CN105352732A - Aeroengine fan shaft composite static force and fatigue tester - Google Patents
Aeroengine fan shaft composite static force and fatigue tester Download PDFInfo
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- CN105352732A CN105352732A CN201510893968.6A CN201510893968A CN105352732A CN 105352732 A CN105352732 A CN 105352732A CN 201510893968 A CN201510893968 A CN 201510893968A CN 105352732 A CN105352732 A CN 105352732A
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Abstract
The invention relates to the intensity test field of component structures of aeroengine shafts, and particularly relates to an aeroengine fan shaft composite static force and fatigue tester. The aeroengine fan shaft composite static force and fatigue tester comprises a support framework, a fan shaft clamp and a force transducer; the top end of the fan shaft is fixedly connected with the top beam of the support framework; the top of a bending moment disc is fixedly connected with the bottom end of the fan shaft; the tops of a plurality of bending moment loading oil cylinders are hinged to the outer torus of the bending moment disc and the bottoms are hinged to the pedestal of the support framework; two symmetrical torque loading oil cylinders are installed on the outer torus of a torque disc; an axial force loading oil cylinder is hinged between the axial direction bottom and the pedestal of the torque disc. Aiming at four load input characteristics of the fan shaft, a vertical stacked structure is adopted, and therefore the loading of rotation bending moment, main torque and/or vibration torque and axial force are realized; the integrated level of the tester is high; and the adaptability is stronger.
Description
Technical field
The present invention relates to aeromotor Axle Parts stryctyrak test field, particularly relate to a kind of compound static(al) and fatigue tester of aerial engine fan axle.
Background technology
The load more complicated that during engine operation, main bearing is subject to, comparatively large on main shaft impact fatigue lifetime, the operating load that should take in has moment of torsion, axial force, vibration moment of torsion and moment of flexure.Engine blower axle is the ingredient of main shaft, and by the edge-restraint condition of fan shaft and the analysis of suffered load condition, four kinds of load act on fan wheel disc, and then are delivered on fan shaft.
Wherein, the loading rotating moment of flexure now mainly contains rotating eccentricity balancing disk and rotating hydraulic pressurized strut two kinds of modes.In the first load mode, the tensile force of motor pulley can cause eccentric force to affect on load applying, and load and frequency size thereof are restricted (balancing weight centrifugal couple and load; Load frequency and motor speed), under the rotating speed up to 3000RPM (during 50Hz), unbalanced high speed balancing disk can not ensure in loading accuracy and security.And in the second load mode, need the special hydraulic pressure of design and electric interfaces whirligig, follow-up repair and maintenance cost is high, workload is large, the whether stable checking of still needing of the duty of hydraulic unit in High Rotation Speed in addition, the high speed centrifugation power be attached in pressurized strut also will carry out corresponding calculating and process.The two all carries out the rotation of bending load by motor drag, the environment of strong electromagnetic radiation also can have an impact to the measuring precision.In addition, after applying bending load, can cause testpieces that certain distortion occurs to subjects, this influences each other to the moment of torsion on test specimen and axial force formation to same purpose, also needs a set of decoupling device.
Vibrate the loading of moment of torsion or pass through shaking table (hydraulic pressure or electromagnetism), or adopting a pair symmetrical pressurized strut to realize.Although shaking table can provide frequency to be not less than the oscillating load of 50Hz, shaking table does not generally provide open control development interface, is difficult to realize Seamless integration-and the timing synchronization with other load; And vibrate moment of torsion from main moment of torsion and adopt different pressurized struts to implement, and acting in conjunction is on the same moment of torsion arm of force, can cause and being coupled of main moment of torsion, and is necessary to design to the following device of main moment of torsion for decoupling zero.
In sum, at least there is following deficiency in existing exerciser:
1), for moment of torsion, axial force, vibration moment of torsion and moment of flexure, need to adopt different exercisers to load, load operation is complicated, and cost is higher; 2), existing exerciser or due to for the difference of subjects, equipment load type, load capability and load and execution mechanism (as pressurized strut two cavity pressure difference simulation load) are not exclusively applicable to fan shaft test; 3), due to design defect, extra additional force (as eccentric force, centrifugal force) is introduced in rotation bending load loads, being coupled between main moment of torsion with vibration moment of torsion causes control system complicated, and between four kinds of load, moment of flexure is incomplete thus cannot ensure the accurate loading of each load with moment of torsion (containing axial force) decoupling zero; 4), because automaticity is lower, cannot carry out compound between different loads according to strict loading spectrum sequential logic, maintenance cost is huge with check time overhead, and equipment operating efficiency is low.
