CN115184004A - Aviation birotor test bench - Google Patents
Aviation birotor test bench Download PDFInfo
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- CN115184004A CN115184004A CN202211094140.0A CN202211094140A CN115184004A CN 115184004 A CN115184004 A CN 115184004A CN 202211094140 A CN202211094140 A CN 202211094140A CN 115184004 A CN115184004 A CN 115184004A
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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
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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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Abstract
The application discloses aviation birotor test bench includes: 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 supporting unit is used for supporting the rotor unit and comprises a first supporting unit and a second supporting unit, the first supporting unit is used for supporting the low-pressure rotor and is connected with the low-pressure rotor in a rotating mode, and the second supporting unit is used for supporting the high-pressure rotor and is connected with the high-pressure rotor in a rotating mode. Two rotors in the rotor unit only set up through the support mode that two different support element supported respectively, still include the associative support setting of intermediary bearing between two rotors among the prior art that compares, the rotational speed range that the rotational speed between two rotors of test bench of this application no longer restricts testable each other is wider.
Description
Technical Field
The application relates to the technical field of aero-engines, in particular to an aviation dual-rotor test bed.
Background
The aero-engine, called the heart of the aero-device, is one of the important elements determining the performance, reliability and economy of the aero-device, wherein the arrangement mode of the dual sub-structure is the most common one, and the relevant experimental research on the structure has become one of the important research contents in the field. The cost of performing the tests using actual engines in such test studies is high and there is a great risk that many of the test studies are performed using rotor test stands.
The invention patent with the application number of CN201810221382.9 discloses a pneumatic turbine driven type double-rotor test bed which comprises a rotor system, a power system, a lubricating system, a test system and a safety system, wherein an intermediate bearing is arranged between an inner rotor and an outer rotor, the outer rotor is driven by the pneumatic turbine, the control system is a feedback control system, the pneumatic turbine arranged on the outer rotor is driven by compressed air, the compressed air provided by an air compressor enters a pressure stabilizing box, flows through a pressure regulating valve and then flows out of a nozzle to impact the pneumatic turbine to drive the pneumatic turbine to rotate, a rotating speed transmitter detects the rotating speed of the outer rotor and feeds the rotating speed back to a rotating speed controller, the flow of the compressed air is regulated by controlling the opening of the pressure regulating valve to control the rotating speed of the outer rotor, and the device can be used for the experimental research on the power characteristics of a double-rotor-support system coupled with the inner rotor and the outer rotor and for the simulation and research on the vibration fault of an aircraft engine and the rotor system thereof.
The utility model patent with the application number of CN202121810468.9 discloses a double-rotor test bed which avoids the influence of a drive end motor shaft coupling, and comprises an outer rotor and an inner rotor, wherein the support base comprises a first base, a second base, a third base and a fourth base; one end of the inner rotor is rotatably connected with the first base, the middle part of the inner rotor is rotatably connected with the second base, and the other end of the inner rotor is rotatably connected with the fourth base after sequentially penetrating through the through holes of the third base and the outer rotor; one end of the outer rotor is rotatably connected with the third base, and the other end of the outer rotor is connected with the inner rotor through an intermediate bearing; the inner rotor is fixedly provided with a toothed belt wheel I between the first base and the second base, the outer rotor is fixedly provided with a toothed belt wheel II, and the toothed belt wheel I and the toothed belt wheel II are respectively connected with a servo motor through synchronous toothed belts.
It can be seen that, intermediary bearings are arranged between the inner rotor and the outer rotor of the test bed in the above patent, and the intermediary bearings can play a role in supporting and connecting, but the arrangement of the intermediary bearings also enables the rotating speeds of the inner rotor and the outer rotor to meet a certain proportion, so that the applicable range of the test rotating speeds of the inner rotor and the outer rotor is limited.
Therefore, it is desirable to provide a related solution that can make the range of testing speeds that can be performed by the two rotors of the dual-rotor testing stand wider.
Disclosure of Invention
The embodiment of the application provides a relative technical scheme which can enable two rotors of a double-rotor test bed to implement a wider test speed range, so that the problem that in the prior art, the speed of two rotors of the double-rotor test bed which can be implemented in a test is limited due to the arrangement of an intermediate bearing is solved.
