Aero-engine main shaft composite load loading test device

Abstract

The present application relates to the technical fields of aero-engine structure strength test, and discloses a kind of aero-engine main shaft composite load loading test device, including fixed platform, the bottom of fixed platform is provided with first stewart platform, vertical direction is provided with guide support column on fixed platform, guide support column is installed with movable platform, still be provided with adjusting locking mechanism and first bearing on fixed platform;Movable platform is provided with counterforce seat, six-component force sensor is arranged between main shaft and first stewart platform.The present application can realize six degrees of freedom motion in a certain range of space rectangular coordinate system, applies composite load to main shaft by first stewart platform, meets the demand of space composite load loading;And installation environment of main shaft on bearing is simulated in loading process, can simulate the fatigue life test of aero-engine main shaft under axial force, lateral force, vertical force or torsional stiffness of main shaft under bearing installation condition.

Description

Technical Field

[0001] This invention relates to the field of aero-engine structural strength testing technology, and discloses an aero-engine main shaft composite load loading test device. Background Technology

[0002] The main shaft structure strength test of an aero-engine is a test conducted to assess the structural component's ability to withstand loads without failure. This test is widely carried out during the development of aero-engine products. The main components of the main shaft structure strength test include static strength testing, stiffness testing, pressure testing, and fatigue life testing.

[0003] Stewart parallel mechanisms (i.e., Stewart platforms) are widely used in mechanical assembly, motion simulation, and forming devices due to their advantages such as six degrees of freedom, compact structure, high rigidity, and high load-bearing capacity. A Stewart parallel mechanism consists of servo-loaded actuators, a stationary coil, and a moving coil. Types of servo-loaded actuators include electric, hydraulic, and pneumatic servo actuators. Hydraulic servo actuators are used for high-frequency response applications; pneumatic servo actuators are used for high-speed applications; and electric servo actuators are used for other applications. One Stewart parallel mechanism contains six servo-loaded actuators. The two ends of each servo-loaded actuator are connected to the stationary and moving coils via universal joints. The stationary coil is connected to the fixed or moving platform via a flange.

[0004] The main shaft of an aero-engine is subjected to very complex loads and operating conditions. During the testing of the main shaft, it is necessary to simultaneously apply multi-dimensional composite loads in space, including axial, lateral, bending, and torque loads. Existing composite loading devices are complex in structure or can only load one or a few types of composite loads. Summary of the Invention

[0005] The purpose of this invention is to provide a composite load loading test device for aero-engine main shafts. The first Stewart platform can achieve six-degree-of-freedom motion within a certain range of a spatial rectangular coordinate system. Composite loads are applied to the main shaft through the first Stewart platform, and measurements are taken using six-component force sensors installed between the main shaft and the first Stewart platform, thus meeting the requirements for spatial composite load loading. Moreover, the loading process simulates the installation environment of the main shaft on the bearing, and can simulate the fatigue life test of aero-engine main shafts under axial force, lateral force, vertical force, or torsional stiffness of the main shaft under bearing installation conditions.

[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0007] A composite load loading test device for an aero-engine main shaft includes a fixed platform mounted on a support, a first Stewart platform at the bottom of the fixed platform, a guide support column vertically mounted on the fixed platform, and a movable platform mounted on the guide support column. The fixed platform also includes an adjustment and locking mechanism, which is drivenly connected to the movable platform. The adjustment and locking mechanism is used to adjust the movable platform to move axially along the guide support column to a preset position and then lock it in place. Both the fixed platform and the movable platform have openings through which the aero-engine main shaft can pass. A first bearing is also mounted on the fixed platform to fix the bearing of the main shaft. A reaction seat is provided on the movable platform. One end of the main shaft is fixedly connected to the first Stewart platform via a flange, and the other end of the main shaft is fixed to the reaction seat. A six-component force sensor is provided between the main shaft and the first Stewart platform.

[0008] Furthermore, the first bearing is mounted on the fixed platform via a first cage ring.

[0009] Furthermore, the reaction seat includes a second Stewart platform, which is arranged opposite to the first Stewart platform and is fixedly connected to the spindle.

[0010] Furthermore, a six-component force sensor is also installed between the spindle and the second Stewart platform.

[0011] Furthermore, a second bearing is installed on the active platform, which is used to axially fix the spindle.

[0012] Furthermore, the second bearing is fixedly connected to the movable platform via the second squirrel cage ring.

