Reversing loading device for reversing loading bearing test of aero-engine

Abstract

The reversing loading device for reversing loading bearing test of aero-engine belongs to the field of aero-engine main shaft bearing test. It comprises a cylinder fixing seat, a left axial loading cylinder, a right axial loading cylinder, a limiting screw, a tested bearing seat, a tested bearing fixing nut and a tested bearing inner ring cover. The left and right sides of the cylinder fixing seat are respectively provided with the left axial loading cylinder and the right axial loading cylinder. The outer side wall of the tested bearing is installed in the cylinder fixing seat through the tested bearing seat of the cylinder fixing seat. The limiting screw is threadedly connected to the cylinder fixing seat, and the bottom of the limiting screw is tightly combined with the outer side wall of the tested bearing seat. The tested bearing inner ring is provided with the tested bearing inner ring cover. The purpose is to solve the problems of lacking of a loading device which can simulate the axial load size and direction and independently and continuously change according to the test load spectrum in the existing aero-engine main shaft bearing test. The device has the technical advantages of simple structure and ingenious design.

Description

TECHNICAL FIELD

[0001] The application relates to a reversing loading device for an aero-engine reversing loading bearing test, and belongs to the field of aero-engine main shaft bearing tests. BACKGROUND

[0002] An aero-engine main shaft bearing is a key supporting component of an aero-engine, and is required to have high reliability, and needs to be subjected to simulation test examination according to various conventional and special working conditions applied to the aero-engine main bearing. A conventional aero-bearing tester simulates an axial load by only changing the load size without changing the load direction, and therefore whether the aero-engine main bearing axial load size and direction can be simulated will directly affect the effectiveness of the aero-engine main shaft bearing ground test. Therefore, aiming at the simulation test requirement of the aero-engine main shaft bearing axial load reversing test, the application provides the reversing loading device for the aero-engine reversing loading bearing test to solve the above technical problems. SUMMARY

[0003] The application is developed to solve the problems that the existing aero-engine main shaft bearing test examination lacks a real simulation of the axial load size and direction, and a loading device for independent and continuous change according to a test load spectrum. In the following, a brief overview of the application is given to provide a basic understanding of some aspects of the application. It should be understood that this overview is not an exhaustive overview of the application. It is not intended to determine the key or important parts of the application, nor to limit the scope of the application.

[0004] The technical scheme of the application is as follows:

[0005] The reversing loading device for the aero-engine reversing loading bearing test comprises a test bearing shaft end baffle, an oil cylinder fixing seat, a left axial loading oil cylinder, a right axial loading oil cylinder, a limiting screw, a test bearing seat, a test bearing fixing nut and a test bearing inner ring sleeve, the left and right sides of the oil cylinder fixing seat are respectively provided with the left axial loading oil cylinder and the right axial loading oil cylinder, the outer side wall of the test bearing is installed in the oil cylinder fixing seat through the test bearing seat, the limiting screw is threadedly connected to the oil cylinder fixing seat, and the bottom of the limiting screw is tightly attached to the outer side wall of the test bearing seat, the left side of the test bearing inner ring sleeve is fixedly connected with the test bearing inner ring, the right side of the test bearing inner ring sleeve is threadedly connected with the test bearing fixing nut, the left end surface of the test bearing fixing nut is attached to the right end surface of the test bearing, and the left side inner ring of the test bearing is provided with the test bearing shaft end baffle.

[0006] Preferably, the sealing cover and the oil injection fork are further included, the left side of the left axial loading oil cylinder is provided with the sealing cover, the oil injection fork is installed on the sealing cover, and one end of the oil injection fork penetrates into the inside of the left axial loading oil cylinder.

[0007] Preferably, the left and right axial loading oil cylinders are symmetrically fixed and installed on the left and right sides of the oil cylinder fixing seat through the oil cylinder fixing screws.