The application provides an aviation birotor test bench includes:
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 supporting unit is used for supporting the rotor unit and comprises a first supporting unit and a second supporting unit, the first supporting unit is used for supporting the low-pressure rotor and is connected with the low-pressure rotor in a rotating mode, and the second supporting unit is used for supporting the high-pressure rotor and is connected with the high-pressure rotor in a rotating mode.
Further, in a preferred embodiment provided by the present application, the support unit further includes a base, and the support unit is disposed on the base.
Further, in a preferred embodiment provided by the present application, the supporting unit is a supporting unit movably disposed on the base.
Further, in a preferred embodiment provided by the present application, a limiting structure for limiting the movement of the supporting unit is further included.
Further, in a preferred embodiment provided herein, the aviation dual-rotor test bed comprises a first support unit and/or a second support unit, wherein the first support unit and/or the second support unit comprises:
a bearing;
a bearing support assembly;
wherein, bearing support assembly includes:
the bearing seat is provided with a hollow cavity;
a plurality of end covers, every end cover including the installation department that is the ring form, extend to one side from the ring and form have the cavity just the cavity with the portion of inserting of the hollow department intercommunication of ring, the portion of inserting inserts in the well cavity, and pass through on the bearing frame is installed to the installation department, the portion of inserting is used for the installation to bear support bearing, a plurality of end covers are different on the one hand at least in the structure size of portion of inserting, the morphological structure type, and the switching of a plurality of end covers uses in order to adapt to different bearings.
Further, in a preferred embodiment provided by the present application, the shape structure type of the insertion portion includes a squirrel cage structure, an elastic ring structure, and a hollow cylindrical structure with a complete circumferential envelope surface.
Further, in a preferred embodiment provided by the present application, the bearing seat and the end cover are correspondingly provided with a bolt connection structure.
Further, in a preferred embodiment provided by the present application, the first driving unit includes a high-speed motor, and the high-speed motor is in transmission connection with the low-pressure rotor through a coupling.
Further, in a preferred embodiment provided by the present application, the second driving unit includes an air blowing device for providing a rotational power of the high pressure rotor.
The embodiment provided by the application has at least the following beneficial effects:
the test bench does not have an intermediate bearing, only supports the arrangement mode of the low-pressure rotor and the high-pressure rotor respectively and independently through the first supporting unit and the second supporting unit, so that the speed of the two rotors is not restricted with each other, and the range of the testing speed of the two rotors of the double-rotor test bench can be wider, and the application range of the test bench is wider.
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 embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
fig. 1 is a schematic structural diagram of an aviation dual-rotor test bed provided in an embodiment of the present application;
FIG. 2 is a schematic turbine structure diagram of a high pressure rotor according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of a bearing support assembly and a bearing assembly structure according to an embodiment of the present disclosure;
FIG. 4 isbase:Sub>A schematic view of the assembled structure of FIG. 3 taken along A-A;
fig. 5 is a partial schematic structural view of an end cap provided in an embodiment of the present application, cut along a central axis thereof;
fig. 6 is a schematic perspective view of an insertion portion of an end cap according to an embodiment of the present disclosure;
FIG. 7 is a schematic structural diagram of an end cap according to an embodiment of the present disclosure at a viewing angle;
FIG. 8 is a perspective view of an insert portion of another end cap according to an embodiment of the present disclosure;
fig. 9 is a schematic structural view of the three-dimensional structure of the insertion portion in fig. 8 from one perspective.
2. Low-pressure rotor
20. Low-pressure rotor shaft
22. Low-pressure compressor wheel disc
24. Low-pressure turbine wheel disc
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
10. First support unit
12. Second supporting unit
14. Coupling device
0. Bearing seat
00. Bearing seat screw hole
3. End cap
30. Mounting part
302. Epitaxial structure
32. Insertion part
34. End cover screw hole
5. Bearing assembly
50. Bearing inner ring
52. Bearing rolling body
54. And (4) a bearing outer ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it is to be noted that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the system or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application unless otherwise specified. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description of the present application, it is to be noted that, unless explicitly set and defined otherwise, the terms "mounted", "connected" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description of the present application, it is to be noted that unless explicitly set forth or limited otherwise, the terms "first", "second", and the like are merely used for convenience in describing the present application and simplifying the description, but are not used for limiting the present application unless otherwise specified. The terms used in this application are to be understood as meaning specifically in this application to the extent that one of ordinary skill in the art would understand them.