[0013] Furthermore, the adjusting and locking mechanism is any one or a combination of at least two of the following: a lead screw, a telescopic cylinder, and a hydraulic telescopic rod.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: the first Stewart platform in the present invention can realize six-degree-of-freedom motion within a certain range of a spatial rectangular coordinate system. The first Stewart platform applies a composite load to the spindle, and the six-component force sensors set between the spindle and the first Stewart platform are used for measurement, which meets the requirements of spatial composite load loading. Moreover, the loading process simulates the installation environment of the spindle on the bearing, and can simulate the fatigue life test of the aero-engine spindle under the axial force, lateral force, vertical force or torsional stiffness of the spindle under the bearing installation conditions. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the composite load loading test device for the main shaft of an aero-engine in the embodiment.

[0016] Figure 2 This is a perspective view of the composite load loading test device for the main shaft of an aero-engine in the embodiment.

[0017] The components are: 1. Support; 2. Fixed platform; 3. Guide support column; 4. Movable platform; 5. Main shaft; 6. First cage ring; 7. First Stewart platform; 8. First bearing; 9. Adjustment and locking mechanism; 10. Six-component force sensor; 11. Second bearing; 12. Second cage ring; 13. Second Stewart platform. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0019] Example

[0020] See Figure 1 and Figure 2 A composite load loading test device for an aero-engine main shaft includes a fixed platform 2 mounted on a support 1, a first Stewart platform 7 at the bottom of the fixed platform 2, a guide support column 3 vertically mounted on the fixed platform 2, and a movable platform 4 mounted on the guide support column 3; the fixed platform 2 also includes an adjustment and locking mechanism 9, which is drivenly connected to the movable platform 4 and used to adjust the movable platform 4 to move axially along the guide support column 3 to a preset position and then lock it in place; both the fixed platform 2 and the movable platform 4 have openings through which the aero-engine main shaft 5 can pass; a first bearing 8 is also mounted on the fixed platform 2, which is used to fix the bearing of the main shaft 5; a reaction seat is provided on the movable platform 4, one end of the main shaft 5 is fixedly connected to the first Stewart platform 7 via a flange, the other end of the main shaft 5 is fixed to the reaction seat, and a six-component force sensor 10 is provided between the main shaft 5 and the first Stewart platform 7.

[0021] In this embodiment, when a composite load loading test is required on the main shaft 5, one end of the aero-engine main shaft 5 with a bearing on the shoulder is first passed through the opening of the movable platform 4, so that one end of the main shaft 5 is located on the first Stewart platform 7. One end of the main shaft 5 is fixedly connected to the first Stewart platform 7 through a flange, and the other end of the main shaft 5 is fixed to the reaction seat (which can generally be fixed by a flange or bolts). The movable platform 4 is adjusted to move axially along the guide support column 3 by adjusting the locking mechanism 9, so that the first bearing 8 on the movable platform 4 corresponds to the bearing on the shoulder, and then the position of the movable platform 4 is locked and limited, fixing the bearing in the first bearing 8. Then, the first Stewart platform 7 is controlled to apply a composite load to the main shaft 5. In this embodiment, the first Stewart platform 7 can realize six-degree-of-freedom motion within a certain range of a spatial rectangular coordinate system. The first Stewart platform 7 applies a composite load to the spindle 5, and the six-component force sensor 10 set between the spindle 5 and the first Stewart platform 7 is used for measurement to meet the spatial composite load loading requirements. Moreover, the loading process simulates the installation environment of the spindle 5 on the bearing, and can simulate the fatigue life test of the aero-engine spindle 5 under the axial force, lateral force, vertical force or torsional stiffness of the spindle 5 under the bearing installation conditions.

[0022] In this embodiment, the first bearing 8 is mounted on the fixed platform 2 via the first cage ring 6. The stiffness of the first cage ring 6 can be adjusted according to the experimental design, which can further realize the variable stiffness support test of the main shaft 5.

[0023] In this embodiment, the reaction seat includes a second Stewart platform 13, which is positioned opposite to the first Stewart platform 7 and is fixedly connected to the main shaft 5. The second Stewart platform 13 can achieve six-degree-of-freedom motion within a certain range of a spatial Cartesian coordinate system; it works in conjunction with the first Stewart platform 7 to meet the requirements of composite loads under different loading conditions. For example, during the application of force by the first Stewart platform 7, torque can be applied to the main shaft 5 through the second Stewart platform 13, simulating the actual operating conditions of an aero-engine.

