1. An aeroengine elastic support fatigue test device which is characterized by comprising:

a support (1);

the motor (2) is connected to the bracket (1);

a loading rod (3), one end of which can be sleeved with an elastic supporting test piece (4);

the sliding bearing (5) is sleeved at the other end of the loading rod (3), is connected to a rotating shaft of the motor (2), and can slide along the radial direction of the rotating shaft of the motor (2);

the mounting plate (6) is connected to the bracket (1) and is provided with a mounting hole for mounting the elastic support test piece (4);

the supporting plate (7) is connected to the bracket (1) and is provided with a supporting hole;

the piston rod of the actuating cylinder (8) is connected with one end, back to the motor (2), of the loading rod (3);

and the joint bearing (9) is sleeved on the cylinder body of the actuating cylinder (8) and is arranged in the support hole.

2. The fatigue test device for an elastic support of an aircraft engine according to claim 1,

further comprising:

the rotary disc (10) is connected to the rotating shaft of the motor (2), a disc cavity is formed in the rotary disc, and a plurality of radial displacement adjusting holes are formed in the edge of the rotary disc; the disc cavity is communicated with each radial adjusting hole, and the sliding bearing (5) is arranged in the disc cavity;

and a plurality of radial displacement adjusting bolts (11), wherein each radial displacement adjusting bolt is correspondingly screwed in one radial displacement adjusting hole and abuts against the sliding bearing (5).

3. The fatigue test device for an elastic support of an aircraft engine according to claim 2,

further comprising:

one end of the adapter cylinder (12) is sleeved on the turntable (10), and the other end of the adapter cylinder is connected on the rotating shaft of the motor (2).

4. The fatigue test device for an elastic support of an aircraft engine according to claim 3,

the rotary disc (10) is provided with a convex part;

one end of the adapter cylinder (12), which faces away from the rotating shaft of the motor (2), is sleeved on the convex part.

5. The fatigue test device for an elastic support of an aircraft engine according to claim 4,

further comprising:

and the plurality of adapter bearings (13) are arranged in the adapter cylinder (12) and are sleeved on the convex parts.

6. The fatigue test device for an elastic support of an aircraft engine according to claim 3,

further comprising:

the connecting plate (14) is connected to the bracket (1) and is provided with a connecting hole; the connecting hole is sleeved on the adapter cylinder (12).

7. The fatigue test device for an elastic support of an aircraft engine according to claim 1,

further comprising:

and the simulation bearing (15) is sleeved at one end of the loading rod (3) back to the rotating shaft of the motor (2), and is arranged in the elastic support test piece (4).

8. The fatigue test device for an elastic support of an aircraft engine according to claim 1,

further comprising:

and the dynamometer (16) is connected between the piston rod of the actuating cylinder (8) and one end of the loading rod (3) back to the motor (2).

9. The fatigue test device for an elastic support of an aircraft engine according to claim 8,

the adapter (17) is connected between the piston rod of the actuating cylinder (8) and the dynamometer (16).

10. The fatigue test device for an elastic support of an aircraft engine according to claim 1,

further comprising:

and the two anti-abrasion rings (18) are sleeved on the piston rod of the actuating cylinder (8), are positioned at the sealing part between the piston rod and the cylinder body of the actuating cylinder (8), and are symmetrically distributed on two sides of the joint bearing (9).

Background

The elastic support is an important component in an aircraft engine rotor system, once the elastic support is damaged, the dynamic balance of the rotor system can be influenced, the overall vibration of the aircraft engine is caused, catastrophic accidents are caused, the elastic support is subjected to fatigue test, relevant test data is obtained, and data support can be provided for the design and improvement of the elastic support.

The elastic support bears axial load when in work and can displace along the radial direction when rotating, and the current test device is shown in figure 1 and has the following defects:

1) the lower end of a radial load loading rod is supported by a single-lug and double-lug connection structure, the single-lug and double-lug connection structure bears axial load and rotary radial load and is close to an elastic bearing test piece, the radial force of a lever acting on the position is large, and the radial load loading rod is easy to wear in the high-cycle fatigue loading process and influences the loading precision of the test load;

2) the axial load dynamometer is positioned between the single-double lug connecting structure supporting the lower end of the radial load loading rod and the axial load loading actuator cylinder, large radial load exists on an axial measuring path, and the influence of friction on measurement is large.

The present application has been made in view of the above-mentioned technical drawbacks.

It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.

Disclosure of Invention

The application aims to provide an aeroengine elastic support fatigue testing device to overcome or alleviate at least one technical defect of the known existence.

