CN111579184A - Static rigidity testing device for elastic ring supporting structure of rotor system of aircraft engine - Google Patents

Abstract

The invention discloses a static stiffness test device for an elastic ring supporting structure of an aero-engine rotor system. The device is mainly composed of an elastic ring component part, a force applying device, a force measuring device, an optical testing system and a T-slot plane. The force measuring system can apply different radial loading forces to the elastic ring from small to large, and can accurately test the magnitude of the radial force. The optical test system is used to take pictures of the elastic ring before and after loading, and the elastic ring can be calculated and analyzed before and after being loaded. Part of the deformation, the static stiffness of the elastic ring can be obtained. The present invention applies different magnitudes of force to the elastic ring through the force applying device and the force measuring system, which can be used to study the nonlinear situation of the static stiffness of the elastic ring; the optical testing system of the present invention can test the deformation of the elastic ring at different positions, and can calculate The average static stiffness of the elastic ring and the local static stiffness at different positions are obtained.

Description

Static stiffness test device for elastic ring support structure of aero-engine rotor system

technical field

The invention belongs to the field of aero-engine rotor systems, and in particular relates to a static stiffness test device for an elastic ring supporting structure of an aero-engine rotor system.

Background technique

In order to control the critical speed of the aero-engine, the rotor system of most aero-engines is provided with elastic support at the bearing fulcrum. For small engines, due to their small size, high rotational speed, and wide operating rotational speed range, when the overall structural size of the engine is strictly limited, an effective and feasible method is to use a simple structure, light weight, and small footprint. Elastic ring spring.

The typical structure of the elastic ring is an annular elastic element with several bosses whose inner and outer surfaces are staggered and evenly distributed. The boss on the inner surface is supported on the outer ring of the bearing, the boss on the outer surface is supported on the outer support, and the rigidity is changed by changing the structural parameters, so as to achieve the purpose of controlling the critical speed of the rotor system.

For the elastic ring stiffness, the analytical method and the finite element method are commonly used for calculation. The analytical method is an approximate calculation, and there is a certain deviation; the finite element method is suitable for complex boundary conditions, but the accuracy of the finite element mesh and the parameters of the material will be different. It affects the accuracy of the calculation; therefore, a method of elastic ring stiffness testing is needed to further verify the results of the analytical algorithm and the finite element calculation.

SUMMARY OF THE INVENTION

In view of the above problems, the present invention realizes the loading of force on the elastic ring structure by designing a static stiffness test device for the elastic ring supporting structure of the aero-engine rotor system, and at the same time accurately measures the magnitude of the force, so as to realize the elastic ring structure under the loading state of the force. Deformation at different positions, so as to achieve the purpose of testing the stiffness of the elastic ring.

In order to achieve the above object, the present invention adopts the following technical solutions:

An aero-engine rotor system elastic ring supporting structure static stiffness testing device, including elastic ring assembly, force applying device, force measuring device, optical testing system and T-slot plane 1 .

The T-slot plane 1 is used as the base of the static stiffness test device for the elastic ring support structure of the aero-engine rotor system. The upper surface of the T-slot plane 1 is provided with a plurality of T-slots arranged in parallel to each other for installing and fixing other part.

The elastic ring assembly includes a bearing seat 2, an outer bushing 7, an elastic ring 8 and an inner bushing 9, wherein the bearing seat 2 is arranged on the T-slot plane 1, and the outer bushing 7 is arranged on the bearing seat 2 with an interference fit. In the inner hole of the elastic ring 8, the elastic ring 8 is arranged in the outer bushing 7, the inner bushing 9 is arranged in the elastic ring 8, the inner surface and the outer surface of the elastic ring 8 are provided with bosses, and the bosses on the inner surface are The bosses on the outer surface are staggered and evenly distributed, the bosses on the outer surface are supported on the outer bushing 7 , and the bosses on the inner surface are supported on the inner bushing 9 .

The force measuring device includes a force sensor 10, a mechanical data acquisition system 5 and an adapter tool 11, wherein one end of the force sensor 10 is fixedly connected to one end of the adapter tool 11, and the other end of the adapter tool 11 is connected to the inner bushing 9. Contact, the other end of the force sensor 10 is fixed on the top plate 15 of the force applying device, and the force sensor 10 is connected with the mechanical data acquisition system 5 .

