CN116539307A - Bearing support assembly and aviation double-rotor test stand applying same - Google Patents
Bearing support assembly and aviation double-rotor test stand applying same Download PDFInfo
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- CN116539307A CN116539307A CN202310474263.5A CN202310474263A CN116539307A CN 116539307 A CN116539307 A CN 116539307A CN 202310474263 A CN202310474263 A CN 202310474263A CN 116539307 A CN116539307 A CN 116539307A
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- 230000008093 supporting effect Effects 0.000 claims description 54
- 238000007664 blowing Methods 0.000 claims description 15
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Classifications
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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
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
Abstract
The application discloses bearing support assembly and use its aviation birotor test bench, support assembly includes: the bearing seat is provided with a hollow cavity; the multiple end covers comprise a mounting part in a circular ring shape and an insertion part which extends from the circular ring surface to one side to form a cavity and is communicated with the hollow part of the circular ring, the insertion part is inserted into the hollow cavity and is mounted on the bearing seat through the mounting part, the insertion part is used for mounting a bearing support bearing, the multiple end covers are different in at least one aspect of the structural size and the morphological structure type of the insertion part, and the multiple end covers are used for adapting to different bearings in a switching mode. The end covers comprising the mounting part and the inserting part are arranged, so that the support assembly can adapt to different test bearings by replacing the end covers with different specifications, and has higher universality.
Description
Technical Field
The application relates to the technical fields of bearing performance tests and bearing dynamic characteristic research tests developed by aero-engine research, in particular to a bearing support assembly and an aviation double-rotor test bed using the same.
Background
Rolling bearings are widely used in rotating machinery, and their rigidity, dynamics, etc. affect the reliability of the rotating machinery. Therefore, research institutions often build corresponding bearing test benches to explore the rigidity, dynamics and other characteristics of the bearings.
The utility model patent with the application number of CN202021190892.3 discloses a rolling bearing test bed, which comprises a horizontally arranged main shaft, wherein one end of the main shaft is connected with a rotary driving assembly so as to drive the main shaft to rotate; the outer part of the main shaft is sleeved with two test bearings, the test bearings are supported by test bearing seats, and the test bearing seats are respectively supported by a non-centering adjustment platform; the misalignment adjustment platform can adjust the height of the test bearing in the vertical direction, so that the coaxiality of the central axis of the test bearing and the central axis of the main shaft is adjusted.
The utility model patent with the application number of CN201922054176.6 discloses a sliding bearing test bed for applying random regular variable load, which comprises an alternating current motor, a coupler, a bearing seat, a rolling bearing, a sliding bearing seat, a test main shaft, a bearing end cover, an encoder, a ball screw, a screw nut, a first loading plate, a spring, a second loading plate, a loading rod, a steering box and a servo motor, wherein the alternating current motor is fixed on a table frame and is connected with the test main shaft through the coupler, the two ends of the test main shaft are supported through the rolling bearing, and the rolling bearing is fixed on the table frame through the bearing seat; the servo motor is fixed on the base and is connected with the steering box through the coupler, the steering box is fixedly connected with the ball screw, the ball screw is provided with a screw nut, and the screw nut is in fit connection with the first loading plate; the spring is arranged on the upper side of the second loading plate, the first loading plate is arranged on the upper side of the spring, the loading rod penetrates through the inside of the spring and the first loading plate to fixedly connect the second loading plate with the sliding bearing seat, and the sliding bearing seat is suspended on the test main shaft.
Therefore, the test bed bearings in the above patent are supported by the bearing blocks directly, the bearing blocks and the bearings can only be in one-to-one correspondence, the bearing blocks serving as supporting structures of the test bearings do not have universality, and the bearing blocks are required to be replaced more difficultly when experimental researches are carried out on the bearings with different specifications.
Accordingly, there is a need to provide a related art solution that enables the versatility of a bearing support assembly including a bearing housing to be improved.
