CN115235783A - Double-rotor coupling test device - Google Patents
Double-rotor coupling test device Download PDFInfo
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- CN115235783A CN115235783A CN202211154818.XA CN202211154818A CN115235783A CN 115235783 A CN115235783 A CN 115235783A CN 202211154818 A CN202211154818 A CN 202211154818A CN 115235783 A CN115235783 A CN 115235783A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Combustion & Propulsion (AREA)
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Abstract
The invention relates to a double-rotor coupling test device which comprises a driving motor, a gear transmission set, a high-pressure rotor, a low-pressure rotor and a plurality of wheel discs, wherein the low-pressure rotor is partially arranged in the high-pressure rotor in a penetrating mode, the low-pressure rotor and the high-pressure rotor are coaxially arranged with the wheel discs, the gear transmission set comprises a driving bevel gear, a first bevel gear and a second bevel gear, the first bevel gear and the second bevel gear are coaxially arranged and are respectively meshed with two sides of the driving bevel gear, the driving motor is in transmission connection with the driving bevel gear, the first bevel gear is connected with the high-pressure rotor, and the second bevel gear is connected with the low-pressure rotor. The double-rotor coupling test device provided by the invention has a simple structure, saves the installation space, can reach higher rotating speed, runs more stably, further ensures that the test result is more accurate, provides a reference basis for the structural optimization of a double-rotor system, and solves the problems of overlarge scale, overhigh cost and inaccurate test result of the conventional double-rotor coupling test device.
Description
Technical Field
The invention belongs to the technical field of rotor tests, and particularly relates to a double-rotor coupling test device.
Background
With the rapid development of the aviation field, the complexity of the aircraft is continuously improved, the reliability of the aircraft engine serving as a power device of the aircraft is an important factor influencing the safety of the aircraft, and in order to ensure that the aircraft engine can safely and efficiently operate, the operating condition and the change rule of the aircraft engine must be known, and tests such as state monitoring, fault diagnosis and the like are regularly performed on key components in the aircraft engine.
The rotor structure is the core structure of aeroengine, and current aviation turbojet or turbofan all adopt many rotor structures such as birotor or three rotors, and wherein the birotor structure uses more, so need carry out the coupling test to birotor structure.
At present, both an internal and external dual-rotor coupling test device built in a relevant academy of the aeroengine industry adopts a high-low voltage driving motor to drive a high-low voltage rotor respectively, and most of the internal and external dual-rotor coupling test devices are subjected to test tests on a complete machine table, so that the test device is overlarge in scale and overhigh in cost; at present, some internal and external dual-rotor coupling test devices built in colleges and universities are driven by a belt device to rotate a shaft, the reached rotating speed is low, the functions of the test devices are limited, the structural design of the test devices has a large difference from that of an actual aero-engine to a certain extent, the dynamic real situation of a high-low pressure dual-rotor system of the aero-engine under the condition of maneuvering flight cannot be reflected, and the test result is inaccurate.
Disclosure of Invention
The invention aims to at least solve the problems of overlarge scale, overhigh cost and inaccurate test result of the existing internal and external double-rotor coupling test device. The purpose is realized by the following technical scheme:
the invention provides a double-rotor coupling test device which comprises a driving motor, a gear transmission set, a high-pressure rotor, a low-pressure rotor and a plurality of wheel discs, wherein the low-pressure rotor is partially arranged in the high-pressure rotor in a penetrating mode, the low-pressure rotor, the high-pressure rotor and the plurality of wheel discs are coaxially arranged, the gear transmission set comprises a driving bevel gear, a first bevel gear and a second bevel gear, the driving motor is in transmission connection with the driving bevel gear, the first bevel gear and the second bevel gear are coaxially arranged, the first bevel gear and the second bevel gear are respectively meshed with two sides of the driving bevel gear, the first bevel gear is connected with the high-pressure rotor to drive the high-pressure rotor to rotate, and the second bevel gear is connected with the low-pressure rotor to drive the low-pressure rotor to rotate.