The force applying device includes a handle 12, a lead screw 13, a slide rail 14, a top plate 15 and a fixing plate 16. The handle 12 is fixedly connected to one end of the lead screw 13, and the fixing plate 16 includes a front plate 1601 and a bottom plate 1602 that are perpendicular to each other. , the front plate 1601 and the bottom plate 1602 form an L shape; the middle of the front plate 1601 is provided with a threaded hole that matches the size of the lead screw 13, the lead screw 13 passes through the threaded hole, and the other end of the lead screw 13 is fixedly connected to the middle of the top plate 15, The top plate 15 and the front plate 1601 are arranged parallel to each other, the bottom plate 1602 is provided with a slide rail 14 , and one end surface of the top plate 15 is matched with the slide rail 14 .

The optical test system includes an optical test camera 3, an optical test software system 4 and a three-coordinate tester 6, the optical test camera 3 and the three-coordinate tester 6 are arranged on the T-slot plane 1, and the optical test camera 3 is connected to the optical tester 6. The software system 4 is connected; the bearing seat 2 and the optical test camera 3 are in two parallel planes, and the three-coordinate tester 6 is used to determine that the optical test camera 3 and the bearing seat 2 are in two parallel planes to ensure the optical test accuracy.

Further, the optical test camera 3 is a GOM optical camera.

Further, the force sensor 10 is a static force sensor, and the cable of the force sensor 10 is connected to the interface of the mechanical data acquisition system 5 .

Beneficial effects of the present invention:

By designing the force applying device and the force measuring system, the invention can apply different radial loading forces to the elastic ring from small to large, and can accurately test the magnitude of the radial force, and can be used to study the nonlinear situation of the static stiffness of the elastic ring.

The invention uses a three-coordinate tester to test and adjust the optical camera and the elastic ring assembly, which can accurately ensure that the optical camera and the elastic ring assembly are in a parallel plane, and can make the optical test of the elastic ring deformation more accurate.

The invention uses an optical testing system to take pictures before and after the elastic ring is loaded, and can calculate and analyze the deformation of each part before and after the elastic ring is loaded, analyze the average static stiffness of the elastic ring, and analyze the local static stiffness of the elastic ring.

Description of drawings

1 is a schematic structural diagram of a static stiffness testing device for an elastic ring support structure of an aero-engine rotor system provided in an embodiment of the present invention.

2 is a schematic structural diagram of the elastic ring assembly of the static stiffness testing device for the elastic ring supporting structure of the aero-engine rotor system provided in the embodiment of the present invention.

3 is a schematic structural diagram of the force measuring device of the static stiffness testing device for the elastic ring support structure of the aero-engine rotor system provided in the embodiment of the present invention.

FIG. 4 is a schematic diagram of a force applying device of the static stiffness test device of the elastic ring support structure of the aero-engine rotor system provided in the embodiment of the present invention.

Fig. 5 is a schematic diagram of the position of the deformation observation point of the elastic ring.

In the picture: 1T groove plane; 2 bearing seat; 3 optical test camera; 4 optical test software system; 5 mechanical data acquisition system; 6 three-coordinate tester; 7 outer bushing; 8 elastic ring; 9 inner bushing; 10 Force sensor; 11 transfer tool; 12 handle; 13 lead screw; 14 slide rail; 15 top plate; 16 fixed plate; 1601 front plate; 1602 bottom plate.

Detailed ways

The specific embodiments of the present invention will be further described below with reference to the accompanying drawings and technical solutions.

1 is a schematic structural diagram of a static stiffness testing device for an elastic ring support structure of an aero-engine rotor system provided in an embodiment of the present invention. As shown in Figure 1, the static stiffness test device of the elastic ring support structure of the aero-engine rotor system includes an elastic ring assembly, a force application device, a force measurement device, an optical test system and a T-slot plane 1.

The T-slot plane 1 is used as the base of the static stiffness test device for the elastic ring support structure of the aero-engine rotor system. The upper surface of the T-slot plane 1 is provided with a plurality of T-slots arranged in parallel to each other for installing and fixing other components. .

FIG. 2 is a schematic diagram of the structure of the elastic ring assembly. As shown in Figures 1 and 2, the elastic ring assembly includes a bearing seat 2, an outer bushing 7, an elastic ring 8 and an inner bushing 9, wherein the bearing seat 2 is fixed to the T-slot plane 1 by bolts, and the outer bushing 7. The interference fit is installed into the inner hole of the bearing seat 2, the elastic ring 8 is arranged in the middle of the outer bushing 7, the inner bushing 9 is arranged in the elastic ring 8, and the inner surface and the outer surface of the elastic ring 8 are provided with convex The bosses on the inner surface and the bosses on the outer surface are staggered and evenly distributed, wherein the bosses on the outer surface are supported on the outer bushing 7 , and the bosses on the inner surface are supported on the inner bushing 9 .