Disclosure of Invention
The embodiment of the application provides a related technical scheme capable of improving the universality of a bearing support assembly comprising a bearing pedestal, so as to solve the problem of low universality of the bearing pedestal in the arrangement of a test bearing supported by the bearing pedestal directly in the prior art.
A bearing support assembly provided herein includes:
the bearing seat is provided with a hollow cavity;
the multiple end covers comprise a mounting part in a circular ring shape and an insertion part which extends from the circular ring surface to one side to form a cavity and is communicated with the hollow part of the circular ring, the insertion part is inserted into the hollow cavity and is mounted on the bearing seat through the mounting part, the insertion part is used for mounting a bearing support bearing, the multiple end covers are different in at least one aspect of the structural size and the morphological structure type of the insertion part, and the multiple end covers are used for adapting to different bearings in a switching mode. Further, in a preferred embodiment provided herein, the morphology and structure type of the insert portion includes a squirrel cage structure, an elastic ring structure, a hollow columnar structure with a complete circumferential envelope.
Further, in a preferred embodiment provided in the present application, the bearing seat and the mounting portion end cover are correspondingly provided with screw structures.
The application provides an aviation birotor test bench, include:
the rotor unit comprises a low-pressure rotor and a high-pressure rotor arranged outside the low-pressure rotor;
the driving unit comprises a first driving unit which is in transmission connection with the low-pressure rotor and is used for driving the low-pressure rotor, and a second driving unit which is used for driving the high-pressure rotor;
the support unit is used for supporting the rotor unit and comprises a first support unit and a second support unit, wherein the first support unit is used for supporting the low-pressure rotor and is rotationally connected with the low-pressure rotor, and the second support unit is used for supporting the high-pressure rotor and is rotationally connected with the high-pressure rotor;
wherein the first support unit and/or the second support unit comprises a bearing support assembly according to any one of claims 1-3.
Further, in a preferred embodiment provided herein, the device further includes a base, and the support unit is disposed on the base.
Further, in a preferred embodiment provided in the present application, the support unit is a support unit movably disposed on the base.
Further, in a preferred embodiment provided herein, the support unit further includes a limiting structure for limiting the movement of the support unit.
Further, in a preferred embodiment provided herein, the first drive unit comprises a high-speed motor drivingly connected to the low-voltage rotor through a coupling.
Further, in a preferred embodiment provided in the present application, an aviation dual rotor test stand as described in any one of the above, the second driving unit includes an air blowing device for providing high-pressure rotor rotation power.
The embodiment provided by the application has at least the following beneficial effects:
the support assembly comprises the installation part and the insertion part, and the support assembly can be matched with the test bearing through the end covers, so that the universality of the support assembly comprising the bearing seat is improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute an undue limitation to the application. In the drawings:
FIG. 1 is a schematic view of a bearing support assembly and test bearing assembly structure according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of the assembled structure of FIG. 1 taken along line A-A;
FIG. 3 is a schematic view of a portion of an end cap according to an embodiment of the present disclosure, taken along a central axis thereof;
fig. 4 is a schematic perspective view of an insert portion of an end cap according to an embodiment of the present disclosure;
FIG. 5 is a schematic view of an end cap according to an embodiment of the present disclosure in a view angle;
FIG. 6 is a schematic perspective view of an insert of another end cap according to an embodiment of the present disclosure;
FIG. 7 is a schematic view of the insert portion of FIG. 6 from one perspective;
fig. 8 is a schematic structural diagram of an aviation dual rotor test stand according to an embodiment of the present application;
fig. 9 is a schematic view of a turbine structure of a high-pressure rotor according to an embodiment of the present application.