According to the double-rotor coupling test device provided by the embodiment of the invention, only one driving motor is arranged, so that the overall structure of the double-rotor coupling test device is simple and convenient, and the installation space and the construction cost are saved; in the embodiment, the gear transmission set is arranged, so that the first bevel gear and the second bevel gear are respectively meshed with the driving bevel gear, and the high-pressure rotor and the low-pressure rotor are simultaneously driven to rotate by one driving motor, so that the driving motor can realize continuous speed regulation between 0 and the maximum rotating speed, and the whole dual-rotor coupling test device can reach higher rotating speed, thereby more truly simulating the structure of an internal dual rotor and an external dual rotor of an aircraft engine and providing a reference basis for the structural optimization of a dual-rotor system; in addition, in the embodiment, the high-pressure rotor, the low-pressure rotor and the plurality of wheel discs are coaxially arranged, so that vibration caused by unbalance in the operation process is reduced or avoided, the double-rotor coupling test device is more stable in the rotation process of the rotors, and the test result is more accurate.
In addition, in some embodiments of the present invention, the dual-rotor coupling test apparatus further includes a plurality of support bearings including a first support bearing and a second support bearing provided on the high-pressure rotor, the first support bearing and the second support bearing being respectively adjacent to both ends of the high-pressure rotor.
In some embodiments of the invention, the first support bearing and the second support bearing are both provided as rolling bearings.
In some embodiments of the present invention, the plurality of support bearings further comprises an intermediate bearing disposed between the high pressure rotor and the low pressure rotor.
In some embodiments of the present invention, the plurality of support bearings further includes a third support bearing, the third support bearing and the intermediate bearing being respectively adjacent to both ends of the low pressure rotor.
In some embodiments of the invention, the third support bearing is provided as a rolling bearing.
In some embodiments of the present invention, the plurality of discs includes a first disc mounted on the high pressure rotor and a second disc mounted on the low pressure rotor.
In some embodiments of the invention, the first disk is located between the first support bearing and the second support bearing and near an end of the high pressure rotor distal from the gear drive train.
In some embodiments of the invention, both ends of the low pressure rotor respectively extend outside the high pressure rotor, and the second disk is located between the end of the high pressure rotor and the third support bearing.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
FIG. 1 is a schematic structural diagram of a dual-rotor coupling test device;
fig. 2 is a partial structural schematic diagram of a dual-rotor coupling test device.
The reference symbols in the drawings denote the following:
100. a dual rotor coupling test device;
10. a drive motor; 11. a motor shaft; 12. a drive bevel gear; 20. a first bevel gear; 21. a first support bearing; 22. a high pressure rotor; 23. a first wheel disc; 24. a second support bearing; 30. a second bevel gear; 31. an intermediate bearing; 32. a low-pressure rotor; 33. a second wheel disc; 34. and a third support bearing.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.
Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
For convenience in description, the relationship of one element or feature to another element or feature as illustrated in the figures may be described herein using spatially relative terms, such as "inner", "outer", "lower", "below", "upper", "over", and the like. Such spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the example term "below … …" may include both an up and down orientation.
As shown in fig. 1 and fig. 2, an embodiment of the present invention provides a dual-rotor coupling test apparatus 100, where the dual-rotor coupling test apparatus 100 includes a driving motor 10, a gear transmission set, a high-pressure rotor 22, a low-pressure rotor 32, and a plurality of wheel discs, the low-pressure rotor 32 is partially inserted into the high-pressure rotor 22, the low-pressure rotor 32 and the high-pressure rotor 22 are coaxially disposed with the plurality of wheel discs, the gear transmission set includes a driving bevel gear 12, a first bevel gear 20, and a second bevel gear 30, the driving motor 10 is in transmission connection with the driving bevel gear 12, the first bevel gear 20 and the second bevel gear 30 are coaxially disposed, the first bevel gear 20 and the second bevel gear 30 are respectively engaged with two sides of the driving bevel gear 12, the first bevel gear 20 is connected with the high-pressure rotor 22 to drive the high-pressure rotor 22 to rotate, and the second bevel gear 30 is connected with the low-pressure rotor 32 to drive the low-pressure rotor 32 to rotate.