[0008] Preferably, the left axial loading oil cylinder comprises a loading oil cylinder inner cylinder, a loading piston, a cylinder cover and a loading oil cylinder outer cylinder, the left side of the loading oil cylinder outer cylinder is fixedly connected with the left side of the loading oil cylinder inner cylinder through the cylinder inner and outer ring connecting screw, the right side of the loading oil cylinder inner cylinder is arranged inside the loading oil cylinder outer cylinder, an annular oil cylinder is formed between the loading oil cylinder inner cylinder and the loading oil cylinder outer cylinder, the loading piston is installed in the annular oil cylinder, the cylinder cover is arranged on the right side of the loading piston in a fit mode, the cylinder cover is fixedly connected with the right side of the loading oil cylinder outer cylinder through the gland screw, and the inner and outer sidewalls of the loading piston are connected with the loading oil cylinder inner cylinder and the loading oil cylinder outer cylinder through the sealing structure respectively.

[0009] Preferably, a first O-shaped ring is arranged at the left connecting position of the loading oil cylinder outer cylinder and the loading oil cylinder inner cylinder.

[0010] Preferably, the sealing structure comprises a first guide belt, a first Gley ring, a second O-shaped ring, a second guide belt, a second Gley ring and a third O-shaped ring, the outer sidewalls of the loading piston and the loading oil cylinder inner cylinder are both processed with sealing installation grooves, the second O-shaped ring is arranged in the sealing installation groove of the loading piston, the first Gley ring is arranged on the outer side of the second O-shaped ring, the outer sidewall of the loading piston is connected with the inner sidewall of the loading oil cylinder outer cylinder through the first Gley ring and the first guide belt, the right end outer sidewall of the loading oil cylinder inner cylinder is processed with a sealing installation groove, the third O-shaped ring is arranged in the sealing installation groove of the loading oil cylinder inner cylinder, the second Gley ring is arranged on the outer side of the third O-shaped ring, and the right end outer sidewall of the loading oil cylinder inner cylinder is connected with the inner sidewall of the loading piston through the second Gley ring and the second guide belt.

[0011] Preferably, the loading piston is uniformly arranged with slot holes.

[0012] The application has the following beneficial effects:

[0013] 1. The large engine reversing loading bearing tester reversing loading device can simulate the dynamic axial reversing loading working condition in the reversing loading bearing test of an aero-engine, has the technical advantages of simple structure and ingenious design, and overturns the traditional one-way axial loading structure form of the bearing test mechanism.

[0014] 2. The simulated aero-engine main shaft bearing reversing loading test working condition is closer to the actual working condition, and the test result is more reliable, so that the effectiveness of the ground test of the aero-engine main shaft bearing is greatly improved. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 Fig. 1 is a structural schematic diagram of the reversing loading device for the reversing loading bearing test of the aero-engine of the present application;

[0016] Figure 2 Fig. 2 is an assembly schematic diagram of the reversing loading device for the reversing loading bearing test of the aero-engine of the present application;

[0017] Figure 3 Fig. 3 is a structural schematic diagram of the left axial loading oil cylinder of the present application;

[0018] Figure 4 Fig. 4 is a perspective view of the loading piston of the present application;

[0019] In the figure, 1 is the shaft end baffle of the test bearing, 2 is the left axial loading oil cylinder, 3 is the limiting screw, 4 is the oil cylinder fixing seat, 5 is the oil cylinder fixing screw, 6 is the right axial loading oil cylinder, 7 is the test bearing seat, 8 is the test bearing, 9 is the fixing nut, 10 is the test bearing inner ring sleeve, 11 is the loading oil cylinder body inner ring, 12 is the loading piston, 121 is the slot hole, 13 is the cylinder body gland, 14 is the gland screw, 15 is the loading oil cylinder body outer ring, 16 is the cylinder body inner and outer ring connecting screw, 17 is the first O-ring, 18 is the first guide belt, 19 is the first Gleye ring, 20 is the second O-ring, 21 is the second guide belt, 22 is the second Gleye ring, 23 is the third O-ring, 24 is the sealing cover, and 25 is the oil injection fork. DETAILED DESCRIPTION

[0020] To make the objectives, technical solutions and advantages of the present application clearer and more comprehensible, the present application will be described below through specific embodiments shown in the drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present application. In addition, in the following description, the description of the known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present application.