1. Bearing pedestal
10. Bearing seat screw hole
3. End cap
30. Mounting part
302. Epitaxial structure
32. Insertion part
34. Screw hole of end cover
5. Bearing
50. Bearing inner ring
52. Bearing rolling element
54. Bearing outer ring
2. Low-pressure rotor
20. Low-pressure rotor shaft
22. Wheel disc of low-pressure compressor
24. Low pressure turbine disk
4. High-pressure rotor
40. High-pressure rotor shaft
42. High-pressure compressor wheel disc
44. High-pressure turbine wheel disc
440. Blade
6. First drive unit
8. Second drive unit
70. First support unit
72. Second support unit
9. A coupling.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments of the present application and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In the description of the present application, it should be noted that, unless explicitly set and defined otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
In the description of the present application, it should be noted that, unless explicitly set and defined otherwise, the terms "first", "second", and the like are merely used for convenience of description of the present application and to simplify the description, and are not used for limiting the present application unless otherwise noted. The specific meaning of the terms herein will be understood to be specifically understood by those of ordinary skill in the art.
In the description of the present application, it should be noted that, unless explicitly set and defined otherwise, terms such as "one end", "the other end", and the like are merely for convenience of description of the present application and for simplification of description, and are not intended to limit the present application to distinguish between different ends of the same object. The specific meaning of the terms in this application will be understood to those of ordinary skill in the art in a specific context.
The bearing seat is often directly used as an outer supporting structure of the bearing, so that a stable environment state is provided for the bearing, and the bearing seat and the bearing are required to be matched highly, so that a one-to-one correspondence is formed between the bearing seat and the bearing, and the bearing seat is low in universality. However, the specifications of the bearings in the test research related to the bearings cannot be unchanged, and the existing bearing outer supporting structure cannot meet the requirements well, so that the bearing supporting component of the bearing test device is high in universality, and at least the defects that all the test devices related to the bearings in industry hospitals are simple in function, single in test item, low in integration level, high in cost and the like can be effectively overcome.
Namely, it can be appreciated that the present application relates to the field of support reliability of rotary mechanical equipment, in particular to bearing performance tests and bearing dynamics research tests developed by aero-engine research; the rolling bearing is widely applied to rotary mechanical equipment, in order to explore the rigidity and dynamic characteristics of the rolling bearing, a research institution usually builds a corresponding bearing test bed, the bearing test bed is often specific, only bearing tests with fixed outer ring sizes can be carried out, and the universality cannot be achieved; aiming at the defects and shortcomings of the prior art, the application aims to provide a novel bearing support assembly in a bearing test device, which has the advantages of relatively high universality, low cost, repeatability test and the like, and is more suitable for bearing performance tests and bearing dynamics characteristic research of scientific research institutes.
As shown in the drawings, fig. 1 is a schematic view of an assembly structure of a bearing support assembly and a test bearing provided in the embodiment of the present application, fig. 2 is a schematic view of an assembly structure of fig. 1 cut along A-A, fig. 3 is a schematic view of a portion of an end cover cut along an axis thereof provided in the embodiment of the present application, fig. 4 is a schematic view of an insert portion of an end cover provided in the embodiment of the present application, fig. 5 is a schematic view of an end cover provided in one view angle, fig. 6 is a schematic view of an insert portion of another end cover provided in the embodiment of the present application, fig. 7 is a schematic view of an insert portion of fig. 6 cut along an axis thereof, specifically, fig. 3 may be a schematic view of a portion of an end cover cut along an axis thereof, fig. 5 may be a schematic view of an insert portion of fig. 4 cut along an axis thereof, fig. 4, fig. 5 may be a schematic view of a structure of a cage structure of an end cover, fig. 6, and fig. 7 may be a schematic view of an elastic ring structure.
The bearing seat 1 is provided with a hollow cavity, and a screw structure is arranged at one end of the bearing seat, and the screw structure can be a bearing seat screw hole 10.
