Balancing method for gas generator rotor with stator components of aircraft engines

Abstract

The invention discloses a balancing device and method for a gas generator rotor with a stator component of an aircraft engine, comprising a rotating fixture at the bottom, a gas generator rotor assembly being clamped in the rotating fixture, a radial detection assembly being sleeved on the gas generator rotor assembly, an axial detection assembly being mounted on the radial detection assembly, the radial detection assembly comprising a base, an annular plate being fixed inside the base, nozzles being evenly fixed on the inner wall of the annular plate, and the nozzles being located on the outer side of the gas generator rotor assembly. The invention improves the assembly quality of the gas generator rotor, so that the unbalance amount of the gas generator rotor meets the requirements during actual operation, and increases the rotation speed of the sleeve by generating an air film between the sleeve and the throttle in the rotating fixture, so that the rotation speed of the gas generator rotor during dynamic balancing is close to the actual working rotation speed, thereby making the dynamic balancing amount meet the use requirements.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine engines or ground gas turbines, in particular to a balancing method for a gas generator rotor with a stator component of an aero-engine. Background Art

[0002] When assembling an aircraft engine, the rotor components need to be balanced to prevent vibration during operation from causing unpredictable damage to the aircraft engine structure. The gas generator rotor is an important rotating component of an aircraft engine, and its function is to provide power for the operation of the aircraft engine. The gas generator rotor is mainly composed of a compressor rotor and a gas turbine rotor. The two are positioned by arc end teeth, and there is an interference fit between the gas turbine rotor and the compressor shaft. In the early days, the traditional method only balanced the assembled gas generator rotor, marked it after the balance was qualified, disassembled the gas generator rotor, and directly installed the stator components on the gas generator rotor that was reinstalled in place according to the mark, and continued the subsequent assembly work. The stator components have a certain influence on the balance of the gas generator rotor. The traditional balancing method fails to detect the imbalance of the gas generator rotor in actual operation, which makes it easy for the imbalance of the gas generator rotor actually installed to not meet the requirements.

[0003] At the same time, the existing balance detection device has a limited rotation speed and cannot approach the rotation speed of the engine when it is actually working. In this way, when it is actually working, the rotor is prone to vibrate beyond the limit, affecting the reliability of the engine. Summary of the invention

[0004] The object of the present invention is to provide a balancing method for a gas generator rotor with a stator component of an aircraft engine, which is used to improve the assembly quality of the gas generator rotor and make the unbalance amount of the gas generator rotor meet the requirements during actual operation.

[0005] The present invention provides the following technical solution: a method for balancing a gas generator rotor with a stator component of an aircraft engine, comprising a gas generator rotor assembly with a stator component and a gas generator rotor balancing device with a stator component for an aircraft engine, wherein the gas generator rotor assembly comprises an impeller cover, a compressor rotor, a gas turbine rotor, a double comb teeth and a bearing arranged in sequence, a gas turbine guide is fixed to the outer end of the gas turbine rotor, a diffuser and a compressor casing are fixed in sequence on one side of the gas turbine guide on the outer side of the compressor rotor, and an air intake casing is fixed to one end of the compressor casing;

[0006] The gas generator rotor balancing device is used to clamp the gas generator rotor assembly for radial and axial testing;

[0007] The gas generator rotor balancing device comprises a rotating fixture at the bottom, a gas generator rotor assembly is clamped in the rotating fixture, a radial detection assembly is sleeved on the gas generator rotor assembly, and an axial detection assembly is installed on the radial detection assembly;

[0008] The radial detection assembly includes a base, an annular plate is fixed inside the base, nozzles are evenly fixed on the inner wall of the annular plate, the nozzles are located on the outside of the gas generator rotor assembly, an air inlet and an air outlet are opened on the side wall of the base, the air outlet is connected with the annular plate to form an exhaust channel, an annular channel is formed between the base and the annular plate, a flange is fixed on the upper end of the base, a cover plate is fixed on the upper end of the flange, an air pressure sensor is installed on the inner side of the nozzle, a mesh is fixed inside the annular plate, and the mesh is located inside the air pressure sensor;