In the description of the present application, it is to be noted that, unless explicitly set and defined otherwise, terms such as "one end", "the other end", and the like are merely used for convenience in describing the present application and simplifying the description, and descriptions made for distinguishing different ends of the same object are not used for limiting the present application. The specific meaning of the terms in this application will be understood in a particular context to those of ordinary skill in the art.
Modern turbojet or turbofan engines mostly adopt a dual-rotor or even three-rotor structure, wherein the dual-rotor structure is more common, in order to explore the dynamic characteristics of an aircraft engine rotor system, a research organization usually builds a rotor test bed the same as an aircraft engine supporting structure, and then develops related researches such as rotor dynamic characteristic tests to obtain related test data so as to provide basis for optimizing the aircraft engine rotor system structure.
As shown in FIG. 1, the application provides an aviation dual-rotor test bed which can comprise a rotor unit, a driving unit and a supporting unit.
The rotor unit can be a high-pressure rotor 4 which comprises a low-pressure rotor 2 and is arranged 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 include a high pressure rotor shaft 40, a high pressure compressor disk 42, and a high pressure turbine disk 44, the blades of which may be arranged in a simulated manner as shown in fig. 2.
And the driving unit comprises a first driving unit 6 which is in transmission connection with the low-pressure rotor 2 and is used for driving the low-pressure rotor 2 and a second driving unit 8 which is used for driving the high-pressure rotor 4.
Specifically, the first driving unit may include a high-speed motor, the high-speed motor may be in transmission connection with the low-pressure rotor 2 through a coupler 14, and in actual 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 can achieve continuous adjustability from 0 to a target maximum rotation speed; the second driving unit can comprise an air blowing device, the air blowing device provides rotating power of the high-pressure rotor 4, and the air blowing device is selected to be preferentially used according to needs; the arrangement of only one motor can also solve the problem of overhigh cost caused by that a high-low voltage motor is adopted by a double-rotor testing device built in relevant institutions of the aeroengine industry and the like to drive a high-low voltage rotor respectively in the prior art.
The supporting unit is used for supporting the rotor unit and comprises a first supporting unit 10 and a second supporting unit 12, the first supporting unit is used for supporting the low-pressure rotor 2 and is connected with the low-pressure rotor in a rotating mode, and the second supporting unit 12 is used for supporting the high-pressure rotor 4 and is connected with the high-pressure rotor in a rotating mode.
Specifically, as shown in fig. 1, the supporting unit may include a plurality of first supporting units 10 and a plurality of second supporting units 12, and more specifically, may include two first supporting units 10 and two second supporting units 12, where one of the two first supporting units 10 may be disposed between the coupling 14 and the low-pressure compressor wheel disc 22 and rotatably connected to one end of the low-pressure rotor shaft 20, the other may be disposed at the other end of the low-pressure rotor shaft 20, one of the two second supporting units 12 may be disposed at one end of the high-pressure rotor shaft 40 and rotatably connected to the rotor shaft, and the other may be disposed at the other end of the high-pressure rotor shaft 40.
The supporting unit may specifically include a rolling bearing and a bearing seat, that is, the high-pressure rotor and the low-pressure rotor may be supported by a pair of rolling bearings provided with the bearing seat, respectively.
The relative position of the supporting unit can be correspondingly adjusted according to the actual working condition, so that the stress of each part of the test device is more reasonable.
The dual-rotor test bed also comprises a base, wherein the supporting unit is arranged on the base, and more specifically, the supporting unit is arranged on the base through a bearing seat.
Furthermore, the supporting unit can be movably arranged on the supporting unit on the base, so that the positions of the supporting units on the base can be reasonably arranged according to the specific conditions of the test object, and the relative positions of the supporting units are adapted to the actual working conditions, so that the stress of all parts of the test bed is more reasonable. The base can be provided with a slide rail, the supporting unit is connected with the slide rail in a sliding way through a slide block arranged on the bearing seat, and other movable arrangement schemes can also be adopted.
Furthermore, the aviation dual-rotor test bed further comprises a limiting structure for limiting the movement of the supporting unit, so that the supporting unit can be fixed after the position of the supporting unit is adjusted.