According to the double-rotor coupling test device 100 provided by the embodiment of the invention, only one driving motor 10 is arranged, so that the whole structure of the double-rotor coupling test device 100 is simple and convenient, and the installation space and the construction cost are saved; in the embodiment, by arranging the gear transmission set, the first bevel gear 20 and the second bevel gear 30 are respectively meshed with the drive bevel gear 12, the high-pressure rotor 22 and the low-pressure rotor 32 are simultaneously driven to rotate by one driving motor 10, the driving motor 10 can realize continuous speed regulation between 0 and the maximum rotating speed, and the whole dual-rotor coupling test device 100 reaches a higher rotating speed, so that the internal and external dual-rotor structure of the aero-engine can be simulated more truly, a reference basis is provided for the structural optimization of the dual-rotor system, and by coaxially arranging the high-pressure rotor 22 and the low-pressure rotor 32 with a plurality of wheel discs, the vibration caused by unbalance in the operation process is reduced or avoided, the dual-rotor coupling test device 100 is more stable in the rotor rotation process, and the test result is more accurate. In summary, the dual-rotor coupling test device 100 provided by the embodiment of the present invention solves the problems of the existing internal and external dual-rotor coupling test device 100, such as large scale, high cost and inaccurate test result.
As shown in fig. 1 and 2, in the dual-rotor coupling test apparatus 100 according to the embodiment of the present invention, the driving motor 10 includes a motor shaft 11, the gear transmission set includes a driving bevel gear 12, a first bevel gear 20 and a second bevel gear 30, as shown in fig. 1, the motor shaft 11 of the driving motor 10 is in transmission connection with the driving bevel gear 12, so that the driving bevel gear 12 can be driven by the driving motor 10 to rotate, on the basis that the first bevel gear 20 and the second bevel gear 30 are respectively engaged with the driving bevel gear 12, and the first bevel gear 20 and the second bevel gear 30 are respectively located at two radial sides of the driving bevel gear 12, the axes of the first bevel gear 20 and the second bevel gear 30 are perpendicular to the axis of the driving bevel gear 12, so that when the driving bevel gear 12 rotates with the driving motor 10, the first bevel gear 20 and the second bevel gear 30 rotate therewith, and the rotation directions of the first bevel gear 20 and the second bevel gear 30 are opposite.
Referring to fig. 1, the dual-rotor coupling test apparatus 100 includes a high-pressure rotor 22 and a low-pressure rotor 32, wherein the length of the low-pressure rotor 32 is greater than the length of the high-pressure rotor 22, the low-pressure rotor 32 is disposed in the high-pressure rotor 22, and two ends of the low-pressure rotor 32 respectively extend out of two ends of the high-pressure rotor 22, and on the basis, a first bevel gear 20 is connected to one end of the high-pressure rotor 22 close to the driving motor 10 to drive the high-pressure rotor 22 to rotate; the second bevel gear 30 is connected to an end of the low pressure spool 32 near the driving motor 10 to rotate the low pressure spool 32. Therefore, the driving motor 10, the gear train, and the high pressure rotor 22 and the low pressure rotor 32 are reasonably compact in layout in the present embodiment.
On the basis of the above embodiment, the axis of the high-pressure rotor 22 coincides with the axis of the low-pressure rotor 32, and accordingly, the axis of the first bevel gear 20 coincides with the axis of the second bevel gear 30, so that in the present embodiment, the high-pressure rotor 22, the low-pressure rotor 32, the first bevel gear 20, and the second bevel gear 30 are coaxially disposed, and the vibration amount caused by the unbalanced force in the operation process of the dual-rotor coupling test device 100 is reduced, so that the imbalance precision grade standard of the rotary machine is met, and the test accuracy of the dual-rotor coupling test device 100 is improved.