[0024] In this embodiment, both the first Stewart platform 7 and the second Stewart platform 13 consist of servo load actuators, a stationary coil, and a moving coil. The types of servo load actuators include electric servo actuators, hydraulic servo actuators, and pneumatic servo actuators. For high-frequency response applications, hydraulic servo actuators can be used; for high-speed requirements, pneumatic servo actuators can be used; and for other applications, electric servo actuators can be used. Both the first Stewart platform 7 and the second Stewart platform 13 contain six servo load actuators. The two ends of each servo load actuator are connected to the stationary and moving coils via universal hinges. The stationary coil is connected to the corresponding support 1 or reaction seat via a flange. In this embodiment, the servo load actuators of the first Stewart platform 7 are divided into three groups, evenly distributed along the circumference. Each group has two actuators arranged in an isosceles triangle. This allows the moving coil to move with six degrees of freedom within a certain range in a spatial rectangular coordinate system, meeting the requirements for spatial composite load loading.

[0025] In this embodiment, a six-component force sensor 10 is also provided between the main spindle 5 and the second Stewart platform 13. By installing a six-component force sensor 10 on each of the first Stewart platform 7 and the second Stewart platform 13, six-degree-of-freedom load closed-loop control can be achieved through a decoupling algorithm.

[0026] A second bearing 11 is installed on the movable platform 4. The second bearing 11 is used to axially fix the main shaft 5, which can realize the combined loading of axial force, lateral force, vertical force or torsional stiffness of the main shaft 5 under the action of double bearing fixation. Similarly, in this embodiment, the second bearing 11 is fixedly connected to the movable platform 4 through a second cage ring 12. The stiffness of the second cage ring 12 can be adjusted according to the experimental design, which can further realize the variable stiffness support test of the main shaft 5.

[0027] In this embodiment, the first bearing 8 can be a roller bearing, which only bears radial loads. The second bearing 11 can be a ball bearing, which can bear both axial and radial loads, and can simulate the actual working conditions of the main shaft of an aero-engine.

[0028] The adjustment and locking mechanism 9 in this embodiment is used to adjust the position of the movable platform 4, so that the movable platform 4 can be moved axially along the guide support column 3 to a preset position and then locked and limited. The adjustment and locking mechanism 9 can be any one or a combination of at least two of the following: lead screw, telescopic cylinder, and hydraulic telescopic rod.

[0029] 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 protection scope of the present invention.

Claims

1. A composite load loading test device for aero-engine main shaft, characterized in that, The system includes a fixed platform (2) mounted on a support (1), a first Stewart platform (7) at the bottom of the fixed platform (2), a guide support column (3) vertically mounted on the fixed platform (2), and a movable platform (4) mounted on the guide support column (3); the fixed platform (2) is also equipped with an adjustment and locking mechanism (9), which is drivenly connected to the movable platform (4). The adjustment and locking mechanism (9) is used to adjust the movable platform (4) to move axially along the guide support column (3) to a preset position and then lock it in place; both the fixed platform (2) and the movable platform (4) are equipped with adjustable... An opening for the main shaft (5) of an aircraft engine to pass through; a first bearing (8) is also installed on the fixed platform (2), which is used to fix the bearing of the main shaft (5); a reaction seat is provided on the movable platform (4), one end of the main shaft (5) is fixedly connected to the first Stewart platform (7) through a flange, and the other end of the main shaft (5) is fixed on the reaction seat; a six-component force sensor (10) is provided between the main shaft (5) and the first Stewart platform (7); a second bearing (11) is installed on the movable platform (4), which is used to axially fix the main shaft (5); The first bearing (8) is mounted on the fixed platform (2) via the first cage ring (6), and the second bearing (11) is fixedly connected to the movable platform (4) via the second cage ring (12). The first bearing (8) is a roller bearing that only bears radial load, and the second bearing (11) is a ball bearing that bears axial load and radial load. The reaction seat includes a second Stewart platform (13), which is arranged opposite to the first Stewart platform (7), and the second Stewart platform (13) is fixedly connected to the main shaft (5).

2. The composite load loading test device for aero-engine main shaft according to claim 1, characterized in that, A six-component force sensor (10) is also provided between the main spindle (5) and the second Stewart platform (13).

3. The composite load loading test device for aero-engine main shaft according to claim 1, characterized in that, The adjusting and locking mechanism (9) is any one or a combination of at least two of the following: lead screw, telescopic cylinder, and hydraulic telescopic rod.

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