CN201724799U - Vibration tester for inner-outer rotor systems - Google Patents
Vibration tester for inner-outer rotor systems Download PDFInfo
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- CN201724799U CN201724799U CN2010202607158U CN201020260715U CN201724799U CN 201724799 U CN201724799 U CN 201724799U CN 2010202607158 U CN2010202607158 U CN 2010202607158U CN 201020260715 U CN201020260715 U CN 201020260715U CN 201724799 U CN201724799 U CN 201724799U
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Abstract
The utility model relates to a vibration tester for inner-outer rotor systems, which belongs to the technical field of aeroengines. The vibration tester comprises an inner rotor and an outer rotor, the inner rotor is arranged in the outer rotor, the inner and the outer rotors are connected through intermediate bearings, and the outer rotor is connected with bearing pedestals through pedestal bearings; inner bearing covers are arranged on the inner sides of the bearing pedestals, outer bearing covers are arranged on the outer sides of the bearing pedestals, and the ends of the outer rotor are positioned in oil chambers; one end of the outer rotor is provided with a through hole, and the inner rotor at the end sequentially passes through the through hole of the outer rotor and the through hole of the outer bearing cover and is connected with a second coupling; the other end of the outer rotor is connected with one end of an outer rotor flange cover, and the other end of the outer rotor flange cover is connected with a first coupling via the through hole of the outer bearing cover; the end of the outer rotor flange cover connected with the outer rotor is provided with an oil guide hole, the outer circle of the outer rotor is provided with a shaft disk, and seals are arranged between the inner and the outer rotors at both ends of the outer rotor; and an eddy current sensor which is connected with an upper computer is arranged on the inner and the outer rotors or the shaft disk.
Description
Technical field:
The utility model belongs to the aero engine technology field, particularly relates to the vibration testing device of a kind of inner and outer rotors system.
Background technology:
Modern aeroengine adopts inside and outside many rotor-support-foundation systems version of arranging, wherein great majority are inner-outer birotor structures.Compare with common single rotor, multi-bearing rotor (tandem, run-in index), the arrangement form of this inner-outer birotor, the centrifugal force effect is more obvious aspect softening in firmization of stress and rotation, and the vibration behavior is more complicated.
In view of environment more complicated and the expense of aeromotor when the test run relatively more expensive, adopting the model test device is special-purpose test unit, some vibration faults to engine inner and outer rotors system carry out phenomenon simulation or reproduction, can significantly reduce experimentation cost, and can also play directive function to its manufacturing and repair procedures to a certain extent.
But, the version great majority of present existing vibration of rotor system test unit are single rotor or multi-bearing rotor (tandem and run-in index), on such test unit, carry out vibration test, can not truly reflect the fundamental vibration feature of the inner and outer rotors system of aeromotor.
For the vibration testing device of any plant equipment, the test unit of being set up must satisfy the principle of " three is similar ", that is: structural similarity, kinematic similarity and kinematic similarity as far as possible to actual machine.In order to carry out the vibration simulation test of aeroengine rotor system better,, need manufacture and design a kind of test unit that can simulate its vibration characteristics more truly equally at the design feature of aeromotor inner and outer rotors system.
The vibration testing device of inner and outer rotors system requires to satisfy the following aspects: structurally, it at first should be the inner and outer rotors system, its version is identical with actual machine, has so just eliminated to the full extent owing to the different test problems that cause of version; Aspect kinematics, inner and outer rotors is all simulated actual rotor and is rotated, and should reach the degree that can control as required aspect rotating speed, and realization and actual machine maximal phase are seemingly; Aspect vibration and dynamic test, test unit should change speed, the rigidity of rotor, and multi-form shaft coupling misaligns the different running statuses of simulated engine rotor-support-foundation system.
The utility model content:
In the inner and outer rotors system vibration The Study on Fault of aeromotor, can not effectively simulate the shortcoming of actual rotor system in order to overcome existing vibration of rotor system test unit, and the deficiency of aspect such as function singleness, the utility model provides a kind of vibration testing device that can effectively simulate the inner and outer rotors system of actual rotor system.