As shown in fig. 2, in the present embodiment, the rotation speed of the driving motor 10 is taken as
The number of teeth of the drive bevel gear 12 is
The first bevel gear 20 has a rotational speed of
The number of teeth of the first bevel gear 20 is
The second bevel gear 30 has a rotational speed of
The number of teeth of the second bevel gear 30 is
For example, the relationship between the driving motor 10, the drive bevel gear 12, the first bevel gear 20, and the second bevel gear 30 is:
further, as shown in fig. 1, in some embodiments of the present invention, the dual-rotor coupling test apparatus 100 further includes a plurality of support bearings for supporting the high-pressure rotor 22 and the low-pressure rotor 32, and exemplarily, as shown in fig. 1, the plurality of support bearings includes a first support bearing 21 and a second support bearing 24 disposed on the high-pressure rotor 22, the first support bearing 21 and the second support bearing 24 are respectively located near both ends of the high-pressure rotor 22, and accordingly, the dual-rotor coupling test apparatus 100 further includes bearing supports (not shown) corresponding to the first support bearing 21 and the second support bearing 24, and in this embodiment, the arrangement of the first support bearing 21 and the second support bearing 24 ensures the stability of the high-pressure rotor 22.
Further, in some embodiments of the present invention, the first support bearing 21 and the second support bearing 24 are both provided as rolling bearings, and the rolling bearings can change sliding friction between the operating high-pressure rotor 22 and the bearing support into rolling friction, thereby reducing friction loss and ensuring normal operating position and rotation accuracy of the high-pressure rotor 22 during operation of the dual-rotor coupling test apparatus 100.
Further, in some embodiments of the present invention, the plurality of support bearings further includes an intermediate bearing 31 disposed between the high-pressure rotor 22 and the low-pressure rotor 32, the intermediate bearing 31 is used for supporting the low-pressure rotor 32, according to the above-mentioned embodiment, the low-pressure rotor 32 is partially disposed in the high-pressure rotor 22, in this embodiment, the intermediate bearing 31 is disposed between the high-pressure rotor 22 and the low-pressure rotor 32 and is disposed close to the driving motor 10, that is, the intermediate bearing 31 can support the front end of the low-pressure rotor 32, and the intermediate bearing 31 can also enhance the rigidity, ensure that the low-pressure rotor 32 and the high-pressure rotor 22 are not touched by deformation, so that the structural layout of the dual-rotor coupling test apparatus 100 is more reasonable.
Further, in some embodiments of the present invention, the plurality of support bearings further include a third support bearing 34, the third support bearing 34 and the intermediate bearing 31 are respectively close to two ends of the low-pressure rotor 32, in the above embodiment, the intermediate bearing 31 is close to the driving motor 10, and the third support bearing 34 is close to one end of the low-pressure rotor 32 far from the driving motor 10, so that the third support bearing 34 and the intermediate bearing 31 jointly support the low-pressure rotor 32, and accordingly, the dual-rotor coupling test apparatus 100 further includes a bearing support (not shown) corresponding to the third support bearing 34, and in this embodiment, the third support bearing 34 and the intermediate bearing 31 are arranged to ensure the stability of the low-pressure rotor 32.
Further, in some embodiments of the present invention, the third support bearings 34 are all configured as rolling bearings, and the rolling bearings can change the sliding friction between the operating low-pressure rotor 32 and the bearing support into rolling friction, so as to reduce friction loss and ensure the normal working position and rotation accuracy of the low-pressure rotor 32 during the operation of the dual-rotor coupling test device 100.
In addition, in this embodiment, the plurality of support bearings may be adjusted in corresponding positions according to actual conditions, so that the stress on each portion of the dual-rotor coupling test apparatus 100 is more reasonable, the axes of the plurality of support bearings may be completely overlapped and overlapped with the axes of the high-pressure rotor 22 and the low-pressure rotor 32, and it is further ensured that the vibration amount caused by the unbalanced force is the minimum in the operation process, and the standard of the unbalanced precision level of the rotary machine is satisfied. Therefore, the dynamic characteristics of the inner and outer high-low pressure double-rotor systems are coupled with each other by the arrangement of the plurality of support bearings, so that the double-rotor coupling test device 100 provided by the embodiment can simulate the inner and outer double-rotor structures of the aero-engine more truly.