Each end cover 3 comprises a mounting part 30 in a circular ring shape and an inserting part 32 which extends to one side from the circular ring surface to form a cavity, wherein the cavity is communicated with the hollow part of the circular ring, the inserting part 32 is inserted into the hollow cavity and is mounted on a bearing seat through the mounting part 30, the inserting part 32 is used for mounting the bearing support bearing 5, and the plurality of end covers 3 are different in at least one aspect of the structural size and the morphological structure type of the inserting part 32, and the plurality of end covers 3 are used in a switching way so as to adapt to different bearings 5. Specifically, the end cover 3 may be a screw structure which is arranged by itself and corresponds to a screw structure arranged at one end of the bearing seat, and is connected and mounted to the bearing seat by a connecting piece; the insertion portion 32 may be a structure formed by extending from the annular surface of the mounting portion 30 to one side, and having a cavity, wherein the cavity is communicated with the hollow portion of the mounting portion, and specifically, may be as shown in fig. 2 and 3; the outer diameter of the mounting portion 30 may be larger than the outer diameter of the insertion portion 32, as shown in fig. 2 and 3, which are examples in which the outer diameter of the mounting portion 30 is larger than the outer diameter of the insertion portion 32, and in fig. 2 and 3, the annular region where the outer diameter portion of the mounting portion 30 beyond the insertion portion 32 is located is the extension structure 302, and in this example, the extension structure 302 may serve as a limit for setting a screw structure; the inner diameter dimension of the mounting portion 30 may be smaller than the inner diameter dimension of the insertion portion 32, and as shown in fig. 2 and 3, the inner diameter dimension of the mounting portion 30 is smaller than the inner diameter dimension of the insertion portion 32, in which case the mounting portion may function as dust protection for the bearing mounted in the insertion portion cavity.
The outer diameters of the mounting portion 30 and the insertion portion 32 may be the same, and at this time, the screw structure end cover screw hole 34 on the end cover may be arranged along the radial direction of the mounting portion, at this time, the mounting portion 30 and the insertion portion 32 may be inserted into the hollow cavity of the bearing seat, the bearing seat screw hole 10 is correspondingly arranged, and the connecting piece for connecting the mounting portion 30 and the bearing seat 1 may play a limiting role in addition to playing a role of connecting and mounting; when the outer diameter of the mounting portion 30 is larger than the outer diameter of the insertion portion 32, the screw structure end cap screw hole 34 on the end cap may be provided on the extension structure 302 and along the axial direction of the mounting portion, and at this time, only the insertion portion 32 may be inserted into the hollow cavity of the bearing housing, and the specific arrangement of the bearing housing screw hole 10 and the end cap screw hole 34 may be as shown in fig. 2 and 3.
The type of morphology of the insert 32 may be a squirrel cage structure, an elastic ring structure; specifically, the squirrel-cage structure may be an elastic ring structure as shown in fig. 4 and 5, and the rigidity of the insertion portion 32 of the two types of morphological structures may be adjusted by the axially arranged rib width, the distance between ribs, and the like as shown in fig. 6 and 7; the insert 32 may also be a hollow cylindrical structure with a complete circumferential envelope; when the test bearing is used, the test bearing can be properly selected according to the characteristic requirement of the test bearing, the bearing with high rigidity usually selects an elastic ring type structure, and the bearing with low rigidity selects a squirrel-cage structure or a hollow columnar structure with a complete circumferential enveloping surface.
The bearing seat 1 and the end cover 3 can be connected through a screw structure, or can be connected through other connecting modes which can meet the working condition requirement, and are preferably in screw connection, so that the cost is low.
The bearing 5, i.e., the test bearing, may include the bearing inner ring 50, the bearing rolling elements 52, and the bearing outer ring 54; in the rigidity calculation, rigidity=load/deformation, when the assembly is used, the bearing seat 1, the end cover 3 and the bearing 5 can be concentrically arranged, and in the supporting structure formed by the three components, the rigidity K of the bearing 1 Stiffness of end cap K 2 The bearing and the end cover form a parallel connection relation, and the total rigidity of the support system formed by the bearing and the end cover is K, so that the calculation formula is as follows:
K=K 1 K 2 /( K 1 +K 2 )
it can be seen that according to the test task requirements, the total rigidity K of the support system is along with the end cover K 2 The rigidity of the end cover can be adjusted adaptively according to the changed characteristics of the support system, so that the effect of adjusting the support rigidity of the support system can be achieved.
