Driving auxiliary device for dynamic balance test of aero-engine rotor

Abstract

The invention relates to the field of aero-engine rotor balance tests, in particular to an aero-engine rotor dynamic balance test driving auxiliary device which comprises a supporting mechanism, and a supporting rod structure, an airflow driving mechanism and a driving auxiliary mechanism are arranged above the supporting mechanism. The supporting rod structure is used for supporting the airflow driving mechanism and the driving auxiliary mechanism; the airflow driving mechanism is used for outputting compressed air; and the driving auxiliary mechanism is used for adjusting the position of the airflow driving mechanism on the supporting rod structure, so that the aeroengine rotor balance test auxiliary device which is driven by compressed air, portable, adjustable in position in all directions and controllable in air pressure and airflow flexibility is provided. The influence of vibration generated by the mode that the motor, the belt and the engine rotor are connected on the dynamic balance test of the engine rotor is avoided.

Description

Technical Field

[0001] The invention relates to the field of aero-engine rotor balancing test, and in particular to a driving auxiliary device for aero-engine rotor dynamic balancing test. Background Art

[0002] When the residual imbalance of the rotor exceeds the design requirements during operation, it will cause excessive vibration of the aircraft engine, accelerate bearing wear, increase noise, shorten mechanical life, and directly affect its working performance and service life. Therefore, during the assembly process of the aircraft engine, its rotor needs to be dynamically balanced. In the traditional dynamic evaluation test of aircraft engine rotors, the engine is fixed on the base, connected to the engine rotor through a motor and a belt, and the motor is used to drive the rotor to rotate for dynamic balancing test. This method has great deficiencies for the dynamic balancing test of small engine rotors used in drones: the mode of connecting the motor, belt and engine rotor will generate certain vibrations when working. For large-thrust aircraft engines, due to their heavy weight, the impact of this vibration can be ignored, but due to the small-thrust aircraft engines used in drones, due to their light weight, it is enough to cause distortion of the rotor balance test. Summary of the invention

[0003] In view of the above problems, the present invention provides a drive auxiliary device for a dynamic balancing test of an aircraft engine rotor.

[0004] The adopted technical solution is a driving auxiliary device for dynamic balancing test of aircraft engine rotor, comprising a supporting mechanism, wherein a supporting rod structure, an airflow driving mechanism and a driving auxiliary mechanism are arranged above the supporting mechanism; The support rod structure is used to support the airflow driving mechanism and the driving auxiliary mechanism; The airflow driving mechanism is used to output compressed air; The drive auxiliary mechanism is used to adjust the position of the airflow drive mechanism on the support rod structure.

[0005] Optionally, the support mechanism includes a T-bolt, a flat washer, a hexagonal nut and a mounting base; The straight section of the T-bolt passes through the mounting seat and the flat washer in sequence, and the horizontal section of the T-bolt can contact the supporting surface; The hexagonal nut can be sleeved on the straight section of the T-bolt.

[0006] Optionally, the mounting seat is in a T-shaped structure, the horizontal section of the mounting seat faces the supporting surface, and the vertical section of the mounting seat is connected to the supporting rod structure.

[0007] Optionally, the support rod structure includes a round tube, and the bottom of the round tube is connected to the support mechanism.

[0008] Optionally, the air flow driving mechanism includes a P-type quick connector, a PU air pipe, an SM-type quick connector, a three-piece internally threaded ball valve, and a universal cooling pipe; The universal cooling pipe is connected to the auxiliary driving mechanism, one end of the universal cooling pipe is connected to the air supply structure, and the other end of the universal cooling pipe is connected to one end of the three-piece internal thread ball valve; The other end of the three-piece internal thread ball valve is connected to one end of the SM type quick connector; The other end of the SM-type quick connector is connected to one end of the P-type quick connector; The other end of the P-type quick connector is connected to one end of the PU air pipe; The other end of the PU air pipe faces the engine rotor.

[0009] Optionally, a combined gasket is further provided between the SM-type quick connector and the three-piece internally threaded ball valve.

[0010] Optionally, the other end of the PU air pipe is also connected to a P-type quick connector.

[0011] Optionally, the drive assist mechanism includes a star nut, a clamp and a sleeve; The clip is sleeved on the support rod structure; The star nut is arranged on one side of the clamp and is used to fix the clamp and the support rod structure; The sleeve is arranged on the other side of the clip, and the airflow driving mechanism can pass through the sleeve.

[0012] Optionally, the star nut is connected to the clamp through the spherical washer.

[0013] Optionally, the sleeve is provided with fixing bolts for fixing the airflow driving mechanism.