[0009] The rotating fixture comprises a shell, a throttle is fixed inside the shell, and an air inlet connected to the throttle is opened on the outer wall of the shell;

[0010] The axial detection assembly includes a bracket, a tension sensor is fixed at the lower end of the bracket, a counterweight is connected to the lower end of the tension sensor through a spring, and the counterweight is located at the upper end of the gas generator rotor assembly;

[0011] The balancing steps are as follows:

[0012] S1. Clamp the tooling on one side of the gas generator rotor assembly by rotating the fixture, and then sleeve the radial detection assembly on the upper end of the gas generator rotor assembly, and connect the axial detection assembly to the radial detection assembly;

[0013] S2. Compressed air is introduced into the air inlet of the rotating fixture and the inlet of the radial detection component, and the power is turned on to enable the rotating fixture and the radial detection component to rotate at high speed;

[0014] S3, detecting the real-time air pressure of the nozzle through the air pressure sensor, and determining the radial runout of the gas generator rotor assembly according to the change amplitude of the air pressure. When the radial displacement of the rotor approaches the nozzle, the air pressure of the nozzle will change;

[0015] S4. The axial jump of the gas generator rotor assembly is performed by following the axial jump of the gas generator rotor assembly through the counterweight block at the upper end of the gas generator rotor assembly. In this way, the counterweight block will jump up and down, thereby affecting the tension of the tension sensor. The axial jump of the gas generator rotor assembly can be determined according to the variation of the tension.

[0016] According to the above solution, the upper and lower ends of the gas generator rotor assembly are respectively connected to an upper tooling and a lower tooling, the upper tooling is connected to the radial detection assembly, and the lower tooling is connected to the rotating fixture.

[0017] According to the above scheme, a shaft sleeve is provided on the inner side of the throttle, a top plate is fixed on the shaft sleeve on the upper side of the throttle, an air film channel exists between the top and the shaft sleeve and the throttle, the air inlet is connected to the air film channel, a motor is fixed between the shaft sleeve and the bottom end of the shell, the motor includes a rotor and a stator, the rotor is fixed on the outer wall of the shaft sleeve, the stator is fixed on the inner wall of the shell, and a grating is fixed on the bottom of the rotor.

[0018] According to the above solution, an air channel is opened in the throttle, and the air channel is connected to the air inlet, and the air channel is also connected to the air film channel outside the throttle.

[0019] According to the above scheme, there are at least two tension sensors, one of which is fixed above the outer edge of the gas generator rotor assembly, and the other is fixed above the center of the rotating shaft of the gas generator rotor assembly. The number of the counterweight blocks corresponds to the number of tension sensors.

[0020] According to the above scheme, in S3, the outlet is first closed, and compressed air is introduced into the inlet to make a certain air pressure between the annular plate and the base, and then the flow rate of the inlet is reduced and the outlet is opened to keep the air pressure between the annular plate and the base and the air pressure inside the annular plate constant. When the gas generator rotor assembly undergoes radial runout, the gas generator rotor assembly will approach the air pressure sensor, so that the air pressure of the air pressure sensor will change;

[0021] The air pressure value of the air pressure sensor is recorded in real time, and the position of the radial imbalance point of the rotor on the rotor can be determined according to the time point of the air pressure change and the speed of the rotor;

[0022] In S4, the weight change of the counterweight block on the gas generator rotor assembly is detected by a tension sensor, and the axial runout amplitude can be determined according to the weight change. At the same time, the position of the axial runout can be determined according to the runout amplitude of the edge and center of the gas generator rotor assembly.

[0023] Compared with the prior art, the beneficial effects achieved by the present invention are:

[0024] (1) By fixing the stator components on the gas generator rotor for dynamic balancing testing, the stator components do not need to be disassembled, which effectively shortens the assembly time of the aircraft engine, improves the assembly quality of the aircraft engine, reduces the incidence of vibration failures of the aircraft engine, and greatly improves the reliability of the aircraft engine;

[0025] (2) Through the rotation of the gas generator rotor in the annular plate, when the rotation of the gas generator rotor is unbalanced, the detected air pressure of the air pressure sensor will increase when the rotor approaches the air pressure sensor. The greater the radial runout, the greater the air pressure change. The radial imbalance of the rotor is indirectly determined by the change in air pressure.