To achieve these goals, the utility model adopts following technical scheme, the vibration testing device of a kind of inner and outer rotors system, comprise internal rotor, outer rotor, described internal rotor is arranged on the inside of outer rotor, internal rotor is connected by intermediary's bearing with outer rotor, and described outer rotor is connected with bearing seat by block bearing; Inboard at bearing seat is provided with inside cap, in the arranged outside of bearing seat the outer bearing cover with through hole and oil pocket is arranged, and the end of described outer rotor is positioned at oil pocket; One end of described outer rotor has through hole, and the internal rotor of this end is connected with second shaft coupling by the through hole of outer rotor, the through hole of outer bearing cover successively; The other end of described outer rotor is connected with an end of outer rotor blind flange, and the other end of outer rotor blind flange is connected with first shaft coupling by the through hole of outer bearing cover; Be provided with oil guiding hole at the outer rotor blind flange end that links to each other with outer rotor, an end of described oil guiding hole is connected with oil pocket, and the other end is corresponding with the intermediary bearing; Outer setting at outer rotor has reel, and reel is fixed on by the spring axle sleeve on the cylindrical of outer rotor, is provided with first packoff between the internal rotor at described outer rotor two ends and outer rotor; Described internal rotor, outer rotor or reel are provided with current vortex sensor, and described current vortex sensor is connected with host computer.
Described internal rotor adopts hollow structure, and the hollow position place of the internal rotor of rotor flange lid end is provided with second packoff outside.
Described outer rotor is connected by screw with the outer rotor blind flange.
Described inside cap, outer bearing cover all are connected with bearing seat by screw.
The oil guiding hole of described outer rotor blind flange end is set to 6.
The beneficial effects of the utility model:
(1) vibration testing device structural similarity height of the present utility model has been avoided the invalidate the test that causes because of version difference;
(2) vibration testing device of the present utility model is easy to maintenance, and cost is low;
(3) is connected by the spring shaft cover between reel of the present utility model and the outer rotor, does not use the shaft shoulder to fix, can realize reel optional position fixing on the outer rotor cylindrical, the value volume and range of product of also convenient adjustment reel simultaneously is to satisfy different testing requirementss;
(4) internal rotor of the present utility model adopts hollow structure, with the similarity height of actual aeromotor structure, has also reduced the quality of test unit simultaneously on the structure, and has facilitated for some have the test (testing as cavity volume oil) of specific (special) requirements;
(5) have oil pocket in the outer bearing cover of the present utility model, provide pressure lubricating oil, for the running of intermediary's bearing and block bearing provides lubricated and cooling by hydraulic system; Wherein, utilize 6 oil guiding holes of outer rotor blind flange end can also satisfy lubricating requirement to intermediary's bearing.
Description of drawings:
Fig. 1 is the structural representation of vibration testing device of the present utility model;
Fig. 2 is the A portion enlarged diagram of Fig. 1;
Wherein, 1-block bearing; 2-intermediary bearing; 3-first shaft coupling; 4-spring axle sleeve; The 5-outer bearing cover; The 6-bearing seat; The 7-inside cap; The 8-reel; The 10-outer rotor; The 11-oil guiding hole; The 12-oil pocket; The 16-internal rotor; 17-outer rotor blind flange; 19-second shaft coupling; 23-first packoff; 24-second packoff; The 25-current vortex sensor; The 26-host computer.
Embodiment:
As shown in Figure 1 and Figure 2, the vibration testing device of a kind of inner and outer rotors system, comprise internal rotor 16, outer rotor 10, described internal rotor 16 is arranged on the inside of outer rotor 10, internal rotor 16 is connected by intermediary's bearing 2 with outer rotor 10, and described outer rotor 10 is connected with bearing seat 6 by block bearing 1; Be provided with inside cap 7 in the inboard of bearing seat 6, in the arranged outside of bearing seat 6 outer bearing cover 5 with through hole and oil pocket 12 arranged, the end of described outer rotor 10 is positioned at oil pocket 12; One end of described outer rotor 10 has through hole, and the internal rotor 16 of this end is connected with second shaft coupling 19 by the through hole of outer rotor 10, the through hole of outer bearing cover 5 successively; The other end of described outer rotor 10 is connected with an end of outer rotor blind flange 17, and the other end of outer rotor blind flange 17 is connected with first shaft coupling 3 by the through hole of outer bearing cover 5; Be provided with oil guiding hole 11 at outer rotor blind flange 17 ends that link to each other with outer rotor 10, an end of described oil guiding hole 11 is connected with oil pocket 12, and the other end is corresponding with intermediary bearing 2; Outer setting at outer rotor 10 has reel 8, and reel 8 is fixed on the cylindrical of outer rotor 10 by spring axle sleeve 4; Between the internal rotor 16 at described outer rotor 10 two ends and outer rotor 10, be provided with first packoff 23; Described internal rotor 16, outer rotor 10 or reel 8 are provided with current vortex sensor 25, and described current vortex sensor 25 is connected with host computer 26.Described outer rotor 10 and outer rotor blind flange 17 are connected by screw, and described inside cap 7, outer bearing cover 5 all are connected with bearing seat 6 by screw; Described internal rotor 16 adopts hollow structures, and the rotor flange hollow position place of covering the internal rotor 16 of 17 ends is provided with second packoff 24 outside; The oil guiding hole 11 of described outer rotor blind flange 17 ends is set to 6.