Referring to fig. 1 to 7, in one embodiment, a support structure includes a bearing and any bearing support assembly of the present application, that is, the support structure may include a bearing housing 1, an end cover 3, and a bearing 5, the bearing 5 is mounted in the end cover 3, the end cover 3 is mounted on the bearing housing, specifically, an insertion portion 32 of the end cover 3 is disposed in the bearing housing 1 and is mounted on the bearing housing 1 through a mounting portion 30, and the bearing 5 is mounted in the insertion portion 32 of the end cover 3; when in use, the end cover 3 can be made into end cover sleeve groups with various structural sizes and/or various morphological structure types and selected for use according to the specification types of the bearing 5 in test at least by adjusting one aspect of structural size and morphological structure type of the design insertion part 32, wherein the adjustment of the structural size is specifically to at least change one of radial inner diameter size and outer diameter size of the insertion part 32 of the end cover 3, and the change of the morphological structure type is a switching use among a squirrel cage structure, an elastic ring structure and a hollow columnar structure with a complete circumferential enveloping surface, and the switching use on the morphological structure type is mainly used for changing the supporting rigidity of a supporting system of the supporting structure so as to develop a bearing related performance test in expansion; in detail, the end cover 3 may be connected to the bearing seat 1 by bolts or screws, and main components such as the bearing seat 1, the end cover 3, and the test bearing 5 may be kept highly concentric during installation and integration, that is, the coaxiality between the inner and outer profiles of the bearing seat 1 and the end cover 3 and the test bearing 5 needs to be controlled during design, so that the main components such as the bearing seat 1, the end cover 3, and the test bearing 5 are ensured to be kept highly concentric during installation and integration, so that the test device using the support structure can cover a larger rotating speed working condition. The supporting structure has the advantages of scientific and reasonable integral structure, simple and convenient production process, easy popularization and promotion, repeated use of the bearing seat 1, no need of replacement, great reduction of test cost and wide application in the test research of the bearing of the rotating equipment.
It can be appreciated that, the bearing support assembly that this application provided, end cover 3 can have concurrently and connect, seal, adjust bearing braced system and support the function of rigidity, through the end cover structural dimension, form structure type's adjustment can realize the change of whole rigidity, can play the effect of adjusting braced system whole and support rigidity characteristic, can develop more supporting property tests simultaneously in accomplishing bearing performance test, can understand as end cover support bearing, so the end cover can be according to test demand adjustment and select, thereby adjust the supporting rigidity of the braced system including bearing, the bearing frame, the bearing structure of end cover, with the supporting characteristic of the supporting structure of adjusting including the bearing, and then the development bearing performance test of expansibility. For the bearing test device built by relevant courts and various universities of the aeroengine industry, the end cover 3 with the characteristics is introduced for the first time, and the multifunctional and reusable characteristics of the test device using the support assembly can be fully exerted. The structure of the application is relatively simple, and a large amount of funds are saved in the aspect of construction cost.
As shown in fig. 8 and 9, the present application further provides an aviation dual rotor test stand, which may include: the bearing support assembly of any one of the present application may specifically include: the rotor unit comprises a low-pressure rotor and a high-pressure rotor arranged outside the low-pressure rotor; the driving unit comprises a first driving unit which is in transmission connection with the low-pressure rotor and is used for driving the low-pressure rotor, and a second driving unit which is used for driving the high-pressure rotor; the support unit is used for supporting the rotor unit and comprises a first support unit and a second support unit, wherein the first support unit is used for supporting the low-pressure rotor and is rotationally connected with the low-pressure rotor, and the second support unit is used for supporting the high-pressure rotor and is rotationally connected with the high-pressure rotor; wherein the first support unit and/or the second support unit comprises a bearing support assembly as described in any one of the applications. More specifically, it may be that at least one of the two support units comprising the bearing support assembly shown in fig. 1, i.e. the aeronautical birotor test stand, comprises a support structure as described herein.
The aviation dual-rotor test stand can further comprise a base, and the supporting unit is arranged on the base.
Further, the supporting unit may be a supporting unit movably disposed on the base.