[0026] (3) The radial imbalance of the rotor is detected by a radial detection component, and compressed air is introduced between the base and the annular plate so that the gas generator rotor in the annular plate is surrounded by the compressed air, thereby reducing the contact area between the gas generator rotor and the annular plate and reducing the friction between the two;

[0027] (4) By generating an air film between the sleeve and the throttle in the rotating fixture, the rotation speed of the sleeve is increased and the energy loss is reduced. When the gas generator rotor is dynamically balanced, it can be simulated according to the operating speed of the gas generator rotor to avoid the speed being too low during dynamic balancing, which may cause the rotor to vibrate beyond the limit during actual operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0029] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0030] Figure 2 is an internal structural diagram of the radial detection assembly of the present invention;

[0031] In the figure: 1. rotating fixture; 11. shell; 12. sleeve; 13. throttle; 14. top plate; 15. air inlet; 16. stator; 17. rotor; 18. grating; 2. gas generator rotor assembly; 21. air inlet casing; 22. impeller cover; 23. compressor rotor; 24. compressor casing; 25. diffuser; 26. gas turbine guide; 27. gas turbine rotor; 28. double comb teeth; 29. ​​bearing; 3. radial detection assembly; 31. base; 311. outlet; 312. inlet; 32. annular plate; 321. nozzle; 33. mesh; 34. flange; 35. cover plate; 36. air pressure sensor; 4. upper tooling; 5. lower tooling; 6. axial detection assembly; 61. tension sensor; 62. counterweight; 63. bracket. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] See also Figure 1The present invention provides a technical solution: a method for balancing a gas generator rotor with a stator component of an aircraft engine, comprising a gas generator rotor assembly 2 with a stator component and a gas generator rotor balancing device with a stator component for an aircraft engine, wherein the gas generator rotor assembly 2 comprises an impeller cover 22, a compressor rotor 23, a gas turbine rotor 27, a double comb teeth 28 and a bearing 29 which are arranged in sequence, a gas turbine guide 26 is fixed to the outer end of the gas turbine rotor 27, a diffuser 25 and a compressor casing 24 are fixed to one side of the gas turbine guide 26 on the outer side of the compressor rotor 23 in sequence, and an air intake casing 21 is fixed to one end of the compressor casing 24;

[0034] The gas generator rotor balancing device is used to clamp the gas generator rotor assembly 2 for radial and axial testing;

[0035] The gas generator rotor balancing device comprises a rotating fixture 1 at the bottom, a gas generator rotor assembly 2 is clamped in the rotating fixture 1, a radial detection assembly 3 is sleeved on the gas generator rotor assembly 2, an axial detection assembly 6 is installed on the radial detection assembly 3, the gas generator rotor assembly 2 is clamped by the rotating fixture 1, the rotating fixture 1 drives the gas generator rotor assembly 2 to rotate, the rotation speed of the rotating fixture 1 is close to the actual rotation speed during operation, and the imbalance amount of the gas generator rotor assembly 2 is detected by using the axial detection assembly 6 and the radial detection assembly 3;

