunnion, the loading disk, the upper cross annular bushing, and the lower cross annular bushing to form a universal joint structure.

[0015] Preferably, the top of the universal joint is a loading plate, which is connected to the upper bearing section of the shaft clamping device. The lower cross-shaped annular bushing at the bottom of the universal joint is fixedly connected to the top of the torque limiting plate of the torque limiting device through two adapter lugs, thus connecting the shaft clamping device, the torque limiting device, and the axial force and bending moment loading device together.

[0016] Preferably, the test shaft is installed inside the shaft clamping device.

[0017] Compared with the prior art, the beneficial effects of this invention are: by connecting the shaft clamping device to the torque loading device, and setting the lower connecting shaft, deep groove ball bearing, and lower bearing section in the shaft clamping device, the axial force and rotational bending moment can be loaded using the same loading device; it is suitable for testing aero-engine shaft parts with different load requirements.

[0018] The overall structural design eliminates the problem of complex control systems caused by using two sets of actuators for torque and vibration torque loading, eliminates the additional force introduced in the rotational bending moment load loading, and uses fewer loading actuators to connect with the torque loading device, so as to realize the loading of torque, axial force, vibration torque and bending moment of aero-engine shaft parts, and reduce the construction cost of the test equipment. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the composite static and fatigue testing device for aero-engine shaft parts of the present invention; Figure 2 This is a cross-sectional view of the composite static and fatigue testing device for aero-engine shaft parts of the present invention. Figure 3 This is a schematic diagram of the load-bearing frame structure of the composite static and fatigue testing device for aero-engine shaft parts of the present invention; Figure 4 This is a schematic diagram of the torque loading device structure of the composite static and fatigue testing apparatus for aero-engine shaft parts of the present invention; Figure 5 This is a schematic diagram of the shaft clamping device of the composite static and fatigue testing apparatus for aero-engine shaft parts of the present invention; Figure 6 This is a schematic diagram of the loading actuator structure of the composite static and fatigue testing device for aero-engine shaft parts of the present invention; Figure 7 This is a schematic diagram of the torsion limiting device structure of the composite static and fatigue testing apparatus for aero-engine shaft parts of the present invention; Figure 8 This is a schematic diagram of the axial force and bending moment loading device of the composite static and fatigue tester for aero-engine shaft parts of the present invention. Reference numerals: 100-Bearing frame, 101-Horizontal bearing beam, 102-Vertical column, 103-Horizontal connecting beam, 104-Horizontal top beam, 200-Torque loading device, 201-Torque support arm, 300-Shaft clamping device, 301-Lower connecting shaft, 302-Deep groove ball bearing, 303-Lower bearing section, 304-Cylindrical roller bearing, 305-Upper bearing section, 306-Upper connecting shaft, 400-Loading device Moving cylinder, 401-front connecting flange, 402-rear connecting flange, 500-torsion limiting device, 501-torsion limiting disc, 502-connecting double lugs, 503-torsion limiting tie rod, 504-mounting seat, 600-axial force and bending moment loading device, 601-adapter lug, 602-connecting pin, 603-cross double lug, 604-loading disc, 605-upper cross ring bushing, 606-lower cross ring bushing, 700-test shaft. Detailed Implementation

[0020] like Figures 1 to 8As shown, a composite static and fatigue testing apparatus for aero-engine shaft components includes a load-bearing frame 100, a torque loading device 200, a shaft clamping device 300, a loading actuator 400, a torsion limiting device 500, an axial force and bending moment loading device 600, and a test shaft 700. The load-bearing frame 100 is equipped with the torque loading device 200, which has two torque-applying actuators 400 arranged horizontally on its components. The torque loading device 200 also has two torque-applying actuators 400 arranged vertically on its components. A shaft clamping device 300 is connected in a straight direction. The shaft clamping device 300 includes a lower connecting shaft 301, a deep groove ball bearing 302, and a lower bearing section 303. The upper end of the lower connecting shaft 301 is connected to the test shaft 700, and the lower end of the lower connecting shaft 301 is connected to the torque loading device 200. The deep groove ball bearing 302 is provided on the outer surface of the middle part of the lower connecting shaft 301. The deep groove ball bearing 302 is installed on the lower bearing section 303, and the lower bearing section 303 is connected to the bearing frame 100. The torque limiting device 500 is used for torque transmission of the torque loading device 200, and transmits the force of the torque loading device 200 to the bearing frame 100. It includes a torque limiting disc 501, a torque limiting rod 503 connected to the torque limiting disc 501, and a mounting base 504 connected to the torque limiting rod. The mounting base 504 is connected to the bearing frame 100. The axial force and bending moment loading device 600 is connected to the torsion limiting disk 501 of the torsion limiting device 500, and is used to load the axial force and rotational bending moment required for the test onto the test shaft 700, and to decouple the loading of axial force and rotational bending moment.