Summary of the invention
A kind of compound static(al) and fatigue tester of aerial engine fan axle are the object of this invention is to provide, to solve at least one technical matters above-mentioned.
Technical scheme of the present invention is:
The compound static(al) of aerial engine fan axle and a fatigue tester, comprising:
Support frame, has the base of level, back timber and the vertical column for supporting described back timber;
Fan shaft fixture, is fixedly installed on the column of described support frame, and the fan shaft of engine vertically rotates, and to be arranged on described fan shaft fixture inner;
First fixed part, is positioned at the described vertical top of fan shaft fixture, for being fixedly connected with by the back timber of the top of described fan shaft with described support frame;
Second fixed part, be positioned at the described vertical below of fan shaft fixture, top is fixedly connected with the bottom of described fan shaft;
Moment of flexure dish, axial top is fixedly connected with the bottom of described second fixed part;
Multiple moment of flexure load cylinder, the axes normal of each described moment of flexure load cylinder is in surface level, the top end of multiple described moment of flexure load cylinder is located in the same horizontal plane, and multiple described moment of flexure load cylinder is uniformly distributed along same circumferencial direction, in addition, the top of multiple described moment of flexure load cylinder is hinged on the outer ring surface of described moment of flexure dish respectively, and bottom is hinged with the base of described support frame respectively, realizes moment of flexure load by multiple moment of flexure load cylinder;
3rd fixed part, is positioned at the described vertical below of moment of flexure dish, and top is fixedly connected with the axis bottom of described moment of flexure dish;
Torque plate, be positioned at the described 3rd vertical below of fixed part, axial top is fixedly connected with the bottom of described 3rd fixed part, the outer ring surface of described torque plate has two and radially protrudes and the support arm of symmetry;
Two moment of torsion load cylinders, the axis of each described moment of torsion load cylinder all and plane-parallel, one end of moment of torsion load cylinder described in one of them is connected with the end winding support of a support arm on described torque plate, and a root post of the other end and described support frame is hinged; One end of moment of torsion load cylinder described in another is connected with the end winding support of another support arm on described torque plate, and another root post of the other end and described support frame is hinged; Two described moment of torsion load cylinders for origin symmetry distributes, realize the loading of main moment of torsion and/or vibration moment of torsion with the central point of described torque plate by moment of torsion load cylinder;
Axial force load cylinder, the axial bottom-hinged of one end and described torque plate, the base of the other end and described support frame is hinged, is realized the loading of axial force by axial force load cylinder;
Force snesor, is separately positioned on each described moment of flexure load cylinder, described moment of torsion load cylinder and described axial force load cylinder.
Preferably, described fan shaft fixture inside is coaxially arranged with two bearing seats from top to bottom, and described fan shaft is rotated by two bearings and is arranged on two described bearing seats, to simulate boundary constraint time described fan shaft is truly installed.
Preferably, described first fixed part is cover tooth flange, and the back timber of described cover tooth flange top and described support frame is bolted to connection, and bottom is fixedly connected with described fan shaft top.
Preferably, described second fixed part is two-way flange transfer panel, and the bottom of top and described fan shaft is bolted to connection, and the axial top of bottom and described moment of flexure dish is bolted to connection.
Preferably, the excircle of described moment of flexure dish is evenly provided with eight ears, the top of each ears and a described moment of flexure load cylinder is hinged.
Preferably, piston rod one end of described moment of flexure load cylinder and described force snesor one end are by Flange joint, and the other end ball-type of described force snesor is hinged on the ears of described moment of flexure dish.
Preferably, described 3rd fixed part is candan universal joint.
Preferably, piston rod one end and described force snesor one end ball-type of described moment of torsion load cylinder are hinged, and the support arm of the described force snesor other end and described torque plate passes through Flange joint.
Preferably, the described force snesor on described axial force load cylinder is arranged on the piston rod of described axial force load cylinder.
Preferably, compound static(al) and the fatigue tester of described aerial engine fan axle also comprise:
Hydraulic servo coordinated loading control device, for controlling described moment of flexure load cylinder, described moment of torsion load cylinder and described axial force load cylinder.