Further, the aviation dual rotor test stand may further include a limiting structure limiting the movement of the supporting unit.
The first driving unit can comprise a high-speed motor which is in transmission connection with the low-voltage rotor through a coupler; the second driving unit may be a blower device including a motor for supplying high-pressure rotor rotation power.
As shown in fig. 8, the present application provides an aviation dual rotor test stand, which may include a rotor unit, a driving unit, and a supporting unit.
The rotor unit may include a low-pressure rotor 2 and a high-pressure rotor 4 disposed outside the low-pressure rotor.
Specifically, the low pressure rotor 2 may include a low pressure rotor shaft 20, a low pressure compressor disk 22, and a low pressure turbine disk 24; the high pressure rotor may be a high pressure rotor shaft 40, a high pressure compressor disk 42, a high pressure turbine disk 44, the blades of which may be arranged in a simulation as shown in fig. 9.
The drive unit comprises a first drive unit 6 in transmission connection with the low-pressure rotor 2 for driving the low-pressure rotor 2, and a second drive unit 8 for driving the high-pressure rotor 4.
Specifically, the first driving unit may include a high-speed motor, where the high-speed motor may be in transmission connection with the low-voltage rotor 2 through a coupling 9, and in practical implementation, the selection of the high-speed motor may be selected according to a specific situation of a dual-rotor structure to be studied, so that the high-speed motor may achieve continuous adjustability from 0 to a target maximum rotation speed; the second driving unit may include an air blowing device, where the air blowing device is used to provide rotation power of the high-pressure rotor 4, and the air blowing device is selected to be used preferentially according to needs, and the above arrangement, compared with the dual-rotor test devices built in related institutions of universities and aero-engine industries in the prior art, the test stand of the application has higher rotational speed and less limited functions due to the arrangement of the rotating shaft of the driving rotor through the belt device; the problem of excessive cost caused by the fact that high-low-voltage motors are respectively driven by high-low-voltage motors in the dual-rotor test devices built by relevant institutions and the like in the aero-engine industry in the prior art can be solved through the arrangement of only one motor.
The support unit is used for supporting the rotor unit, the support unit comprises a first support unit 70 and a second support unit 72, the first support unit is used for supporting the low-pressure rotor 2 and is rotationally connected with the low-pressure rotor, and the second support unit 72 is used for supporting the high-pressure rotor 4 and is rotationally connected with the high-pressure rotor.
Specifically, as shown in fig. 8, the supporting unit may include a plurality of first supporting units 70 and a plurality of second supporting units 72, and more specifically, may include two first supporting units 70 and two second supporting units 72, where one of the two first supporting units 70 may be rotatably connected to one end of the low pressure rotor shaft 20 and the other may be rotatably connected to the other end of the low pressure rotor shaft 20, and one of the two second supporting units 72 may be rotatably connected to one end of the high pressure rotor shaft 40 and the other end of the high pressure rotor shaft 40, and one of the two second supporting units 70 may be rotatably connected to the other end of the high pressure rotor shaft 40.
The support unit may specifically comprise a rolling bearing, a bearing housing 1, a plurality of end caps 3, i.e. the high pressure rotor and the low pressure rotor may essentially be supported by a pair of rolling bearings provided with bearing housings, end caps, respectively.
The relative positions of the supporting units can be correspondingly adjusted according to actual working conditions, so that stress of each part of the test device is more reasonable.
The dual rotor test stand may further comprise a base, and the support unit may be disposed on the base, more specifically, may be disposed on the base through a bearing seat.
Further, the supporting unit can be the movable supporting unit that sets up in on the base, so set up, can rationally arrange the position of supporting unit on the base according to the object specific condition of experimental test, and then make the relative position of supporting unit and actual operating mode do the adaptation to make each position atress of test bench more reasonable. The base is provided with a sliding rail, and the supporting unit is slidably connected with the sliding rail through a sliding block arranged on the bearing seat, and can be provided with other movable setting schemes.