The epitrochanterian outside position of reel of the present utility model can be regulated by the spring shaft cover, thereby structurally satisfies the needs of experimental study.
The utility model before use, at first the outer end with the outer rotor blind flange is connected by the output shaft of first shaft coupling with a control motor; The outer end of internal rotor is connected by the output shaft of second shaft coupling with another control motor, controls inside and outside rotor respectively by two control motors and rotate.Two control motors are driver elements of test unit, employing be the ABB motor, model is QABPIC416 90L, rated power is 2.2kw.
Described intermediary bearing is selected deep groove ball bearing, and model is 61805, and packoff makes the inner oil pocket that forms of bearing cap, for block bearing and intermediary's bearing provide lubricated, and seals and can guarantee in the chamber that lubricating oil do not enter into inside and outside rotor and constituted.Described block bearing is selected deep groove ball bearing, and model is 61810.Because inside and outside rotor all is in the high speed rotating state in the process of the test, so reinforced seal is adopted in the sealing between bearing cap and the outer rotor, encapsulant is selected for use high temperature resistant, anti abrasive material is to guarantee sealing effectiveness.
Utilize vibration testing device of the present utility model to carry out the method that shaft coupling misaligns test below in conjunction with description of drawings:
1) at first, the outer end of outer rotor blind flange is connected by the output shaft of first shaft coupling with a control motor, the outer end of internal rotor is connected by the output shaft of second shaft coupling with another control motor;
2) start two control motors, respectively two control rotating speed of motor are adjusted, as 8000r/min, 12000r/min, 15000r/min; By current vortex sensor the vibration signal of internal rotor, outer rotor or reel under the different rotating speeds is gathered, and noted the vibration signal of collection;
3) first shaft coupling, second shaft coupling are replaced by the shaft coupling that has fault;
4) start two control motors, respectively two control rotating speed of motor are adjusted, as 8000r/min, 12000r/min, 15000r/min; By current vortex sensor the vibration signal that exists shaft coupling to misalign internal rotor, outer rotor or the reel of fault under the different rotating speeds is gathered, and noted the fault vibration signal of collection, finish test.
Claims (5)
1. the vibration testing device of an inner and outer rotors system, comprise internal rotor, outer rotor, it is characterized in that described internal rotor is arranged on the inside of outer rotor, internal rotor is connected by intermediary's bearing with outer rotor, and described outer rotor is connected with bearing seat by block bearing; Inboard at bearing seat is provided with inside cap, in the arranged outside of bearing seat the outer bearing cover with through hole and oil pocket is arranged, and the end of described outer rotor is positioned at oil pocket; One end of described outer rotor has through hole, and the internal rotor of this end is connected with second shaft coupling by the through hole of outer rotor, the through hole of outer bearing cover successively; The other end of described outer rotor is connected with an end of outer rotor blind flange, and the other end of outer rotor blind flange is connected with first shaft coupling by the through hole of outer bearing cover; Be provided with oil guiding hole at the outer rotor blind flange end that links to each other with outer rotor, an end of described oil guiding hole is connected with oil pocket, and the other end is corresponding with the intermediary bearing; Outer setting at outer rotor has reel, and reel is fixed on by the spring axle sleeve on the cylindrical of outer rotor, is provided with first packoff between the internal rotor at described outer rotor two ends and outer rotor; Described internal rotor, outer rotor or reel are provided with current vortex sensor, and described current vortex sensor is connected with host computer.