The technical scheme of the application is as follows:

an aeroengine elastic support fatigue test device comprises:

a support;

the motor is connected to the bracket;

one end of the loading rod can be sleeved with an elastic supporting test piece;

the sliding bearing is sleeved at the other end of the loading rod, is connected to a rotating shaft of the motor and can slide along the radial direction of the rotating shaft of the motor;

the mounting plate is connected to the bracket and is provided with a mounting hole for mounting the elastic support test piece;

the supporting plate is connected to the bracket and is provided with a supporting hole;

the piston rod of the actuating cylinder is connected with one end of the loading rod, which is back to the motor;

and the joint bearing is sleeved on the cylinder body of the actuating cylinder and is arranged in the support hole.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

the rotary disc is connected to a rotating shaft of the motor, a disc cavity is formed in the rotary disc, and a plurality of radial displacement adjusting holes are formed in the edge of the rotary disc; the disc cavity is communicated with each radial adjusting hole, and a sliding bearing is arranged in the disc cavity;

and each radial displacement adjusting bolt is correspondingly screwed in one radial displacement adjusting hole and abuts against the sliding bearing.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

one end of the switching cylinder is sleeved on the turntable, and the other end of the switching cylinder is connected to a rotating shaft of the motor.

According to at least one embodiment of the application, in the aeroengine elastic support fatigue testing device, the turntable is provided with a protruding part;

one end of the adapter cylinder, which is back to the motor rotating shaft, is sleeved on the convex part.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

and the plurality of adapter bearings are arranged in the adapter cylinder and are sleeved on the convex parts.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

the connecting plate is connected to the bracket and is provided with a connecting hole; the connecting hole is sleeved on the adapter tube.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

and the simulation bearing is sleeved at one end of the loading rod, which is back to the motor rotating shaft, and is arranged in the elastic support test piece.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

and the dynamometer is connected between the piston rod of the actuating cylinder and one end of the loading rod, which is back to the motor.

According to at least one embodiment of the application, in the aeroengine elastic support fatigue test device, the adapter is connected between the piston rod of the actuator cylinder and the dynamometer.

According to at least one embodiment of the present application, the fatigue testing apparatus for an elastic support of an aircraft engine further includes:

and the two anti-wear rings are sleeved on the piston rod of the actuating cylinder, positioned at the sealing part between the piston rod and the cylinder body of the actuating cylinder and symmetrically distributed at two sides of the joint bearing.

Drawings

FIG. 1 is a schematic view of a prior art fatigue testing device for an aircraft engine elastomeric bearing;

FIG. 2 is a schematic diagram of an aeroengine elastic support fatigue testing device provided by an embodiment of the application;

FIG. 3 is a partial schematic view of an aircraft engine elastic support fatigue testing device provided by an embodiment of the application;

wherein:

1-a scaffold; 2, a motor; 3-a loading rod; 4-elastically supporting the test piece; 5-a sliding bearing; 6, mounting a plate; 7-a support plate; 8-an actuator cylinder; 9-knuckle bearing; 10-a turntable; 11-a radial displacement adjustment bolt; 12-a transfer cylinder; 13-a transfer bearing; 14-a connecting plate; 15-simulating a bearing; 16-a force gauge; 17-an adapter; 18-wear ring.

For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.

Detailed Description

In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.

In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.

Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.

The present application is described in further detail below with reference to fig. 1 to 3.

An aeroengine elastic support fatigue test device comprises:

a bracket 1;

the motor 2 is connected to the bracket 1;

a loading rod 3, one end of which can be sleeved with an elastic supporting test piece 4;

the sliding bearing 5 is sleeved at the other end of the loading rod 3, is connected to a rotating shaft of the motor 2, can slide along the radial direction of the rotating shaft of the motor 2, and can be a self-aligning ball bearing in a specific form;

a mounting plate 6 connected to the bracket 1 and having a mounting hole for mounting the elastic support test piece 4;

a support plate 7 connected to the bracket 1 and having a support hole thereon;

the piston rod of the actuating cylinder 8 is connected with one end of the loading rod 3, which is back to the motor 2;

and the joint bearing 9 is sleeved on the cylinder body of the actuating cylinder 8 and is arranged in the support hole.

With respect to the fatigue testing device for the elastic support of the aircraft engine disclosed in the above embodiment, it will be understood by those skilled in the art that it can perform fatigue test on the elastic support test piece 4 by outputting rotation through the rotating shaft of the motor 2 and generating radial displacement on the elastic support test piece 4 through the sliding bearing 5 sliding along the radial direction of the rotating shaft of the motor 2, and applying an axial load to the elastic support test piece 4 through the actuator 8.