[0021] The load-bearing frame 100 includes vertical columns 102, horizontal connecting beams 103 connecting the vertical columns 102, horizontal top beams 104 connecting the horizontal connecting beams 103, and horizontal load-bearing beams 101 disposed within the load-bearing frame 100.

[0022] The torque loading device 200 has two radially protruding and symmetrical torque arms 201 on its outer ring surface, and the torque arms 201 are connected to the loading actuator cylinder 400.

[0023] The shaft clamping device 300 further includes a cylindrical roller bearing 304, an upper bearing section 305, and an upper connecting shaft 306. The cylindrical roller bearing 304 is disposed between the upper outer surface of the test shaft 700 and the upper connecting shaft 306. The upper end of the upper bearing section 305 is connected to the upper surface of the axial force and bending moment loading device 600, the lower end of the upper bearing section 305 is connected to the test shaft 700, and the upper end of the upper connecting shaft 306 is connected to the bearing frame 100.

[0024] The loading actuator cylinder 400 includes two cylinders, each of which is provided with a front connecting flange 401 and a rear connecting flange 402; the front connecting flange 401 of one of the loading actuator cylinders 400 is connected to two radially protruding and symmetrical torque support arms 201 of the torque loading device 200, and the rear connecting flange 402 is connected to the horizontal connecting beam 103 of the bearing frame 100. The front connecting flange 401 of the other loading actuator is connected to the axial force and bending moment loading device 600, and the rear connecting flange 402 is connected to the horizontal bearing beam 101 of the bearing frame 100.

[0025] Each loading actuator cylinder 400 is also equipped with a load sensor. One end of the loading actuator cylinder 400 is connected to one end of the load sensor through a flange, and the other end of the load sensor is connected to the torque support arm 201 of the torque loading device 200 or the axial force and bending moment loading device 600 through a ball joint.

[0026] The torsion limiting device 500 further includes connecting ears 502. The torsion limiting disk 501 is evenly provided with a plurality of connecting ears 502 along the circumference. Both ends of the torsion limiting rod 503 are provided with single ears that can be adjusted in length along the axial direction of the torsion limiting rod 503. The single ear at one end of the torsion limiting rod 503 is connected to the connecting ears 502 evenly provided along the circumference of the torsion limiting disk 501. The single ear at the other end of the torsion limiting rod 503 is connected to the mounting base 504. The mounting base 504 is connected to the vertical column 102 of the bearing frame 100.

[0027] The axial force and bending moment loading device 600 includes an adapter 601, a connecting pin 602, a cross double trunnion 603, a loading disk 604, an upper cross annular bushing 605, and a lower cross annular bushing 606; the connecting pin 602 connects the adapter 601, the cross double trunnion 603, the loading disk 604, the upper cross annular bushing 605, and the lower cross annular bushing 606 to form a cross universal joint structure.

[0028] The top of the universal joint is a loading plate 604, which is connected to the upper bearing section 305 of the shaft clamping device 300. The lower cross-shaped annular bushing 606 at the bottom of the universal joint is fixedly connected to the top of the torque limiting plate 501 of the torque limiting device 500 through two adapter lugs 601, thus connecting the shaft clamping device 300, the torque limiting device 500, and the axial force and bending moment loading device 600 together.

[0029] The test shaft 700 is installed inside the shaft clamping device 300.

[0030] Specifically, the load-bearing frame 100 includes horizontal load-bearing beams 101, vertical columns 102, horizontal connecting beams 103, and a horizontal top beam 104. In this embodiment, the load-bearing frame 100 preferably includes two horizontal load-bearing beams 101, four vertical columns 102, eight horizontal connecting beams 103, and one horizontal top beam 104 forming an open installation space to facilitate the subsequent installation of various devices. The length of the vertical columns 102 can be selected according to the testing needs of different length test shafts 700. All beams and columns are connected by bolts.