Furthermore, the aviation double-rotor test stand further comprises a limiting structure for limiting the movement of the supporting unit, so that the position of the supporting unit can be fixed after the position of the supporting unit is adjusted.
In this application, do not set up the intermediate bearing that plays support connection effect between the high low pressure rotor, decoupling formula sets up promptly for need not the mutual restriction on the test speed of high low pressure rotor, and then the selection of the implementable test speed of two is more freely extensive, and holistic, the test bench that this application provided need not to carry out test on the whole board, and test device scale can not be too big, and the cost can not be improved.
Referring to fig. 1 to 9, in one embodiment, an aviation dual-rotor test stand comprises a rotor unit, a driving unit and a supporting unit, specifically may include a high-speed motor, a blowing device, a high-pressure rotor shaft, a low-pressure rotor shaft, two first supporting units and two second supporting units, the high-speed motor drives the low-pressure rotor to rotate through a coupling, the motor can achieve continuous speed regulation from 0 to a target maximum rotation speed, the high-pressure rotor and the low-pressure rotor can be respectively supported through a pair of first supporting units and second supporting units including a supporting component and a rolling bearing, the turbine blades of the high-pressure turbine wheel are designed to simulate blades, specifically may be as shown in fig. 9, the air blowing device blows air to the simulation blades to drive the high-pressure rotor to rotate, the air blowing device drives the high-pressure rotor to rotate, so that the configuration of a motor of the test bed is reduced, the cost is lowered, and meanwhile, the double-rotor structure of the aeroengine can be simulated more truly, the high-pressure rotor, the low-pressure rotor, the rolling bearings, each wheel disc and other components are assembled to be highly concentric, so that the vibration quantity caused by unbalanced force of the rotor system in the running process is ensured to be minimum, the unbalanced precision grade standard of the rotating machinery is met, the double-rotor test bed can simulate the double-rotor structure system of the aeroengine to a great extent at least in the aspects of rotating speed and pneumatic rotation of the high-pressure rotor, and has the advantages of scientific structure, simple process, few components, light weight, low cost, high rotating speed and easy popularization, and can be used for carrying out experiments of dynamic characteristics of the bearing-rotor system, the method is suitable for scientific researchers to develop related works of structural optimization design of the double-rotor system of the aero-engine.
Referring to fig. 1 to 9, in another embodiment, an aviation dual-rotor test stand includes components such as a high-speed motor, a coupling, a low-pressure rotor front support rolling bearing, a low-pressure compressor wheel disc, a low-pressure rotor shaft, a low-pressure turbine wheel disc, a low-pressure rotor rear support rolling bearing, a high-pressure compressor wheel disc, a high-pressure rotor front support rolling bearing, a high-pressure rotor shaft, a high-pressure turbine wheel disc, a high-pressure rotor rear support rolling bearing, and an air blowing device, wherein a turbine blade of the high-pressure turbine wheel disc can be designed as a simulation blade, and the simulation blade has a simple structure and convenient design compared with a real blade of an aeroengine, and the material cost and the processing technology are also greatly reduced; the high-pressure rotor is supported by the front and rear support rolling bearings of the high-pressure rotor, and the low-pressure rotor is supported by the front and rear support rolling bearings of the low-pressure rotor; the high-pressure rotor, the low-pressure rotor, the supporting rolling bearing, the wheel disc and other components are highly concentric during assembly; during the test, the test bed starts the high-speed motor to drive the low-pressure rotor to rotate through the coupler, the test bed starts the air blowing device to drive the high-pressure rotor to rotate through blowing air to the simulation blade, namely the simulation blade rotates at a high speed under the aerodynamic force generated by the air blowing device, so as to drive the high-pressure rotor to rotate at a high speed, wherein the air blowing power of the air blowing device can be adjusted, namely the rotating speed of the high-pressure rotor can be adjusted, the front support rolling bearing of the low-pressure rotor, the rear support rolling bearing of the low-pressure rotor, the front support rolling bearing of the high-pressure rotor and the rear support rolling bearing of the high-pressure rotor are support units, the specific structures of the support units can be as shown in fig. 1, and the air blowing device drives the high-pressure rotor to rotate, and the high-speed motor drives the low-pressure rotor to rotate; the high-pressure rotor is driven by gas, the test device can simulate the double-rotor structure of the aero-engine more truly, and a reference basis is provided for the structural optimization of the double-rotor system.