2. the vibration testing device of a kind of inner and outer rotors according to claim 1 system is characterized in that described internal rotor adopts hollow structure, and the hollow position place of the internal rotor of rotor flange lid end is provided with second packoff outside.
3. the vibration testing device of a kind of inner and outer rotors according to claim 1 system is characterized in that described outer rotor is connected by screw with the outer rotor blind flange.
4. the vibration testing device of a kind of inner and outer rotors according to claim 1 system is characterized in that described inside cap, outer bearing cover all are connected with bearing seat by screw.
5. the vibration testing device of a kind of inner and outer rotors according to claim 1 system is characterized in that the oil guiding hole of described outer rotor blind flange end is set to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202607158U CN201724799U (en) | 2010-07-16 | 2010-07-16 | Vibration tester for inner-outer rotor systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202607158U CN201724799U (en) | 2010-07-16 | 2010-07-16 | Vibration tester for inner-outer rotor systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201724799U true CN201724799U (en) | 2011-01-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202607158U Expired - Fee Related CN201724799U (en) | 2010-07-16 | 2010-07-16 | Vibration tester for inner-outer rotor systems |
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| CN (1) | CN201724799U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308313A (en) * | 2013-05-15 | 2013-09-18 | 天津大学 | Base-movable aeroengine dual-rotor system model experiment platform |
| CN104297081A (en) * | 2014-09-12 | 2015-01-21 | 大连理工大学 | Hydraulic pipeline vibration testing device with adjustable supporting rigidity |
| CN104422574A (en) * | 2013-08-23 | 2015-03-18 | 超捷紧固系统(上海)股份有限公司 | Automotive dynamic load vibration testing machine |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN105773512A (en) * | 2016-03-23 | 2016-07-20 | 大连理工大学 | Mounting and dismounting method for intermediary bearing of dual-rotor testing table |
| CN108490268A (en) * | 2018-04-04 | 2018-09-04 | 天津中科先进技术研究院有限公司 | Device for detecting quadrature-direct axis inductance |
| CN110243604A (en) * | 2019-07-17 | 2019-09-17 | 大连工业大学 | A kind of intershaft bearing vibration testing device |
| CN114563074A (en) * | 2022-03-03 | 2022-05-31 | 西安热工研究院有限公司 | Vibration detection system with high stability |
-
2010
- 2010-07-16 CN CN2010202607158U patent/CN201724799U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308313A (en) * | 2013-05-15 | 2013-09-18 | 天津大学 | Base-movable aeroengine dual-rotor system model experiment platform |
| CN103308313B (en) * | 2013-05-15 | 2015-09-09 | 天津大学 | Base-movable aeroengine dual-rotor system model experiment platform |
| CN104422574B (en) * | 2013-08-23 | 2017-09-01 | 超捷紧固系统(上海)股份有限公司 | Automobile dynamic load vibration rig |
| CN104422574A (en) * | 2013-08-23 | 2015-03-18 | 超捷紧固系统(上海)股份有限公司 | Automotive dynamic load vibration testing machine |
| CN104297081B (en) * | 2014-09-12 | 2016-07-27 | 大连理工大学 | A kind of adjustable fluid pressure line vibration testing device of support stiffness |
| CN104297081A (en) * | 2014-09-12 | 2015-01-21 | 大连理工大学 | Hydraulic pipeline vibration testing device with adjustable supporting rigidity |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN105571867B (en) * | 2016-01-21 | 2018-10-02 | 苏州东菱振动试验仪器有限公司 | A kind of aero-engine vibration control experiment platform |
| CN105773512A (en) * | 2016-03-23 | 2016-07-20 | 大连理工大学 | Mounting and dismounting method for intermediary bearing of dual-rotor testing table |
| CN105773512B (en) * | 2016-03-23 | 2017-08-01 | 大连理工大学 | A kind of birotor testing stand intershaft bearing handling method |
| CN108490268A (en) * | 2018-04-04 | 2018-09-04 | 天津中科先进技术研究院有限公司 | Device for detecting quadrature-direct axis inductance |
| CN110243604A (en) * | 2019-07-17 | 2019-09-17 | 大连工业大学 | A kind of intershaft bearing vibration testing device |
| CN114563074A (en) * | 2022-03-03 | 2022-05-31 | 西安热工研究院有限公司 | Vibration detection system with high stability |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110126 Termination date: 20110716 |