[0031] The torque loading device 200 also has two radially protruding and symmetrical torque arms 201 on its outer ring surface; the torque loading device 200 is set at the bottom of the lower connecting shaft 301 of the shaft clamping device 300, and the torque loading device 200 and the lower connecting shaft 301 are connected by bolts; two loading actuators 400 for applying torque are provided on the two radially protruding and symmetrical torque arms 201 of the torque loading device 200, the axial direction of the loading actuators 400 is parallel to the horizontal direction, the front connecting flange 401 of the loading actuators 400 is connected to the torque arms 201 by bolts, and the rear connecting flange 402 of the loading actuators 400 is connected to the horizontal connecting beam 103 of the bearing frame 100; The shaft clamping device 300 is located in the installation space formed by the aforementioned bearing frame 100, and is fixedly installed on the horizontal bearing beam 101 and the horizontal top beam 104 of the bearing frame 100. The test shaft 700 is rotatably installed inside the shaft clamping device 300 in the vertical direction. In this embodiment, preferably, a deep groove ball bearing 302 and a cylindrical roller bearing 304 are coaxially arranged from top to bottom inside the shaft clamping device 300. The test shaft 700 is rotatably installed on the lower connecting shaft 301 and the upper connecting shaft 306 through the deep groove ball bearing 302 and the cylindrical roller bearing 304 to simulate the boundary constraints when the test shaft 700 is actually installed. That is, the installation structure of the shaft clamping device 300 and the test shaft 700 completely imitates the installation structure of the real test shaft 700, which can make the structure of the subsequent load loading test more accurate.

[0032] The loading actuator 400 is used to apply the load required for the test. There are two types: loading actuators for applying bending moment and axial force and loading actuators for applying torque. Each loading actuator 400 is provided with a front connecting flange 401 and a rear connecting flange 402. The front connecting flange 401 and the rear connecting flange 402 are hinged to the piston rod and the rear end cover of the loading actuator 400. The number of loading actuators 400 used to apply bending moment and axial force can be set as needed, and the connection method with the loading disk 604 can also be selected appropriately. In this embodiment, four loading points are evenly arranged on the outer circumference of the loading disk 604, with each loading point spaced 90° apart. Each loading point is connected to the front connecting flange 401 of a loading actuator 400. Through the combined action of the four loading actuators 400, a rotational torque field (usually with a rotational frequency of not less than 50Hz) is generated on the loading disk 604, thereby simulating the rotational bending moment load. In addition, each loading actuator 400 is also equipped with a load sensor. Specifically, one end of the piston rod of the loading actuator 400 is connected to one end of a load sensor through a flange, and the other end of the load sensor is spherically hinged to the front connecting flange 401 and the loading point of the loading disk 604.

[0033] There are two loading actuator cylinders 400 for applying torque, and the axis of each loading actuator cylinder 400 is parallel to the horizontal plane; the front connecting flange 401 of one loading actuator cylinder 400 is fixedly connected to the end of a torque support arm 201 on the torque loading device 200, and the rear connecting flange 402 is hinged to a horizontal connecting beam 103 of the bearing frame 100; the front connecting flange 401 of the other loading actuator cylinder 400 is fixedly connected to the end of a torque support arm 201 on the torque loading device 200, and the rear connecting flange 402 is hinged to another horizontal connecting beam 103 of the bearing frame 100; in addition, the two loading actuator cylinders 400 are symmetrically distributed with the center point of the torque loading device 200 as the origin, and preferably in the initial state (when not loaded), the axial direction of the loading actuator cylinder 400 is perpendicular to the axis of the torque support arm 201 of the torque loading device 200.

[0034] Similarly, each loading actuator 400 used to apply torque is equipped with a load sensor. Specifically, one end of the piston rod of the loading actuator 400 is connected to one end of a load sensor via a flange, and the other end of the load sensor is ball-jointed to the flange 401 connected to the torque support arm 201 of the torque loading device 200. The ball-joint connection ensures that deformation (torsion angle) under torsion does not affect the accuracy of the torque load; and it can eliminate the reaction force of the two loading actuators 400 on the axial force and the uncertain gravitational component caused by the deformation under the axial force.

[0035] In addition, all loading actuators 400 in this invention can be selected as ordinary two-chamber hydraulic actuators. The loading of main torque and vibration torque, rotational bending moment and axial force is achieved through the hydraulic actuator, thereby realizing the decoupling between main torque and vibration torque, and the decoupling between axial force and rotational bending moment.