The novel double-rotor test bed provided by the utility model effectively solves the problems that the motor of the driving equipment of the industrial court test device is expensive in multiple price and the double-rotor system of the aeroengine is difficult to truly simulate by the university test device. Specifically, the test bed can be used for carrying out an inherent vibration characteristic experiment of a rotor system, a vibration response experiment of the rotor system, a model verification and state monitoring experiment of a fault rotor system, a dynamic experiment of a rolling bearing and the like, and can effectively promote the structural optimization design of the double-rotor system of the aero-engine and the research of the dynamic characteristics of key parts.
It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other.
The foregoing is merely exemplary of the present application and is not intended to limit the present application. Various modifications and changes may be made to the present application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc. which are within the spirit and principles of the present application are intended to be included within the scope of the claims of the present application.
Claims (9)
1. A bearing support assembly, comprising:
the bearing seat is provided with a hollow cavity;
the multiple end covers comprise a mounting part in a circular ring shape and an insertion part which extends from the circular ring surface to one side to form a cavity and is communicated with the hollow part of the circular ring, the insertion part is inserted into the hollow cavity and is mounted on the bearing seat through the mounting part, the insertion part is used for mounting a bearing support bearing, the multiple end covers are different in at least one aspect of the structural size and the morphological structure type of the insertion part, and the multiple end covers are used for adapting to different bearings in a switching mode.
2. A bearing support assembly according to claim 1, wherein the morphological structure type of the insert comprises a squirrel cage structure, an elastic ring structure, a hollow cylindrical structure with a complete circumferential envelope.
3. A bearing support assembly according to claim 1 or claim 2, wherein the bearing housing and end cap are provided with corresponding screw-on formations.
4. An aviation dual rotor test stand, comprising:
the rotor unit comprises a low-pressure rotor and a high-pressure rotor arranged outside the low-pressure rotor;
the driving unit comprises a first driving unit which is in transmission connection with the low-pressure rotor and is used for driving the low-pressure rotor, and a second driving unit which is used for driving the high-pressure rotor;
the support unit is used for supporting the rotor unit and comprises a first support unit and a second support unit, wherein the first support unit is used for supporting the low-pressure rotor and is rotationally connected with the low-pressure rotor, and the second support unit is used for supporting the high-pressure rotor and is rotationally connected with the high-pressure rotor;
wherein the first support unit and/or the second support unit comprises a bearing support assembly according to any one of claims 1-3.
5. The aircraft birotor test stand of claim 4, further comprising a base, wherein the support unit is disposed on the base.
6. The aircraft birotor test stand of claim 5, wherein the support unit is a movable support unit disposed on the base.
7. The aircraft birotor test stand of claim 6, further comprising a limiting structure limiting movement of the support unit.
8. The aircraft birotor test stand of claim 4, wherein the first drive unit comprises a high speed motor drivingly connected to the low voltage rotor via a coupling.
9. An aeronautical birotor test stand according to any of claims 4-8, wherein the second drive unit comprises a blowing device for providing high pressure rotor rotational power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310474263.5A CN116539307A (en) | 2023-04-28 | 2023-04-28 | Bearing support assembly and aviation double-rotor test stand applying same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310474263.5A CN116539307A (en) | 2023-04-28 | 2023-04-28 | Bearing support assembly and aviation double-rotor test stand applying same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116539307A true CN116539307A (en) | 2023-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310474263.5A Pending CN116539307A (en) | 2023-04-28 | 2023-04-28 | Bearing support assembly and aviation double-rotor test stand applying same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116539307A (en) |
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2023
- 2023-04-28 CN CN202310474263.5A patent/CN116539307A/en active Pending
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