[0021] The connection mentioned in the present application is divided into fixed connection and detachable connection. The fixed connection, i.e. the non-detachable connection, includes but is not limited to the conventional fixed connection modes such as flange connection, rivet connection, adhesive connection and welding connection. The detachable connection includes but is not limited to the conventional detachable modes such as threaded connection, buckle connection, pin connection and hinge connection. When the specific connection mode is not explicitly limited, it is assumed that at least one connection mode can be found in the existing connection modes to achieve the function. The person skilled in the art can select as needed. For example, the fixed connection selects welding connection, and the detachable connection selects hinge connection.

[0022] Specific implementation one: combination Figures 1-4The aero-engine reversing loading bearing test reversing loading device of the embodiment comprises a cylinder fixing seat 4, a left axial loading cylinder 2, a right axial loading cylinder 6, a limiting screw 3, a test bearing seat 7, a test bearing fixing nut 9, a test bearing inner ring sleeve 10, a sealing cover 24 and an oil injection fork 25. The left axial loading cylinder 2 and the right axial loading cylinder 6 apply axial loads in different directions to the outer ring of the test bearing 8, so as to achieve the purpose of reversing loading of the test bearing 8. The left axial loading cylinder 2 and the right axial loading cylinder 6 are the same in structure and are symmetrically fixed and installed on the left and right sides of the cylinder fixing seat 4 through cylinder fixing screws 5. The outer wall of the test bearing 8 is installed in the cylinder fixing seat 4 through the test bearing seat 7. The limiting screw 3 is threadedly connected to the cylinder fixing seat 4 and tightly contacts the outer wall of the test bearing seat 7 at the bottom. The limiting screw 3 can prevent the outer ring of the test bearing 8 from rotating during the rotation of the tester spindle. The left side of the test bearing inner ring sleeve 10 is fixedly connected to the inner ring of the test bearing 8. The right side of the test bearing inner ring sleeve 10 is threadedly connected to the test bearing fixing nut 9. The left end surface of the test bearing fixing nut 9 is in contact with the right end surface of the test bearing 8. The left inner ring of the test bearing 8 is provided with a test bearing shaft end baffle 1. The test bearing shaft end baffle 1 and the test bearing fixing nut 9 are used to axially fix the test bearing 8. The test bearing seat 7 is used to fixedly install the test bearing 8. The inner side of the test bearing inner ring sleeve 10 is used to fixedly connect the inner ring of the test bearing 8 to the tester rotating spindle.

[0023] The sealing cover 24 is installed on the left side of the left axial loading cylinder 2. The oil injection fork 25 is installed on the sealing cover 24 and penetrates into the left axial loading cylinder 2. Lubricating oil is sprayed through the nozzle of the oil injection fork 25 to lubricate the test bearing 10. The sealing cover 24 seals the lubricating oil in the test cavity to prevent the lubricating oil from overflowing.

[0024] The left axial loading oil cylinder 2 comprises a loading oil cylinder inner cylinder 11, a loading piston 12, a cylinder gland 13 and a loading oil cylinder outer cylinder 15, the loading piston 12 is uniformly provided with a slot hole 121, the left side of the loading oil cylinder outer cylinder 15 is fixedly connected with the left side of the loading oil cylinder inner cylinder 11, and the right side of the loading oil cylinder inner cylinder 11 is arranged inside the loading oil cylinder outer cylinder 15, a first O-shaped ring 17 is arranged at the joint of the left side of the loading oil cylinder outer cylinder 15 and the loading oil cylinder inner cylinder 11, and the loading oil cylinder inner cylinder 11 and the loading oil cylinder outer cylinder 15 jointly constitute an annular oil cylinder which is convenient to process and disassemble through the first O-shaped ring 17, and the tight connection is ensured by a cylinder inner and outer ring connecting screw (16), the loading piston 12 is arranged in the annular oil cylinder, the cylinder gland 13 is arranged on the right side of the loading piston 12, the cylinder gland 13 is fixedly connected with the right side of the loading oil cylinder outer cylinder 15 through a gland screw 14, the loading piston 12 is limited, and the inner and outer side walls of the loading piston 12 are connected with the loading oil cylinder inner cylinder 11 and the loading oil cylinder outer cylinder 15 through sealing structures respectively.