The invention has the advantages that:
The compound static(al) of aerial engine fan axle of the present invention and fatigue tester, for fan shaft four kinds of load input features, adopt vertical stepped construction, the loading rotating moment of flexure can be realized by moment of flexure load cylinder, the loading of main moment of torsion and/or vibration moment of torsion is realized by moment of torsion load cylinder, can also be realized the loading of axial force again by axial force load cylinder, make exerciser integrated level high, adaptability is stronger.
Accompanying drawing explanation
Fig. 1 is the compound static(al) of aerial engine fan axle of the present invention and the structural representation of fatigue tester;
Fig. 2 is the compound static(al) of aerial engine fan axle of the present invention and the structural representation of fatigue tester fan axle holder part;
Fig. 3 is the structural representation of outstanding moment of flexure load cylinder part emphatically in the compound static(al) of aerial engine fan axle of the present invention and fatigue tester;
Fig. 4 is the structural representation of outstanding moment of torsion load cylinder part emphatically in the compound static(al) of aerial engine fan axle of the present invention and fatigue tester;
Fig. 5 is the structural representation of outstanding axial force load cylinder part emphatically in the compound static(al) of aerial engine fan axle of the present invention and fatigue tester.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limiting the scope of the invention can not be interpreted as.
Below in conjunction with accompanying drawing 1 to Fig. 5, the compound static(al) of aerial engine fan axle of the present invention and fatigue tester are described in further details.
The invention provides a kind of compound static(al) and fatigue tester of aerial engine fan axle, comprise support frame 1 and be arranged on the parts such as fan shaft fixture 2, moment of flexure dish 4, torque plate 5, oil cylinder, force snesor on support frame 1, load for carrying out rotation moment of flexure, main moment of torsion, vibration moment of torsion and axial force load to the fan shaft 3 of engine.
Support frame 1 can adopt multiple applicable shape and structure, has the base 11 of level, back timber 12 and the vertical column 13 for supporting top beam 12.In the present embodiment, preferred support frame 1 comprises a horizontal base 11 and a horizontal top cover be made up of many back timbers 12, horizontal top cover is fixedly installed on horizontal base 11 top by least four root post 13 levels, the spatial accommodation of an opening is formed, so that follow-up each parts are installed between horizontal top cover and horizontal base 11; The length of column 13 can be tested needs according to different length fan shaft 3 and select, and, be bolted between top cover and column 13, also can change cap height by increase and decrease steel pad between; Further, in order to add structural strength and the stability of Frame braced column with strong bracing system 1, oblique support beam can also be set up between column 13 and base 11.
Fan shaft fixture 2 be arranged in above-mentioned support frame 1 form spatial accommodation, be fixedly installed on the column 13 of support frame 1, and the fan shaft 3 of engine vertically rotates be arranged on fan shaft fixture 2 inside.Fan shaft fixture 2 can be multiple applicable shape, in the present embodiment, preferred fan shaft fixture 2 inside is coaxially arranged with two bearing seats 23 from top to bottom, from top to bottom clutch shaft bearing seat and the second bearing seat respectively, fan shaft 3 is rotated by two bearings 24 and is arranged on two bearing seats 23, to simulate boundary constraint time fan shaft 3 is truly installed, that is to say that the structure that fan shaft fixture 2 and the mounting structure of fan shaft 3 imitate when true fan shaft 3 is installed completely (comprises selected structural member to assemble, intensity and rigidity) make and form, the structure of follow-up load load test can be made more accurate.Further, the outside of fan shaft fixture 2 is fixedly connected with four root posts 13 by bolt.
Further, be arranged on fan shaft 3 top (stretching out the part of fan shaft fixture 2 clutch shaft bearing seat 23 upper surface) of fan shaft fixture 2 inside, the first fixed part 21 also by being positioned at its vertical top is fixedly connected with the back timber 12 of support frame 1.First fixed part 21 can be multiple applicable syndeton, and in the present embodiment, the first fixed part 21 is cover tooth flange, and the back timber 12 of cover tooth flange top and support frame 1 is bolted to connection, and bottom is fixedly connected with fan shaft 3 top; Further, cover tooth flange base is provided with external tooth, matches with the internal tooth on fan shaft 3 top, thus realize being fixedly connected with fan shaft 3 (being similar to spline fitted).
The axial top of moment of flexure dish 4 is fixedly connected with bottom fan shaft by the second fixed part 22; Equally, the second fixed part 22 can be multiple applicable syndeton, and in the present embodiment, the second fixed part 22 is two-way flange transfer panel, and the bottom of top and fan shaft 3 is bolted to connection, and the axial top of bottom and moment of flexure dish 4 is bolted to connection.