In an aviation dual-rotor test bed of any one of the above applications, the first supporting unit and/or the second supporting unit may further include: a bearing; a bearing support assembly; wherein, bearing support assembly includes: the bearing seat is provided with a hollow cavity; the end cover comprises an installation part and an insertion part, the insertion part is inserted into the hollow cavity and is installed on the bearing seat through the installation part, and the insertion part is used for installing and bearing the supporting bearing.
The morphological structure type of the insertion part can be a squirrel cage structure, an elastic ring structure and a hollow columnar structure with a complete circumferential envelope surface.
The bearing seat and the end cover can be correspondingly provided with screw connection structures.
As shown in the drawings, fig. 3 isbase:Sub>A schematic view ofbase:Sub>A bearing support assembly andbase:Sub>A bearing assembly structure provided in an embodiment of the present application, fig. 4 isbase:Sub>A schematic view of the assembly structure in fig. 3 taken alongbase:Sub>A-base:Sub>A, fig. 5 isbase:Sub>A partial structural view of an end cover provided in an embodiment of the present application taken alongbase:Sub>A central axis, fig. 6 isbase:Sub>A schematic view ofbase:Sub>A three-dimensional structure of an insertion portion of an end cover provided in an embodiment of the present application, fig. 7 isbase:Sub>A schematic view ofbase:Sub>A structure of an end cover provided in an embodiment of the present application, fig. 8 isbase:Sub>A schematic view ofbase:Sub>A three-dimensional structure of an insertion portion of another end cover provided in an embodiment of the present application, fig. 9 isbase:Sub>A schematic view ofbase:Sub>A three-dimensional structure of an insertion portion in fig. 8, and in particular, fig. 5 isbase:Sub>A schematic view ofbase:Sub>A partial structure of an end cover provided in fig. 4 taken alongbase:Sub>A central axis, fig. 7 isbase:Sub>A schematic view ofbase:Sub>A structure of an insertion portion inbase:Sub>A specific perspective view in fig. 6, fig. 7 may bebase:Sub>A structural view, fig. 8 and fig. 9 may bebase:Sub>A structural view of an elastic ring structure, and fig. 8 and fig. 9 may bebase:Sub>A structural schematic view of an elastic ring structure, in the present application,base:Sub>A bearing support assembly may includebase:Sub>A plurality of cage housings 0 andbase:Sub>A plurality of bearing housings.
The bearing seat 0 is provided with a hollow cavity, a screw connection structure can be arranged at one end of the bearing seat, and the screw connection structure can be a bearing seat screw hole 00.
A plurality of end covers, every end cover 3 including be the installation department 30 of ring form, extend to one side from the ring and form have the cavity just the cavity with the portion of inserting 32 of the hollow department intercommunication of ring, portion of inserting 32 inserts in the well cavity and pass through on the bearing frame is installed to installation department 30, portion of inserting 32 is used for the installation to bear support bearing 5, a plurality of end covers 3 are different on the one hand in the structure size of portion of inserting 32, the morphological structure type at least, and the switching of a plurality of end covers 3 uses and is used for adapting to different bearing 5. Specifically, the end cover 3 may be a screw connection structure which is arranged by itself and corresponds to a screw connection structure arranged at one end of the bearing seat, and is connected and mounted on the bearing seat by a connecting piece; the insertion portion 32 may be a structure extending from the circular ring surface of the mounting portion 30 to one side, and having a cavity, where the cavity is communicated with the hollow portion of the mounting portion, specifically, as shown in fig. 4 and 5; the outer diameter of the mounting portion 30 may be larger than the outer diameter of the insertion portion 32, as shown in fig. 4 and 5, an example in which the outer diameter of the mounting portion 30 is larger than the outer diameter of the insertion portion 32 is shown, in fig. 4 and 5, an annular region where the outer diameter of the mounting portion 30 exceeds the outer diameter of the insertion portion 32 is an extension structure 302, and in this example, the extension structure 302 may serve as a limiting part for setting a screwing structure; the inner diameter of the mounting portion 30 may be smaller than the inner diameter of the insertion portion 32, and fig. 4 and 5 show an example in which the inner diameter of the mounting portion 30 is smaller than the inner diameter of the insertion portion 32, and in this example, the mounting portion may play a role of dust prevention for a bearing mounted in the insertion portion cavity.