[0014] The beneficial effects of the present invention are: 1. Avoid the influence of vibration generated by the connection mode between the motor, belt and engine rotor on the dynamic balance test of the engine rotor; 2. The driving force can be flexibly adjusted by controlling the air pressure and airflow of compressed air through a three-piece internal threaded ball valve; 3. The whole device is easy to move, can be fully adjusted, simple to assemble and disassemble, and convenient to transport and store. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 The schematic diagram of the structure of a driving auxiliary device for dynamic balancing test of an aircraft engine rotor is shown in FIG. Figure 2 A schematic side view of a drive auxiliary device for a dynamic balancing test of an aircraft engine rotor; Figure 3 It is a three-dimensional schematic diagram of a drive auxiliary device for a dynamic balancing test of an aircraft engine rotor.

[0016] The accompanying drawings are marked as follows: 1 is a T-bolt, 2 is a flat washer, 3 is a hexagonal nut, 4 is a mounting seat, 5 is a round tube, 6 is a universal cooling tube, 7 is a three-piece internal thread ball valve, 8 is a combination washer, 9 is an SM type quick connector, 10 is a P type quick connector, 11 is a PU air pipe, 12 is a star nut, 13 is a spherical washer, 14 is a clip, 15 is a sleeve, and 16 is a fixing bolt. DETAILED DESCRIPTION

[0017] The following describes the implementation of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific implementations, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0018] It should be noted that the illustrations provided in the following embodiments are only used to schematically illustrate the basic concept of the present invention, and thus the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0019] like Figure 1 and Figure 3 As shown, a driving auxiliary device for a dynamic balancing test of an aircraft engine rotor comprises a supporting mechanism, wherein a supporting rod structure, an airflow driving mechanism and a driving auxiliary mechanism are arranged above the supporting mechanism; The support rod structure is used to support the airflow driving mechanism and the driving auxiliary mechanism; The airflow driving mechanism is used to output compressed air; The drive auxiliary mechanism is used to adjust the position of the airflow drive mechanism on the support rod structure.

[0020] The purpose of this design is to provide an aircraft engine rotor balancing test auxiliary device that is driven by compressed air, portable, fully adjustable in position, and flexibly controllable in air pressure and airflow, so as to avoid the influence of vibration generated by the connection mode between the motor, belt and engine rotor on the engine rotor dynamic balancing test.

[0021] In this embodiment, the support mechanism includes a T-bolt 1, a flat washer 2, a hexagonal nut 3 and a mounting seat 4; The straight section of the T-bolt 1 passes through the mounting seat 4 and the flat washer 2 in sequence, and the horizontal section of the T-bolt 1 can contact the supporting surface; The hexagonal nut 3 can be sleeved on the straight section of the T-bolt 1 .

[0022] Meanwhile, the mounting seat 4 is in a T-shaped structure, the horizontal section of the mounting seat 4 faces the supporting surface, and the vertical section of the mounting seat 4 is connected to the supporting rod structure.

[0023] The purpose of this design is, on the one hand, to provide necessary support for the entire device through the setting of the mounting base, thereby preventing it from shaking during use; on the other hand, by setting T-bolts, and usually an even number of T-bolts, it is convenient for symmetrical setting, and the user can adjust the height of the entire mounting base with hexagonal nuts to meet the needs of various scenarios.

[0024] Meanwhile, in this embodiment, the support rod structure includes a circular tube 5, and the bottom of the circular tube 5 is connected to the support mechanism.

[0025] Meanwhile, in this embodiment, the airflow driving mechanism includes a P-type quick connector 10, a PU air pipe 11, an SM-type quick connector 9, a three-piece internally threaded ball valve 7 and a universal cooling pipe 6; The universal cooling pipe 6 is connected to the drive auxiliary mechanism, one end of the universal cooling pipe 6 faces the engine rotor, and the other end of the universal cooling pipe 6 is connected to one end of a three-piece internally threaded ball valve 7; The other end of the three-piece internal thread ball valve 7 is connected to one end of the SM type quick connector 9; The other end of the SM type quick connector 9 is connected to one end of the P type quick connector 10; The other end of the P-type quick connector 10 is connected to one end of the PU air pipe 11; The other end of the PU air pipe 11 is connected to the air supply mechanism; A combined gasket 8 is also provided between the SM-type quick connector 9 and the three-piece internally threaded ball valve 7 , and a P-type quick connector 10 is also connected to the other end of the PU air pipe 11 .

[0026] The purpose of this design is to achieve flexible adjustment of the driving force by controlling the air pressure and airflow of the compressed air through a three-piece internally threaded ball valve.

[0027] Meanwhile, it should be pointed out that the air supply mechanism referred to in this embodiment may be an air pipe for providing compressed air.