Further, as shown in fig. 1, in some embodiments of the present invention, the plurality of discs in the dual rotor coupling test apparatus 100 includes a first disc 23 and a second disc 33, the first disc 23 is mounted on the high pressure rotor 22, the second disc 33 is mounted on the low pressure rotor 32, and in some embodiments of the present invention, the first disc 23 is located between the first support bearing 21 and the second support bearing 24 and is near an end of the high pressure rotor 22 away from the gear train; according to the above embodiment, both ends of the low pressure rotor 32 are protruded out of the high pressure rotor 22, respectively, and the second disk 33 is located between the end of the high pressure rotor 22 and the third support bearing 34 in this embodiment.
On the basis of the above embodiment, the axes of the first wheel disc 23 and the second wheel disc 33 coincide with the axis of the high-pressure rotor 22, so that the axes of the first wheel disc 23, the plurality of support bearings of the second wheel disc, the high-pressure rotor 22 and the low-pressure rotor 32 completely coincide, the vibration caused by the unbalanced force in the operation process is further ensured to be minimum, the standard of the accuracy grade of the unbalance of the rotating machinery is met, and the stability and the test accuracy in the working process of the double-rotor coupling test device 100 are improved. Compared with the prior art, the dual-rotor coupling test device 100 provided by the embodiment has the advantages of simpler and more reasonable structure, small occupied space, good stability and high test result accuracy, and can effectively promote the structure optimization design of the internal and external dual-rotor system of the aircraft engine and the research on the mechanical properties of key components.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. The double-rotor coupling test device is characterized by comprising a driving motor, a gear transmission set, a high-pressure rotor, a low-pressure rotor and a plurality of wheel discs, wherein the low-pressure rotor is partially arranged in the high-pressure rotor in a penetrating mode, the low-pressure rotor, the high-pressure rotor and the plurality of wheel discs are coaxially arranged, the gear transmission set comprises a driving bevel gear, a first bevel gear and a second bevel gear, the driving motor is in transmission connection with the driving bevel gear, the first bevel gear and the second bevel gear are coaxially arranged, the first bevel gear and the second bevel gear are respectively meshed with two sides of the driving bevel gear, the first bevel gear is connected with the high-pressure rotor to drive the high-pressure rotor to rotate, and the second bevel gear is connected with the low-pressure rotor to drive the low-pressure rotor to rotate.
2. The dual rotor coupling test apparatus of claim 1, further comprising a plurality of support bearings including a first support bearing and a second support bearing disposed on the high pressure rotor, the first support bearing and the second support bearing being respectively proximate to both ends of the high pressure rotor.
3. The dual-rotor coupling test apparatus of claim 2, wherein the first support bearing and the second support bearing are both provided as rolling bearings.
4. The dual rotor coupling test apparatus of claim 2, wherein the plurality of support bearings further comprises an intermediate bearing disposed between the high pressure rotor and the low pressure rotor.
5. The dual rotor coupling test apparatus of claim 4, wherein the plurality of support bearings further comprises a third support bearing, the third support bearing and the intermediate bearing being located near each end of the low pressure rotor.
6. The dual-rotor coupling test device of claim 5, wherein the third support bearing is provided as a rolling bearing.
7. The dual rotor coupling test apparatus of claim 5, wherein the plurality of discs includes a first disc and a second disc, the first disc being mounted on the high pressure rotor and the second disc being mounted on the low pressure rotor.
8. The dual rotor coupling test apparatus of claim 7, wherein the first wheel disc is located between the first and second support bearings and near an end of the high pressure rotor distal from the gear train.
9. The dual rotor coupling test apparatus of claim 8, wherein both ends of the low pressure rotor respectively extend outside the high pressure rotor, and the second disk is located between the end of the high pressure rotor and the third support bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211154818.XA CN115235783B (en) | 2022-09-22 | 2022-09-22 | Birotor coupling test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211154818.XA CN115235783B (en) | 2022-09-22 | 2022-09-22 | Birotor coupling test device |
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| CN115235783A true CN115235783A (en) | 2022-10-25 |
| CN115235783B CN115235783B (en) | 2023-08-22 |
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