The outer diameter of the mounting part 30 and the outer diameter of the inserting part 32 may be the same, at this time, the end cover screw hole 34 of the screw connection structure on the end cover may be arranged along the radial direction of the mounting part, at this time, the mounting part 30 and the inserting part 32 can be inserted into the hollow cavity of the bearing seat, the bearing seat screw hole 00 is correspondingly arranged, and the connecting piece for connecting the mounting part 30 and the bearing seat 0 can play a role in limiting in addition to the 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 of the end cap screw hole 34 on the end cap may be disposed on the extension structure 302 and along the axis direction of the mounting portion, at this time, only the insertion portion 32 may be inserted into the hollow cavity of the bearing seat, and the specific arrangement of the bearing seat screw hole 00 and the end cap screw hole 34 is shown in fig. 4 and 5.
The form structure type of the insertion part 32 can be a squirrel cage structure or an elastic ring structure; specifically, the squirrel-cage structure may be as shown in fig. 6 and 7, and the elastic ring structure may be as shown in fig. 8 and 9, and the rigidity of the insertion portions 32 of these two types of structures may be adjusted by the width of the ribs arranged axially, the distance between the ribs, and the like; the insert 32 may also be a hollow cylindrical structure with a complete circumferential envelope surface; when the bearing test device is used, the bearing test device can be selected according to the characteristic requirements of a test bearing, an elastic ring type structure is selected for a bearing with high rigidity under the common condition, and a squirrel-cage type structure or a hollow columnar structure with a complete circumferential envelope surface is selected for a bearing with low rigidity.
In the above, the bearing 5 may include the bearing inner ring 50, the bearing rolling elements 52, and the bearing outer ring 54; in the rigidity calculation, the rigidity = load/deformation, when the assembly is used, the bearing seat 0, the end cover 3 and the bearing 5 can be concentrically arranged, and at the moment, in the supporting structure formed by the three components, the bearing rigidity K is 1 Rigidity K of end cover 2 The bearing and the end cover are in parallel connection, the total rigidity of a supporting system formed by the bearing and the end cover is K, and then the calculation formula is as follows:
K= K 1 K 2 /( K 1 +K 2 )
therefore, according to the requirement of a test task, the total rigidity K of the supporting system is along with the end cover K 2 The rigidity of the end cover can be adjusted in a adaptability mode according to the changed characteristics, and therefore the effect of adjusting the supporting rigidity of the supporting system can be achieved.
Referring to fig. 3 to 9, in one embodiment, a supporting structure includes a bearing and any one of the bearing support assemblies mentioned in the present application, that is, the supporting structure may include a bearing seat 0, an end cap 3, and a bearing 5, the bearing 5 is installed in the end cap 3, and the end cap 3 is installed on the bearing seat, specifically, an insertion portion 32 of the end cap 3 is disposed in the bearing seat 0 and is installed on the bearing seat 0 through an installation portion 30, and the bearing 5 is installed in the insertion portion 32 of the end cap 3; when in use, the end cover 3 can be adapted to bearings 5 of different types and specifications by adjusting and designing one aspect of the structural size and the morphological structure type of the insertion portion 32, specifically, the end cover kit can be manufactured into various structural sizes and/or various morphological structure types, and is selected and used according to the specification type of the bearing 5 during testing, so that compared with a mode of directly supporting the bearing through a bearing seat in the prior art, the universality of the support assembly mentioned in the application is improved, and the replacement is relatively convenient, wherein the structural size adjustment is specifically to change at least one of the radial inner diameter size and the radial outer diameter size of the insertion portion 32 of the end cover 3, the morphological structure type change refers to the switching use among a squirrel-cage structure, an elastic ring structure and a hollow columnar structure with a complete circumferential envelope surface, and the switching use on the morphological structure type is mainly used for changing the support rigidity of a support system of the support structure, so as to perform a expansibility bearing related performance test; specifically, the end cap 3 may be connected to the bearing seat 0 by a bolt or a screw, and the main components such as the bearing seat 0, the end cap 3, and the bearing 5 may be kept highly concentric during installation and integration, that is, during design, the coaxiality between the inner and outer profiles of the bearing seat 0 and the end cap 3 and the bearing 5 needs to be controlled, and the main components such as the bearing seat 0, the end cap 3, and the bearing 5 are kept highly concentric during installation and integration, so that a test apparatus using the support structure can cover a large rotation speed working condition. The supporting structure is scientific and reasonable in overall structure, simple and convenient in production process and easy to popularize, the bearing seat 0 can be repeatedly used without replacement, the test cost is greatly reduced, and the supporting structure can be widely applied to bearing test research of rotary equipment.