Further, moment of flexure dish 4 outer ring surface is provided with multiple moment of flexure load cylinder 41; Particularly, the axes normal of each moment of flexure load cylinder 41 is in surface level, and the top end of multiple moment of flexure load cylinder 41 is located in the same horizontal plane, and multiple moment of flexure load cylinder 41 is uniformly distributed along same circumferencial direction; In addition, the top of multiple moment of flexure load cylinder 41 is hinged on the outer ring surface of moment of flexure dish 4 respectively, and bottom is hinged with the base 11 of support frame 1 respectively.It should be noted that, when the column 13 of support frame 1 is too high, when moment of flexure load cylinder 41 length is inadequate, also bottom moment of flexure load cylinder 41 and between base 11, some back-up blocks can be set and supports.
The quantity of moment of flexure load cylinder 41 can be set to multiple as required, and also can carry out with the connected mode of moment of flexure dish 4 selection that is applicable to as required, in the present embodiment, evenly be provided with eight ears 43 on the excircle of moment of flexure dish 4,45 °, each interval, the top of each ears 43 and a moment of flexure load cylinder 41 is hinged, by the synergy of eight moment of flexure load cylinders 41, moment of flexure dish 4 produces a turning pair field (usual gyro frequency is not less than 50Hz), thus simulated implementation rotates bending load.In addition, each described moment of flexure load cylinder 41 is also provided with a force snesor 7, particularly, be piston rod one end of moment of flexure load cylinder 41 and force snesor 7 one end by Flange joint, the other end ball-type of this force snesor 7 is hinged on the ears 43 of moment of flexure dish 4.
Torque plate 5 can be multiple applicable shape, in the present embodiment, its outer ring surface also has two and radially protrudes and the support arm 51 of symmetry; Torque plate 5 is the axially bottoms being arranged on moment of flexure dish 4 by the 3rd fixed part 42; Particularly, 3rd fixed part 42 is positioned at the vertical below of moment of flexure dish, be preferably candan universal joint, candan universal joint 6 plays not torque limiting (containing axial force) and upwards transmits but limit the object of moment of flexure going down, realizes the mutual decoupling zero between moment of flexure and moment of torsion (containing axial force); The top of candan universal joint is fixedly connected with the axis bottom of moment of flexure dish 4, and the bottom of candan universal joint is fixedly connected with the axial top of torque plate 5.
Moment of torsion load cylinder 52 is two, and the axis of each moment of torsion load cylinder 52 all and plane-parallel; One end of one of them moment of torsion load cylinder 52 is connected with the end winding support of a support arm 51 on torque plate 5, and a root post 13 of the other end and support frame 1 is hinged; One end of another moment of torsion load cylinder 52 is connected with the end winding support of another support arm 51 on torque plate 5, and another root post 13 of the other end and support frame 1 is hinged; In addition, two moment of torsion load cylinders 52 with the axis direction of for origin symmetry distribution and preferred original state (when not loading) the moment of torsion load cylinder 52 of the central point of torque plate 5 perpendicular to the axis of support arm 51.
Equally, each moment of torsion load cylinder 52 is also provided with a force snesor 7, particularly, piston rod one end of moment of torsion load cylinder 52 and force snesor 7 one end ball-type hinged, in addition, the support arm 51 of this force snesor 7 other end and torque plate 5 passes through Flange joint.Under ball pivot connected mode can ensure twisting action, distortion (windup-degree) does not impact the accuracy of torque load; Further, reacting force and the responsive to axial force deformation that can eliminate two moment of torsion load cylinders, 52 pairs of axial forces cause uncertain partical gravity.
In addition, the hydraulic actuator in two common chambeies can be chosen as at moment of torsion load cylinder 9 of the present invention, realize main moment of torsion and/or the loading of vibration moment of torsion by this hydraulic actuator; In the present embodiment, three known at present chamber pressurized struts can also be selected, eachly contain two cover hydraulic servo valve actuating mechanisms, utilize the large chamber of oil cylinder to realize main moment of torsion and load, utilize two loculuses to realize vibration moment of torsion to load, thus achieve the decoupling zero between main moment of torsion and vibration moment of torsion.
The axial bottom-hinged of axial force load cylinder 6 one end and torque plate 5, the base 11 of the other end and support frame 1 is hinged, and the force snesor 7 on axial force load cylinder 6 is arranged on the piston rod of axial force load cylinder 6.