3 is a schematic structural diagram of the force measuring device of the static stiffness testing device for the elastic ring support structure of the aero-engine rotor system provided in the embodiment of the present invention. Figure 4 is a schematic diagram of the mechanism of the force applying device. Referring to FIGS. 3 and 4 , in the embodiment, the force measuring device includes a force sensor 10, a mechanical data acquisition system 5 and an adapter 11, wherein one end of the force sensor 10 is fixed to one end of the adapter 11 (for example, fixed by bolts). ), the other end of the adapter tool 11 is in contact with the inner bushing 9 , the other end of the force sensor 10 is fixed to the top plate 15 of the force applying device (for example, fixed by bolts), and the force sensor 10 is connected to the mechanical data acquisition system 5 . Specifically, the cable of the force sensor 10 is connected to the interface of the mechanical data acquisition system 5 .

The force applying device includes a handle 12 , a lead screw 13 , a slide rail 14 , a top plate 15 and a fixed plate 16 . The handle 12 is fixedly connected to one end of the lead screw 13 (eg by welding), and the fixing plate 16 includes a front plate 1601 and a bottom plate 1602 arranged perpendicular to each other, and the front plate 1601 and the bottom plate 1602 form an L-shape. The middle of the front plate 1601 is provided with a threaded hole that matches the size of the lead screw 13, the lead screw 13 passes through the threaded hole, and the other end of the lead screw 13 is fixedly connected (for example, by welding) to the middle of the top plate 15. They are arranged parallel to each other, the bottom plate 1602 is provided with the slide rail 14 , and one end surface of the top plate 15 is matched with the slide rail 14 .

When in use, the force applying device drives the lead screw 13 to rotate by turning the handle 12, and then the top plate 15 slides along the slide rail 14, so as to exert a corresponding force on the force sensor 10, and the force sensor 10 converts the force analog signal into The digital signal of the voltage is used to identify the magnitude of the loading force through the software, and the force sensor 10 transmits the force to the elastic ring assembly through the adapter tool 11 .

The optical test system includes an optical test camera 3, an optical test software system 4 and a three-coordinate tester 6. The optical test camera 3 and the three-coordinate tester 6 are fixed on the T-slot plane 1 by bolts, and the optical test camera 3 is mounted on the bearing. In the inner T-slot of the T-slot plane 1 of the base 2 parallel to each other, the three-coordinate tester 6 is installed on the optical test camera 3 at a position close to the bearing base 2, so as to detect the optical test camera 3 and the bearing base 2. The positional relationship of the bearing housing 2. The optical test camera 3 is connected to the optical test software system 4 . Specifically, the optical test camera 3 is arranged on the T-slot plane 1, so that the bearing seat 2 and the optical test camera 3 are in two parallel planes, and the bearing seat 2 and the optical test camera 3 are installed on the T-slot plane 1 by bolts In the different parallel T-slots, the optical test camera 3 and the bearing seat 2 are fine-tuned by the three-coordinate tester 6 to ensure that the bearing seat 2 and the optical test camera 3 are accurately in two parallel planes, and the optical The center of the lens of the test camera 3 is concentric with the center of the elastic ring 8, so as to ensure the optical test accuracy.

In this embodiment, the optical test camera 3 is a GOM optical camera. The GOM optical camera is used to take pictures of the elastic ring assembly before and after the force is loaded, and the GOM optical analysis software is used to analyze and calculate the deformation at each position of the elastic ring 8 before and after the force is loaded. , and then obtain the deformation of the elastic ring 8 under force loading.

The method of using the static stiffness test device of the elastic ring support structure of the aero-engine rotor system for testing:

Before the test, firstly fix the three-coordinate tester 6 to the T-slot plane 1 by bolts, and install the optical test camera 3 and the bearing seat 2 along the T-slot direction of the T-slot plane 1 by bolts ( The bolts are not tightened), and then use the three-coordinate tester 6 to test and fine-tune the optical test camera 3 and the bearing seat 2 to ensure that the optical test camera 3 and the bearing seat 2 are on two parallel planes.

As shown in FIG. 3 , one end of the force sensor 10 is fixed to the inner bushing 9 through the adapter tool 11 , and the other end is fixed to the top plate 15 of the force applying device. When the handle 12 is turned, the lead screw 13 will drive the top plate 15 along the slide rail 14 Translate forward (as shown in FIG. 4 ), thereby applying radial force to the force sensor 10 , the force sensor 10 radially loads the elastic ring assembly through the adapter tool 11 , wherein the cable of the force sensor 10 is connected to the mechanical data acquisition on system 5. The total mass of the force sensor 10 and the transfer tooling 11 is m. By analyzing the mechanical data acquisition system 5, the force F ₀ of the force sensor 10 being loaded by the top plate 15 can be obtained, and the radial force F of the elastic ring assembly can be obtained as :

F=F ₀ +mg (1)

The GOM optical camera is used to take pictures of the elastic ring assembly (before and after force loading), and the optical test software system 4 is used to analyze and process the photos before and after the force loading, and the deformation of the elastic ring 8 before and after the force can be obtained. The elastic ring 8 is provided with a deformation observation point near each boss, with a total of n displacement observation points (as shown in FIG. 5 , in this embodiment, 8 bosses are assumed inside and outside the elastic ring). Then the average deformation of the elastic ring 8 after radial loading can be expressed as the following formula:

where s is the average deformation of the elastic ring, n is the number of bosses, and s _i is the deformation of the i-th observation point.