[0036] like Figure 2As shown, the radial detection assembly 3 includes a base 31, an annular plate 32 is fixed inside the base 31, nozzles 321 are evenly fixed on the inner wall of the annular plate 32, the nozzles 321 are located on the outside of the gas generator rotor assembly 2, an air inlet 312 and an air outlet 311 are opened on the side wall of the base 31, the air outlet 311 is connected with the annular plate 32 to form an exhaust channel, an annular channel is formed between the base 31 and the annular plate 32, a flange 34 is fixed on the upper end of the base 31, a cover plate 35 is fixed on the upper end of the flange 34, an air pressure sensor 36 is installed on the inner side of the nozzle 321, a mesh 33 is fixed inside the annular plate 32, the mesh 33 is located on the inner side of the air pressure sensor 36, the mesh 33 can protect the air pressure sensor 36 to prevent the gas generator rotor assembly 2 from touching the air pressure sensor 36, The base 31 is a cylindrical shell. Compressed air enters from the air inlet 312 and passes through the annular channel between the base 31 and the annular plate 32. The compressed air in the annular channel then enters the inside of the annular plate 32 through the nozzle 321. The annular plate 32 is sleeved with the gas generator rotor assembly 2. The compressed air forms an air film between the annular plate 32 and the gas generator rotor assembly 2. The rotor is supported by the air film. At the same time, the air is used as a lubricant to reduce the friction between the rotor and the rotor, thereby increasing the rotation speed of the rotor. When the gas generator rotor assembly 2 is unbalanced under high-speed rotation, the gas generator rotor assembly 2 will approach the air pressure sensor 36, increase the air pressure of the air pressure sensor 36, and thus detect the radial imbalance of the gas generator rotor assembly 2 according to the air pressure change amplitude of the air pressure sensor 36.

[0037] The rotating fixture 1 comprises a housing 11, a throttle 13 is fixed inside the housing 11, and an air inlet 15 connected to the throttle 13 is formed on the outer wall of the housing 11;

[0038] The axial detection assembly 6 includes a bracket 63, a tension sensor 61 is fixed to the lower end of the bracket 63, a counterweight 62 is connected to the lower end of the tension sensor 61 through a spring, the counterweight 62 is located at the upper end of the gas generator rotor assembly 2, the tension sensor 61 is used to perform tension detection on the counterweight 62, and the counterweight 62 is located at the upper end of the gas generator rotor assembly 2, the counterweight 62 can follow the axial jump of the gas generator rotor assembly 2, and the variation of the tension can determine the axial imbalance of the gas generator rotor assembly 2;

[0039] Rotor balancing steps:

[0040] S1. Clamp the tooling on one side of the gas generator rotor assembly 2 by rotating the fixture, and then sleeve the radial detection assembly on the upper end of the gas generator rotor assembly, and connect the axial detection assembly to the radial detection assembly;

[0041] S2. Compressed air is introduced into the air inlet of the rotating fixture and the inlet of the radial detection component, and the power is turned on to enable the rotating fixture and the radial detection component to rotate at high speed;

[0042] S3, detecting the real-time air pressure of the nozzle 321 through the air pressure sensor 36, and determining the radial runout of the gas generator rotor assembly 2 according to the change amplitude of the air pressure. When the rotor radially deviates close to the nozzle 321, the air pressure of the nozzle 321 will change;

[0043] S4. The counterweight block 62 follows the gas generator rotor assembly to perform axial jump at the upper end of the gas generator rotor assembly 2, so that the counterweight block 62 will jump up and down, thereby affecting the tension of the tension sensor 61. The axial jump of the gas generator rotor assembly 2 can be determined according to the variation of the tension.

[0044] The upper and lower ends of the gas generator rotor assembly 2 are respectively connected to the upper tooling 4 and the lower tooling 5, the upper tooling 4 is connected to the radial detection assembly 3, and the lower tooling 5 is connected to the rotating fixture 1. The gas generator rotor assembly 2 is fixed and installed between the rotating fixture 1 and the radial detection assembly 3 through the upper tooling 4 and the lower tooling 5.