[0025] The sealing structure comprises a first guide belt 18, a first Gley ring 19, a second O-shaped ring 20, a second guide belt 21, a second Gley ring 22 and a third O-shaped ring 23, the outer side walls of the loading piston 12 and the loading oil cylinder inner cylinder 11 are all provided with sealing installation grooves, the second O-shaped ring 20 is arranged in the sealing installation groove of the loading piston 12, the first Gley ring 19 is arranged on the outer side of the second O-shaped ring 20, the outer side walls of the loading piston 12 are connected with the inner side wall of the loading oil cylinder outer cylinder 15 through the first Gley ring 19 and the first guide belt 18, the right end outer side walls of the loading oil cylinder inner cylinder 11 are all provided with sealing installation grooves, the third O-shaped ring 23 is arranged in the sealing installation groove of the loading oil cylinder inner cylinder 11, the second Gley ring 22 is arranged on the outer side of the third O-shaped ring 23, and the right end outer side walls of the loading oil cylinder inner cylinder 11 are connected with the inner side wall of the loading piston 12 through the second Gley ring 22 and the second guide belt 21. The loading piston 12 with the slot hole 121 is arranged in the annular oil cylinder, is guided and sealed through the first guide belt 18, the first Gley ring 19, the second O-shaped ring 20, the second guide belt 21, the second Gley ring 22 and the third O-shaped ring 23, and the uniformly arranged slot holes 121 of the loading piston 12 can smoothly discharge the lubricating oil of the test bearing 8 while ensuring uniform loading.

[0026] In combination Figure 1 , the assembled left axial loading oil cylinder 2 and right axial loading oil cylinder 6 are fixed on the two sides of the cylinder fixing seat 4 through screws, when the left axial loading oil cylinder 2 is filled with hydraulic oil, the hydraulic pipeline of the right axial loading oil cylinder 6 is opened, and the loading piston 12 of the left axial loading oil cylinder 2 is in contact with the left side of the outer ring of the test bearing 8, so that the axial loading to the right is realized.

[0027] When the right axial loading oil cylinder 6 is supplied with hydraulic oil, the hydraulic pipeline of the left axial loading oil cylinder 2 opens the pressure relief valve, and the loading piston 12 of the right axial loading oil cylinder 6 will be in contact with the right side of the outer ring of the test bearing 8, thereby realizing the left axial loading.

[0028] While the axial loading is being performed, the limiting screw 3 can prevent the outer ring of the test bearing 8 from rotating during the rotation of the tester spindle. The hydraulic oil entering and discharging of the left axial loading oil cylinder 2 and the right axial loading oil cylinder 6 will be controlled by the control system, so as to realize the requirements of the axial load test spectrum line of the aero-engine spindle bearing.

[0029] It should be noted that the terms "first", "second", and the like in the description and claims of the application and the above drawings are used to distinguish similar objects, and do not necessarily have to describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the application described herein can be implemented in an order other than that illustrated or described herein.

[0030] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities according to the mathematical knowledge of arrangement and combination, so the application will not be described one by one for the technical solutions after arrangement and combination, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the application.

[0031] The above only describes the preferred embodiments of the application and is not intended to limit the application. For those skilled in the art, the application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the application shall be included in the protection scope of the application.