It can be understood, the bearing support subassembly that this application provided, end cover 3 has the function of connecting, sealing, regulation bearing support system support rigidity concurrently, through the end cover structural dimension, the change of global rigidity can be realized in the adjustment of morphological structure type, can play the effect of adjusting the support system global support rigidity characteristic, can develop more support performance tests when accomplishing bearing performance test, can be in order to understand end cover support bearing, so the end cover can be selected according to experimental demand adjustment, thereby adjust the support system's of the bearing structure including bearing, bearing frame, end cover support rigidity, with the support characteristic of adjusting the bearing structure including the bearing, and then the bearing performance test of developing of expansibility. Compared with bearing test devices built in aeroengine industry relevant institutions and all higher institutions, the end cover 3 with the characteristics is introduced into the support assembly for the first time, and the multifunctional and reusable characteristics of the test device using the support assembly can be fully realized. The support assembly is relatively simple and saves a large amount of money in construction and construction costs.
In this application, do not set up the intermediary bearing who plays support connection effect between the high low pressure rotor, the decoupling type setting promptly for need not mutual restriction in the test speed of high low pressure rotor, and then the two selection that can implement test speed more freely wide range, holistic, the test bench that this application provided need not whole machine bench and carries out the test, and the testing arrangement scale can not be too big, and the cost can not improved.
Referring to fig. 1 to 9, in an embodiment, an aviation dual-rotor test bed includes a rotor unit, a driving unit, and support units, which may specifically include a high-speed motor, an air blowing device, a high-pressure rotor shaft, a low-pressure rotor shaft, two first support units, two second support units, a high-pressure compressor wheel disc, a high-pressure turbine wheel disc, a low-pressure compressor wheel disc, and a low-pressure turbine wheel disc, the high-speed motor drives the low-pressure rotor to rotate through a coupler, the motor may achieve a continuous speed adjustment from 0 to a target maximum rotation speed, the high-pressure rotor and the low-pressure rotor may be supported by a pair of first support unit and a second support unit including a bearing support assembly and a rolling bearing, respectively, turbine blades of the high-pressure turbine wheel disc are designed to simulate blades, and specifically may be as shown in fig. 2, the air blowing device blows air to the simulation blades to drive the high-pressure rotor to rotate, the arrangement of the air blowing device driving the high-pressure rotor to rotate at least can reduce the cost of the configuration of the test bed motor and lower the cost, and can simulate the double-rotor structure of the aircraft engine more truly, the high-pressure rotor, the low-pressure rotor, the rolling bearing, each wheel disc and other parts are highly concentric when being assembled so as to ensure that the vibration quantity caused by unbalanced force is minimum in the running process of a rotor system and meet the unbalanced precision grade standard of rotating machinery, the double-rotor test bed can truly simulate a double-rotor structure system of an aircraft engine to a great extent at least in the aspects of rotating speed and pneumatic rotation of a high-pressure rotor, has scientific structure, simple and convenient process, few components, light weight, low cost, high rotating speed and easy popularization, the method can be used for carrying out experiments such as dynamic characteristics of a bearing-rotor system and the like, and is suitable for carrying out relevant work of structure optimization design of the double-rotor system of the aircraft engine by researchers.