For the fatigue test device for the elastic bearing of the aircraft engine disclosed in the above embodiment, it can be further understood by those skilled in the art that one end of the loading rod 3 facing away from the motor 2 is connected to the piston rod of the actuator cylinder 8, the cylinder of the actuator cylinder 8 is connected to the support plate 7, that is, the lower end of the loading rod 3 is supported by the support plate 7 through the actuator cylinder 8, and the radial load is transmitted to the bracket 1 through the support 7, so that the fatigue test device is not easily damaged by abrasion, and the loading accuracy of the test load can be ensured.

For the aeroengine elastic support fatigue test device disclosed in the above embodiment, it can be further understood by those skilled in the art that the support plate 7 supports the lower end of the loading rod 3 and simultaneously provides support for the actuator cylinder 8, and the support actuator cylinder 8 applies an axial load to the elastic support test piece 4, so that the aeroengine elastic support fatigue test device is simple in structure and easy to manufacture and assemble.

For the aeroengine elastic support fatigue test device disclosed in the above embodiment, it can be understood by those skilled in the art that the cylinder of the actuator cylinder 8 is connected to the support plate 7 through the knuckle bearing 9, and can deflect within a certain angle range, so as to release the stress on the elastic support test piece 4, which generates radial displacement, to a certain extent, and ensure the loading precision of the test load.

With respect to the fatigue testing device for the elastic support of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the radial force between the cylinder of the actuating cylinder 8 and the joint position of the knuckle bearing 9 is greatly reduced after redistribution by the lever ratio, and no serious abrasion is generated at this position.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

a rotary plate 10 connected to a rotary shaft of the motor 2, having a plate cavity thereon, and having a plurality of radial displacement adjusting holes at an edge thereof; the disc cavity is communicated with each radial adjusting hole, and a sliding bearing 5 is arranged in the disc cavity;

and a plurality of radial displacement adjusting bolts 11, each of which is correspondingly screwed in one of the radial displacement adjusting holes and abuts against the sliding bearing 5.

With respect to the fatigue test device for the elastic support of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the sliding bearing 5 can slide along the radial direction of the rotating shaft of the motor 2 by adjusting the tightening degree of each radial displacement adjusting bolt 11 in the corresponding radial displacement adjusting hole, so as to generate radial displacement on the elastic support test piece 4.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

one end of the adapter cylinder 12 is sleeved on the turntable 10, and the other end is connected on the rotating shaft of the motor 2.

In some alternative embodiments, in the above-mentioned fatigue testing device for an aircraft engine elastic support, the turntable 10 has a protruding portion;

one end of the adapter cylinder 12, which is back to the rotating shaft of the motor 2, is sleeved on the convex part.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

a plurality of adapter bearings 13 are provided in the adapter tube 12 and are fitted to the projecting portions.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

a connecting plate 14 connected to the bracket 1 and having a connecting hole; the connecting hole is sleeved on the adapter cylinder 12 to support the adapter cylinder 12, the turntable 10 and the motor 2.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

and the simulation bearing 15 is sleeved at one end of the loading rod 3, which is opposite to the rotating shaft of the motor 2, and is arranged in the elastic support test piece 4.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

and the dynamometer 16 is connected between the piston rod of the actuating cylinder 8 and one end of the loading rod 3, which is opposite to the motor 2.

With respect to the fatigue testing device for the elastic support of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the dynamometer 16 is located between the actuator cylinder 8 and the loading rod 3, and there is no large radial force along the axial measuring path, so that the accuracy of the measurement can be ensured.

In some alternative embodiments, in the above-mentioned fatigue testing device for elastic support of an aircraft engine, the adapter 17 is connected between the piston rod of the ram 8 and the dynamometer 16.

In some optional embodiments, the above aeroengine elastic support fatigue testing apparatus further includes:

two wear-proof rings 18 are sleeved on the piston rod of the actuating cylinder 8, are positioned at the sealing part between the piston rod and the cylinder body of the actuating cylinder 8, and are symmetrically distributed at two sides of the joint bearing 9.

For the fatigue test device for the elastic support of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that, during the test, the actuator cylinder 8 can bear radial force to a certain extent, and uneven friction is generated between the sealing parts of the piston rod and the cylinder body of the actuator cylinder, so that the sealing parts between the piston rod and the cylinder body are damaged, the anti-wear rings 18 are designed between the piston rod and the cylinder body of the actuator cylinder 8, and the anti-wear rings 18 can be made of materials matched with the piston rod of the actuator cylinder 8, so as to prevent the wear between the piston rod and the cylinder body of the actuator cylinder 8, and in addition, the two anti-wear rings 18 are designed to be symmetrically distributed on two sides of the knuckle bearing 9, so that the radial force can be uniformly distributed on the two anti-wear rings 18.

The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.