Claims

1. A reversing loading device for bearing testing in aero-engines, characterized in that: The test bearing assembly includes a bearing end plate (1), a cylinder mounting base (4), a left axial loading cylinder (2), a right axial loading cylinder (6), a limit screw (3), a bearing housing (7), a bearing fixing nut (9), and an inner ring (10). The left axial loading cylinder (2) and the right axial loading cylinder (6) are respectively mounted on the left and right sides of the cylinder mounting base (4). The outer wall of the bearing under test (8) is mounted inside the cylinder mounting base (4) via the bearing housing (7). The limit screw (3) 3) The threaded part is fitted on the cylinder mounting base (4), and the bottom passes through the cylinder mounting base (4) and is tightly fitted to the outer wall of the bearing housing (7) under test. The left side of the inner ring sleeve (10) of the bearing under test is fixedly connected to the inner ring of the bearing under test (8). The right side of the inner ring sleeve (10) of the bearing under test is threadedly fitted to the bearing fixing nut (9) of the bearing under test. The left end face of the bearing fixing nut (9) of the bearing under test is fitted to the right end face of the bearing under test (8). The left inner ring of the bearing under test (8) is fitted with the bearing shaft end baffle (1).

2. The reversing loading device for testing reversing loading bearings in aero-engines according to claim 1, characterized in that: It also includes a sealing cover (24) and an injection fork (25). The sealing cover (24) is installed on the left side of the left axial loading cylinder (2), and the injection fork (25) is installed on the sealing cover (24) with one end protruding into the left axial loading cylinder (2).

3. The reversing loading device for testing reversing load bearings in aero-engines according to claim 2, characterized in that: The left axial loading cylinder (2) and the right axial loading cylinder (6) have the same structure and are symmetrically fixed on the left and right sides of the cylinder mounting base (4) by cylinder fixing screws (5).

4. The reversing loading device for testing reversing load bearings in aero-engines according to claim 3, characterized in that: The left-axis loading cylinder (2) includes an inner ring (11) of the loading cylinder, a loading piston (12), a cylinder cover (13) and an outer ring (15) of the loading cylinder. The left side of the outer ring (15) of the loading cylinder is fixedly connected to the left side of the inner ring (11) of the loading cylinder by a cylinder inner and outer ring connecting screw (16). At the same time, the right side of the inner ring (11) of the loading cylinder is placed inside the outer ring (15) of the loading cylinder. An annular cylinder is formed between the inner ring (11) and the outer ring (15) of the loading cylinder. The loading piston (12) is installed inside the annular cylinder. The cylinder cover (13) is fitted to the right side of the loading piston (12). The cylinder cover (13) is fixedly connected to the right side of the outer ring (15) of the loading cylinder by a cover screw (14). The inner and outer side walls of the loading piston (12) are connected to the inner ring (11) and the outer ring (15) of the loading cylinder by a sealing structure.

5. The reversing loading device for testing reversing load bearings in aero-engines according to claim 4, characterized in that: A first O-ring (17) is provided at the left connection between the outer ring (15) of the loading cylinder and the inner ring (11) of the loading cylinder.

6. The reversing loading device for testing reversing load bearings in aero-engines according to claim 4, characterized in that: The sealing structure includes a first guide band (18), a first Glyd ring (19), a second O-ring (20), a second guide band (21), a second Glyd ring (22), and a third O-ring (23). Sealing mounting grooves are machined on the outer walls of both the loading piston (12) and the inner ring (11) of the loading cylinder. A second O-ring (20) is placed in the sealing mounting groove on the loading piston (12), and a first Glyd ring (19) is positioned on the outer side of the second O-ring (20). The outer wall of the loading piston (12) is traversed by the first Glyd ring (19). The first guide band (18) and the inner wall of the outer ring (15) of the loading cylinder are sealed together. The outer wall of the right end of the inner ring (11) of the loading cylinder is machined with a sealing installation groove. The third O-ring (23) is placed in the sealing installation groove of the inner ring (11) of the loading cylinder. The second Glyd ring (22) is set on the outside of the third O-ring (23). The outer wall of the right end of the inner ring (11) of the loading cylinder is sealed together with the inner wall of the loading piston (12) through the second Glyd ring (22) and the second guide band (21).

7. The reversing loading device for testing reversing load bearings in aero-engines according to claim 6, characterized in that: The loading piston (12) has slots (121) evenly arranged on it.

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