According to the testing principle of the radial static stiffness of the elastic ring 8, the static stiffness of the elastic ring can be obtained: a force of magnitude F is applied to the elastic ring 8 in the radial direction, and the average radial deformation of the elastic ring under this force is s. , the static stiffness k of the elastic ring can be obtained according to the following formula (1).

k=F/s (3)

The local stiffness at different positions of the elastic ring can be obtained according to the following formula (4), where k _i is the local stiffness at each boss position of the elastic ring 8 .

k _i =F/s _i (4)

The test device can accurately test the average static stiffness and local stiffness of the elastic ring of the aero-engine rotor system, and can also be used to study the nonlinear situation of the static stiffness of the elastic ring.

Claims (3)

1. A static stiffness testing device for an elastic ring supporting structure of an aircraft engine rotor system is characterized by comprising an elastic ring assembly, a force application device, a force measurement device, an optical testing system and a T-shaped groove plane (1); wherein,

the T-shaped groove plane (1) is used as a base of the static rigidity testing device of the elastic ring supporting structure of the aircraft engine rotor system, and a plurality of T-shaped grooves which are arranged in parallel are arranged on the upper surface of the T-shaped groove plane (1) and used for installing and fixing other components;

the elastic ring assembly comprises a bearing seat (2), an outer bushing (7), an elastic ring (8) and an inner bushing (9), wherein the bearing seat (2) is arranged on a T-shaped groove plane (1), the outer bushing (7) is arranged in an inner hole of the bearing seat (2) in an interference fit manner, the elastic ring (8) is arranged in the outer bushing (7), the inner bushing (9) is arranged in the elastic ring (8), bosses are arranged on the inner surface and the outer surface of the elastic ring (8), the bosses on the inner surface and the bosses on the outer surface are mutually staggered and uniformly distributed, the bosses on the outer surface are supported on the outer bushing (7), and the bosses on the inner surface are supported on the inner bushing (9);

the force measuring device comprises a force sensor (10), a mechanical data acquisition system (5) and a switching tool (11), wherein one end of the force sensor (10) is fixedly connected with one end of the switching tool (11), the other end of the switching tool (11) is contacted with an inner bushing (9), the other end of the force sensor (10) is fixed on a top plate (15) of the force application device, and the force sensor (10) is connected with the mechanical data acquisition system (5);

the force application device comprises a handle (12), a lead screw (13), a sliding rail (14), a top plate (15) and a fixing plate (16), wherein the handle (12) is fixedly connected with one end of the lead screw (13), the fixing plate (16) comprises a front plate (1601) and a bottom plate (1602) which are perpendicular to each other, and the front plate (1601) and the bottom plate (1602) form an L shape; the middle of the front plate (1601) is provided with a threaded hole matched with the size of the lead screw (13), the lead screw (13) passes through the threaded hole, the other end of the lead screw (13) is fixedly connected with the middle of the top plate (15), the top plate (15) and the front plate (1601) are arranged in parallel, the bottom plate (1602) is provided with a slide rail (14), and one end face of the top plate (15) is matched with the slide rail (14);

the optical testing system comprises an optical testing camera (3), an optical testing software system (4) and a three-coordinate tester (6), wherein the optical testing camera (3) and the three-coordinate tester (6) are arranged on the T-shaped groove plane (1), and the optical testing camera (3) is connected with the optical testing software system (4); the bearing seat (2) and the optical testing camera (3) are located in two parallel planes, and the three-coordinate testing instrument (6) is used for determining that the optical testing camera (3) and the bearing seat (2) are located in the two parallel planes so as to guarantee the optical testing accuracy.

2. The aircraft engine rotor system elastic ring supporting structure static stiffness testing device according to claim 1, characterized in that the optical testing camera (3) is a GOM optical camera.

3. The aeroengine rotor system elastic ring supporting structure static stiffness testing device according to claim 1 or 2, characterized in that the force sensor (10) is a static force sensor, and a cable of the force sensor (10) is connected to an interface of a mechanical data acquisition system (5).

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