[0036] The torque limiting device 500 is used in conjunction with the torque loading device 200 to load the main torque and vibration torque of the test shaft 700, and at the same time can release the constraint along the axial direction of the test shaft 700. An axial force and bending moment loading device 600 is used to load axial force and rotational bending moment onto the test shaft 700. Specifically, in this embodiment, the axial force and bending moment loading device 600 is preferably a two-layer universal joint arranged vertically. This is achieved by connecting pins 602 to connect the adapter 601, the double cross trunnion 603, the loading disc 604, the upper cross annular sleeve 605, and the lower cross annular sleeve 606, forming a two-layer universal joint structure. This two-layer universal joint structure allows for the downward transmission of torque but restricts the downward transmission of bending moment, thus achieving the desired bending moment loading. The decoupling between torque and load is achieved; the top of the universal joint is a loading plate 604, which is connected to the upper bearing section 305 of the shaft clamping device 300. The lower cross-shaped annular bushing 606 at the bottom of the universal joint is fixedly connected to the top of the torque limiting plate 501 of the torque limiting device 500 through two adapter lugs 601, connecting the shaft clamping device 300, the torque limiting device 500, and the axial force and bending moment loading device 600 together. The lower connecting shaft 301 at the bottom of the shaft clamping device 300 is fixedly connected to the torque loading device 200, and the test shaft 700 is installed inside the shaft clamping device 300.

[0037] The working principle and process of this invention are as follows: In this embodiment, the load loading process is controlled by a high-performance fully digital hydraulic servo coordinated loading controller, which controls the movement of all loading actuators 400. Specifically, the two loading actuators 400 used to apply torque move, pushing the torque loading device 200 to rotate circumferentially along the test shaft 700 according to the load spectrum requirements. First, the main torque is applied, and then a vibration torque is applied based on the main torque. The load is transmitted to the test shaft 700 through the lower connecting shaft 301 at the bottom of the shaft clamping device 300, and then transmitted to the upper bearing section 305 at the top of the shaft clamping device 300 through the test shaft 700, and then further transmitted... The torque is transferred to the loading plate 604 of the axial force and bending moment loading device 600, and then to the torque limiting plate 501 of the torque limiting device 500 through the two-layer universal joint structure of the axial force and bending moment loading device 600. Finally, the torque is transferred to the vertical column 102 of the bearing frame 100 through the torque limiting tie rod 503 and the mounting base 504. The rear connecting flange 402 of the loading actuator 400 used to apply torque is fixedly connected to the horizontal connecting beam 103 of the bearing frame 100. Since the bearing frame 100 is a closed structure, the loading of the main torque and vibration torque forms a closed transmission path inside the frame. Similarly, in this embodiment, the four loading actuators 400 for applying bending moment and axial force actuate, pushing the loading disk 604 of the axial force and bending moment loading device 600 to apply axial force along the axial direction of the test shaft 700 according to the load spectrum requirements. At this time, the axial force and bending moment loading device 600 will be displaced vertically as a whole due to the axial deformation of the test shaft 700. The torsion limiting device 500 is not constrained in the axial direction, so the torsion limiting device 500 will not affect the accuracy of axial force loading. The axial force is transmitted along the loading disk 604 to the upper bearing section 305 at the top of the shaft clamping device 300, and then... Loaded onto the test shaft 700, the cylindrical roller bearing 304 at the top of the shaft clamping device 300 is unrestrained in the axial direction, and the deep groove ball bearing 302 at the bottom of the shaft clamping device 300 transmits the axial force to the lower bearing section 303. The lower bearing section 303 transmits the applied axial force to the horizontal bearing beam 101 of the bearing frame 100. Since the rear connecting flanges 402 at the tail of the four loading actuators 400 used to apply bending moment and axial force are fixedly installed on the horizontal bearing beam 101 of the bearing frame 100, a closed axial force transmission path is formed inside the bearing frame 100. In this embodiment, after the four loading actuators 400 for applying bending moment and axial force apply axial force, according to the load spectrum requirements, the four loading actuators 400 apply rotational bending moment at a specified frequency with each adjacent loading actuator 400 having a 90° phase difference. At this time, due to the presence of the two-layer universal joint structure of the shaft clamping device 300, the applied rotational bending moment will not be transmitted to the torque limiting device 500. The cylindrical roller bearing 304 provided inside the shaft clamping device 300 can transmit radial force and load the rotational bending moment onto the test shaft 700. The lower bearing section 303 and the upper connecting shaft 306 of the shaft clamping device 300 are used to simulate the stiffness of the actual test shaft 700 during installation and transmit the rotational bending moment to the bearing frame 100, thus completing the loading of axial force and rotational bending moment.