Referring to fig. 1 to 9, in another embodiment, an aviation dual-rotor test bed comprises a high-speed motor, a coupler, a low-pressure rotor front supporting rolling bearing, a low-pressure compressor wheel disc, a low-pressure rotor shaft, a low-pressure turbine wheel disc, a low-pressure rotor rear supporting rolling bearing, a high-pressure compressor wheel disc, a high-pressure rotor front supporting rolling bearing, a high-pressure rotor shaft, a high-pressure turbine wheel disc, a high-pressure rotor rear supporting rolling bearing, an air blowing device and the like, wherein turbine blades of the high-pressure turbine wheel disc can be designed to be simulation blades, the simulation blades are simpler in structure and more convenient to design than real blades of an aero-engine, and the material cost and the processing technology are also greatly reduced; the high-pressure rotor is supported by the front and rear supporting rolling bearings of the high-pressure rotor, and the low-pressure rotor is supported by the front and rear supporting rolling bearings of the low-pressure rotor; the high-pressure rotor, the low-pressure rotor, the supporting rolling bearing, the wheel disc and other parts are highly concentric during assembly; during testing, 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 blades, namely the simulation blades rotate at a high speed under the action of aerodynamic force generated by the air blowing device, so that the high-pressure rotor is driven 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 low-pressure rotor front supporting rolling bearing, the low-pressure rotor rear supporting rolling bearing, the high-pressure rotor front supporting rolling bearing and the high-pressure rotor rear supporting rolling bearing are supporting units, and the specific structures of the supporting units can be as shown in fig. 3.
According to the double-rotor driving arrangement scheme, the high-pressure rotor is driven to rotate by the blowing device, and the low-pressure rotor is driven to rotate by the high-speed motor, so that the test bed only comprises one motor, the structure is relatively simple, and the manufacturing cost is reduced; the high-pressure rotor is driven by gas, and the test device can simulate the double-rotor structure of the aircraft engine more truly and provide reference basis for the structural optimization of a double-rotor system.
The novel double-rotor test bed provided by the invention effectively solves the problems that the motor of the driving device of the test device in the industrial colleges is expensive, and the test device in the colleges and universities is difficult to truly simulate the double-rotor system of the aero-engine. Specifically, the test bed can be used for an inherent vibration characteristic experiment of a developed rotor system, a vibration response experiment of a 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 optimization design of a double-rotor system structure of an aircraft engine and the research of the dynamic characteristics of key components.
It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict.
The above description is only an example of the present application and is not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement or the like made within the spirit and principle of the present application shall be included in the scope of the claims of the present application.
Claims (9)
1. The utility model provides an aviation birotor test bench which characterized in that includes:
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 supporting unit is used for supporting the rotor unit and comprises a first supporting unit and a second supporting unit, the first supporting unit is used for supporting the low-pressure rotor and is connected with the low-pressure rotor in a rotating mode, and the second supporting unit is used for supporting the high-pressure rotor and is connected with the high-pressure rotor in a rotating mode.
2. The aerial dual-rotor test bed as claimed in claim 1, further comprising a base, wherein the supporting unit is disposed on the base.
3. The aerial double-rotor test bed as claimed in claim 2, wherein the supporting unit is a supporting unit movably arranged on the base.
4. The dual rotor aerial test rig of claim 3, further comprising a restraint structure that restrains movement of the support unit.
5. The dual-rotor airborne test stand according to any one of claims 1-4, wherein said first and/or second support unit comprises:
a bearing;
a bearing support assembly;
wherein, bearing support assembly includes:
the bearing seat is provided with a hollow cavity;
a plurality of end covers, every end cover including the installation department that is the ring form, extend to one side from the ring and form have the cavity just the cavity with the portion of inserting of the hollow department intercommunication of ring, the portion of inserting inserts in the well cavity, and pass through on the bearing frame is installed to the installation department, the portion of inserting is used for the installation to bear support bearing, a plurality of end covers are different on the one hand at least in the structure size of portion of inserting, the morphological structure type, and the switching of a plurality of end covers uses in order to adapt to different bearings.
6. The aviation dual-rotor test rig according to claim 5, wherein the insert portion is of a morphological structure type comprising a squirrel cage structure, an elastic ring structure, a hollow cylindrical structure with a complete circumferential envelope.
7. The aerial double-rotor test bed as claimed in claim 5, wherein the bearing seat and the end cover are correspondingly provided with a bolt connection structure.
8. The aerial dual-rotor test rig of claim 1, wherein the first drive unit comprises a high-speed motor, the high-speed motor being in driving connection with the low-pressure rotor through a coupling.
9. The aerial dual-rotor test rig of claim 1, wherein the second drive unit includes a blower for providing high pressure rotor rotational power.
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