[0045] A shaft sleeve 12 is arranged inside the throttle 13, a top plate 14 is fixed on the shaft sleeve 12 on the upper side of the throttle 13, an air film channel exists between the top plate 14, the shaft sleeve 12 and the throttle 13, an air inlet 15 is connected to the air film channel, a motor is fixed between the shaft sleeve 12 and the bottom end of the housing 11, the motor includes a rotor 17 and a stator 16, the rotor 17 is fixed on the outer wall of the shaft sleeve 12, the stator 16 is fixed on the inner wall of the housing 11, a grating 18 is fixed on the bottom of the rotor 17, and compressed air enters the throttle 1 from the air inlet 15 on the outer wall of the housing 11 3, and after the compressed air flows out of the throttle 13 and enters the air film channel between the top plate 14 and the shaft sleeve 12 and the throttle 13, the friction between the top plate 14 and the shaft sleeve 12 and the throttle 13 is reduced, and the rotor 17 drives the shaft sleeve 12 to rotate, the top plate 14 is fixed on the shaft sleeve 12, and the gas generator rotor assembly 2 is fixed between the shaft sleeves 12. The gas generator rotor assembly 2 can rotate with the shaft sleeve 12, and the friction between the shaft sleeve 12 and the throttle 13 is reduced by the air film, so that the gas generator rotor assembly 2 can rotate at a high speed.

[0046] An air channel is opened in the throttle 13, and the air channel is connected to the air inlet 15. The air channel is also connected to the air film channel outside the throttle 13. Compressed air enters the air channel in the throttle 13, and then flows into the air film channel from the air channel to generate an air film, thereby reducing the friction between the sleeve 12 and the throttle 13.

[0047] In S3, the outlet 311 is closed first, and compressed air is introduced into the inlet 312 to make a certain air pressure between the annular plate 32 and the base 31, and the flow rate of the inlet 312 is reduced, and then the outlet 311 is opened, and the flow rate of the outlet 311 is the same as that of the inlet 312, so that the air pressure between the annular plate 32 and the base 31 and the air pressure in the annular plate 32 are kept constant. When the gas generator rotor assembly 2 undergoes radial runout, the gas generator rotor assembly 2 will approach the air pressure sensor 36, so that the air pressure of the air pressure sensor 36 will change;

[0048] The air pressure value of the air pressure sensor 36 is recorded in real time. The position of the radial imbalance point of the rotor on the rotor can be determined based on the time point of the air pressure change and the rotation speed of the rotor. The air pressure change cycle of the air pressure sensor 36 is the time for one rotation of the gas generator rotor assembly 2. The time point of the air pressure change in the air pressure value and time change table can determine the angular position of the radial imbalance point, and balancing mud can be added at the opposite position of the gas generator rotor assembly 2 to reduce the imbalance.

[0049] In S4, the weight change of the counterweight 62 on the gas generator rotor assembly 2 is detected by the tension sensor 61. The axial runout amplitude can be determined according to the weight change. At the same time, the position of the axial runout can be determined according to the runout amplitude of the edge and center of the gas generator rotor assembly 2. When the axial vibration amplitude exceeds the allowable range, the gas generator rotor assembly 2 needs to be disassembled and the size and installation matching relationship of the components need to be checked one by one, so as to ensure that the axial imbalance of the gas generator rotor assembly 2 is within the allowable range.