Claims

1. A composite static and fatigue testing apparatus for aero-engine shaft components, comprising a load-bearing frame (100), a torque loading device (200), a shaft clamping device (300), a loading actuator (400), a torque limiting device (500), an axial force and bending moment loading device (600), and a test shaft (700), characterized in that, A torque loading device (200) is provided on the bearing frame (100). Two torque-applying loading actuators (400) are provided on the torque loading device (200) in the horizontal direction. A shaft clamp device (300) is connected to the torque loading device (200) in the vertical direction. The shaft clamp device (300) includes a lower connecting shaft (301), a deep groove ball bearing (302), and a lower bearing section (303). The upper end of the lower connecting shaft (301) is connected to the test shaft (700), and the lower end of the lower connecting shaft (301) is connected to the torque loading device (200). A deep groove ball bearing (302) is provided on the outer surface of the middle part of the lower connecting shaft (301). The deep groove ball bearing (302) is installed on the lower bearing section (303), and the lower bearing section (303) is connected to the bearing frame (100). The torque limiting device (500) is used for torque transmission of the torque loading device (200) to transmit the force of the torque loading device (200) to the bearing frame (100). It includes a torque limiting disc (501), a torque limiting rod (503) connected to the torque limiting disc (501), and a mounting base (504) connected to the torque limiting rod. The mounting base (504) is connected to the bearing frame (100). The axial force and bending moment loading device (600) is connected to the torsion limiting disk (501) of the torsion limiting device (500) to load the axial force and rotational bending moment required for the test onto the test shaft (700) and decouple the loading of the axial force and rotational bending moment. The axial force and bending moment loading device (600) includes an adapter lug (601), a connecting pin (602), a cross double trunnion (603), a loading disk (604), an upper cross annular bushing (605), and a lower cross annular bushing (606); the connecting pin (602) connects the adapter lug (601), the cross double trunnion (603), the loading disk (604), the upper cross annular bushing (605), and the lower cross annular bushing (606) to form a cross universal joint structure; The top of the universal joint is a loading plate (604), which is connected to the upper bearing section (305) of the shaft clamping device (300). The lower cross annular bushing (606) at the bottom of the universal joint is fixedly connected to the top of the torque limiting plate (501) of the torque limiting device (500) through two adapter lugs (601), thus connecting the shaft clamping device (300), the torque limiting device (500), and the axial force and bending moment loading device (600) together.

2. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 1, characterized in that, The load-bearing frame (100) includes vertical columns (102), horizontal connecting beams (103) connecting the vertical columns (102), horizontal top beams (104) connecting the horizontal connecting beams (103), and horizontal load-bearing beams (101) installed within the load-bearing frame (100).

3. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 2, characterized in that, The torque loading device (200) has two radially protruding and symmetrical torque arms (201) on its outer ring surface, and the torque arms (201) are connected to the loading actuator (400).

4. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 3, characterized in that, The shaft clamping device (300) further includes a cylindrical roller bearing (304), an upper bearing section (305), and an upper connecting shaft (306). The cylindrical roller bearing (304) is disposed between the upper outer surface of the test shaft (700) and the upper connecting shaft (306). The upper end of the upper bearing section (305) is connected to the upper surface of the axial force and bending moment loading device (600). The lower end of the upper bearing section (305) is connected to the test shaft (700). The upper end of the upper connecting shaft (306) is connected to the bearing frame (100).

5. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 4, characterized in that, The loading actuator (400) includes two, each of which is provided with a front connecting flange (401) and a rear connecting flange (402); the front connecting flange (401) of one of the loading actuators (400) is connected to two radially protruding and symmetrical torque arms (201) of the torque loading device (200), and the rear connecting flange (402) is connected to the horizontal connecting beam (103) of the bearing frame (100); The front connecting flange (401) of the other loading actuator is connected to the axial force and bending moment loading device (600), and the rear connecting flange (402) is connected to the horizontal load-bearing beam (101) of the load-bearing frame (100).

6. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 5, characterized in that, Each loading actuator (400) is also provided with a load sensor. One end of the loading actuator (400) is connected to one end of the load sensor through a flange, and the other end of the load sensor is connected to the torque arm (201) of the torque loading device (200) or the axial force and bending moment loading device (600) through a ball joint.

7. A composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 6, characterized in that, The torsion limiting device (500) further includes connecting ears (502). The torsion limiting disk (501) is evenly provided with a plurality of connecting ears (502) along the circumference. Both ends of the torsion limiting rod (503) are provided with single ears that can be adjusted in length along the axial direction of the torsion limiting rod (503). The single ear at one end of the torsion limiting rod (503) is connected to the connecting ears (502) evenly provided along the circumference of the torsion limiting disk (501). The single ear at the other end of the torsion limiting rod (503) is connected to the mounting base (504). The mounting base (504) is connected to the vertical column (102) of the bearing frame (100).

8. The composite static and fatigue testing apparatus for aero-engine shaft parts according to claim 1, characterized in that, The test shaft (700) is installed inside the shaft clamping device (300).

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