[0028] like Figure 2 As shown, the drive assist mechanism includes a star nut 12, a clamp 14 and a sleeve 15; The clip 14 is sleeved on the support rod structure; The star nut 12 is disposed on one side of the clip 14 and is used to fix the clip 14 and the support rod structure; The sleeve 15 is disposed on the other side of the clip 14, and the airflow driving mechanism can pass through the sleeve 15; The star nut 12 passes through the spherical washer 13 and is connected to the clamp 14 . The sleeve 15 is provided with a fixing bolt 16 for fixing the airflow driving mechanism.

[0029] In this embodiment, based on the above structure, an operation step of performing a dynamic balancing test of an aircraft engine rotor is provided as follows: S1, P-type quick connector 10 is connected to an external air pipe that can provide compressed air; S2, move the mounting seat 4 to a suitable position; S3, adjusting the star nut 12 and the universal cooling pipe 6 so that they are aligned with the aircraft engine air intake; S4, rotating the three-piece internal thread ball valve 7 to control the air pressure and airflow of the compressed air to the working requirements, driving the engine rotor to rotate; S5. Carry out rotor dynamic balancing test.

[0030] The purpose of this design is to use pneumatic drive to avoid the influence of vibration generated by the traditional mode of connecting motors, belts and engine rotors on the dynamic balancing test of the engine rotor; the use of a three-piece internally threaded ball valve to control the air pressure and airflow of compressed air can achieve flexible adjustment of the driving force; the entire device is easy to move, can be adjusted in all positions, is simple to assemble and disassemble, and is convenient to transport and store.

[0031] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A drive auxiliary device for a dynamic balancing test of an aircraft engine rotor, comprising a support mechanism, characterized in that: A support rod structure, an airflow driving mechanism and a driving auxiliary mechanism are arranged above the support mechanism; The support rod structure is used to support the airflow driving mechanism and the driving auxiliary mechanism; The airflow driving mechanism is used to output compressed air; The drive auxiliary mechanism is used to adjust the position of the airflow drive mechanism on the support rod structure.

2. The driving auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 1, characterized in that: The support mechanism comprises a T-bolt (1), a flat washer (2), a hexagonal nut (3) and a mounting seat (4); The straight section of the T-bolt (1) passes through the mounting seat (4) and the flat washer (2) in sequence, and the horizontal section of the T-bolt (1) can contact the supporting surface; The hexagonal nut (3) can be sleeved on the straight section of the T-bolt (1).

3. The driving auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 2, characterized in that: The mounting seat (4) is in a T-shaped structure, the horizontal section of the mounting seat (4) faces the support surface, and the vertical section of the mounting seat (4) is connected to the support rod structure.

4. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 1, characterized in that: The support rod structure comprises a circular tube (5), the bottom of the circular tube (5) being connected to a support mechanism.

5. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 1, characterized in that: The airflow driving mechanism comprises a P-type quick connector (10), a PU air pipe (11), an SM-type quick connector (9), a three-piece internally threaded ball valve (7) and a universal cooling pipe (6); The universal cooling pipe (6) is connected to the auxiliary driving mechanism, one end of the universal cooling pipe (6) faces the engine rotor, and the other end of the universal cooling pipe (6) is connected to one end of a three-piece internally threaded ball valve (7); The other end of the three-piece internally threaded ball valve (7) is connected to one end of an SM-type quick connector (9); The other end of the SM-type quick connector (9) is connected to one end of the P-type quick connector (10); The other end of the P-type quick connector (10) is connected to one end of the PU air pipe (11); The other end of the PU air pipe (11) is connected to an air supply mechanism.

6. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 5, characterized in that: A combined gasket (8) is also provided between the SM-type quick connector (9) and the three-piece internally threaded ball valve (7).

7. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 5, characterized in that: The other end of the PU air pipe (11) is also connected to a P-type quick connector (10).

8. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 1, characterized in that: The auxiliary drive mechanism comprises a star nut (12), a clamp (14) and a sleeve (15); The clip (14) is sleeved on the support rod structure; The star-shaped nut (12) is arranged on one side of the clamp (14) and is used to fix the clamp (14) and the support rod structure; The sleeve (15) is arranged on the other side of the clip (14), and the airflow driving mechanism can pass through the sleeve (15).

9. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 8, characterized in that: The star nut (12) passes through the spherical washer (13) and is connected to the clamp (14).

10. The drive auxiliary device for the dynamic balancing test of an aircraft engine rotor according to claim 8, characterized in that: The sleeve (15) is provided with a fixing bolt (16) for fixing the airflow driving mechanism.

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