[0050] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for balancing a gas generator rotor with a stator component of an aircraft engine, characterized in that: The invention comprises a gas generator rotor assembly with a stator component and a gas generator rotor balancing device with a stator component for an aircraft engine, wherein the gas generator rotor assembly comprises an impeller outer cover, a compressor rotor, a gas turbine rotor, a double comb teeth and a bearing which are arranged in sequence, a gas turbine guide is fixed to the outer end of the gas turbine rotor, a diffuser and a compressor casing are fixed in sequence on one side of the gas turbine guide on the outer side of the compressor rotor, and an air intake casing is fixed to one end of the compressor casing; The gas generator rotor balancing device is used to clamp the gas generator rotor assembly for radial and axial testing; The gas generator rotor balancing device comprises a rotating fixture at the bottom, a gas generator rotor assembly is clamped in the rotating fixture, a radial detection assembly is sleeved on the gas generator rotor assembly, and an axial detection assembly is installed on the radial detection assembly; The radial detection assembly includes a base, an annular plate is fixed inside the base, nozzles are evenly fixed on the inner wall of the annular plate, the nozzles are located on the outside of the gas generator rotor assembly, an air inlet and an air outlet are opened on the side wall of the base, the air outlet is connected with the annular plate to form an exhaust channel, an annular channel is formed between the base and the annular plate, a flange is fixed on the upper end of the base, a cover plate is fixed on the upper end of the flange, an air pressure sensor is installed on the inner side of the nozzle, a mesh is fixed inside the annular plate, and the mesh is located inside the air pressure sensor; The rotating fixture comprises a shell, a throttle is fixed inside the shell, and an air inlet connected to the throttle is opened on the outer wall of the shell; The axial detection assembly includes a bracket, a tension sensor is fixed at the lower end of the bracket, a counterweight is connected to the lower end of the tension sensor through a spring, and the counterweight is located at the upper end of the gas generator rotor assembly; The balancing steps are as follows: S1. Clamp the tooling on one side of the gas generator rotor assembly by rotating the fixture, and then sleeve the radial detection assembly on the upper end of the gas generator rotor assembly, and connect the axial detection assembly to the radial detection assembly; S2. Compressed air is introduced into the air inlet of the rotating fixture and the inlet of the radial detection component, and the power is turned on to enable the rotating fixture and the radial detection component to rotate at high speed; S3, detecting the real-time air pressure of the nozzle through the air pressure sensor, and determining the radial runout of the gas generator rotor assembly according to the change amplitude of the air pressure. When the radial displacement of the rotor approaches the nozzle, the air pressure of the nozzle will change; S4. The axial jump of the gas generator rotor assembly is performed by following the axial jump of the gas generator rotor assembly through the counterweight block at the upper end of the gas generator rotor assembly. In this way, the counterweight block will jump up and down, thereby affecting the tension of the tension sensor. The axial jump of the gas generator rotor assembly can be determined according to the variation of the tension.

2. The method for balancing a rotor of a gas generator of an aircraft engine with a stator component according to claim 1, characterized in that: The upper and lower ends of the gas generator rotor assembly are respectively connected with an upper tooling and a lower tooling, wherein the upper tooling is connected with a radial detection assembly, and the lower tooling is connected with a rotating fixture.

3. The method for balancing a rotor of a gas generator of an aircraft engine with a stator component according to claim 1, characterized in that: A shaft sleeve is arranged on the inner side of the throttle, a top plate is fixed on the shaft sleeve on the upper side of the throttle, an air film channel exists between the top plate, the shaft sleeve and the throttle, the air inlet is connected with the air film channel, a motor is fixed between the shaft sleeve and the bottom end of the shell, the motor includes a rotor and a stator, the rotor is fixed on the outer wall of the shaft sleeve, the stator is fixed on the inner wall of the shell, and a grating is fixed on the bottom of the rotor.

4. The method for balancing a rotor of a gas generator with a stator component of an aircraft engine according to claim 3, characterized in that: An air passage is provided in the throttle, the air passage is communicated with the air inlet, and the air passage is also communicated with the air film passage outside the throttle.

5. The method for balancing a rotor of a gas generator with a stator component of an aircraft engine according to claim 1, characterized in that: There are at least two tension sensors, one of which is fixed above the outer edge of the gas generator rotor assembly, and the other is fixed above the center of the rotating shaft of the gas generator rotor assembly. The number of the counterweight blocks corresponds to the number of the tension sensors.

6. The method for balancing a rotor of a gas generator of an aircraft engine with a stator component according to claim 1, characterized in that: In S3, the outlet is first closed, and compressed air is introduced into the inlet to make a certain air pressure between the annular plate and the base, and then the inlet flow is reduced and the outlet is opened to keep the air pressure between the annular plate and the base and the air pressure inside the annular plate constant. When the gas generator rotor assembly undergoes radial runout, the gas generator rotor assembly will approach the air pressure sensor, so that the air pressure of the air pressure sensor will change. The air pressure value of the air pressure sensor is recorded in real time, and the position of the radial imbalance point of the rotor on the rotor can be determined according to the time point of the air pressure change and the speed of the rotor; In S4, the weight change of the counterweight block on the gas generator rotor assembly is detected by a tension sensor, and the axial runout amplitude can be determined according to the weight change. At the same time, the position of the axial runout can be determined according to the runout amplitude of the edge and center of the gas generator rotor assembly.

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