The compound static(al) of aerial engine fan axle of the present invention and fatigue tester, for fan shaft four kinds of load input features, adopt vertical stepped construction, the loading rotating moment of flexure can be realized by moment of flexure load cylinder 41, the loading of main moment of torsion and/or vibration moment of torsion is realized by moment of torsion load cylinder 52, can also be realized the loading of axial force again by axial force load cylinder 6, make exerciser integrated level high, adaptability is stronger.
Further; the compound static(al) of aerial engine fan axle of the present invention and fatigue tester also comprise High-Performance Digital formula hydraulic servo coordinated loading control device; for automatically controlling according to default control order moment of flexure load cylinder 41, moment of torsion load cylinder 52 and axial force load cylinder 6; make test spectrum sequential logic accurate; power closed-loop control is accurately load simulated; perfect load protection mechanism can also be had, make test efficiency high.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (10)
1. the compound static(al) of aerial engine fan axle and a fatigue tester, is characterized in that, comprising:
Support frame (1), has the base (11) of level, back timber (12) and the vertical column (13) for supporting described back timber (12);
Fan shaft fixture (2), is fixedly installed on the column (13) of described support frame (1), and the fan shaft of engine (3) vertically rotates, and to be arranged on described fan shaft fixture (2) inner;
First fixed part (21), is positioned at described fan shaft fixture (2) vertically top, for being fixedly connected with the back timber (12) of described support frame (1) on the top of described fan shaft (3);
Second fixed part (22), top is fixedly connected with the bottom of described fan shaft (3);
Moment of flexure dish (4), axial top is fixedly connected with the bottom of described second fixed part (22);
Multiple moment of flexure load cylinder (41), the axes normal of each described moment of flexure load cylinder (41) is in surface level, the top end of multiple described moment of flexure load cylinder (41) is located in the same horizontal plane, and multiple described moment of flexure load cylinder (41) is uniformly distributed along same circumferencial direction, in addition, the top of multiple described moment of flexure load cylinder (41) is hinged on the outer ring surface of described moment of flexure dish (4) respectively, and bottom is hinged with the base (11) of described support frame (1) respectively;
3rd fixed part (42), top is fixedly connected with the axis bottom of described moment of flexure dish (4);
Torque plate (5), axial top is fixedly connected with the bottom of described 3rd fixed part (42), the outer ring surface of described torque plate (5) has two and radially protrudes and the support arm of symmetry (51);
Two moment of torsion load cylinders (52), the axis of each described moment of torsion load cylinder (52) all and plane-parallel, one end of moment of torsion load cylinder (52) described in one of them is connected with the end winding support of the upper support arm (51) of described torque plate (5), and a root post (13) of the other end and described support frame (1) is hinged; One end of moment of torsion load cylinder (52) described in another is connected with the end winding support of upper another support arm (51) of described torque plate (5), and another root post (13) of the other end and described support frame (1) is hinged; Two described moment of torsion load cylinders (52) are origin symmetry distribution with the central point of described torque plate (5);
Axial force load cylinder (6), the axial bottom-hinged of one end and described torque plate (5), the base (11) of the other end and described support frame (1) is hinged;
Force snesor (7), is separately positioned on each described moment of flexure load cylinder (41), described moment of torsion load cylinder (52) and described axial force load cylinder (6).
2. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, described fan shaft fixture (2) inside is coaxially arranged with two bearing seats (23) from top to bottom, described fan shaft (3) is arranged on two described bearing seats (23) by the rotation of two bearings (24), to simulate boundary constraint time described fan shaft (3) is truly installed.
3. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, described first fixed part (21) is cover tooth flange, the back timber (12) of described cover tooth flange top and described support frame (1) is bolted to connection, and bottom is fixedly connected with described fan shaft (3) top.
4. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, described second fixed part (22) is two-way flange transfer panel, the bottom of top and described fan shaft (3) is bolted to connection, and the axial top of bottom and described moment of flexure dish (4) is bolted to connection.
5. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, the excircle of described moment of flexure dish (4) is evenly provided with eight ears (43), each ears (43) are hinged with the top of a described moment of flexure load cylinder (41).
6. the compound static(al) of aerial engine fan axle and fatigue tester according to claim 1 or 5, it is characterized in that, piston rod one end of described moment of flexure load cylinder (41) and described force snesor (7) one end are by Flange joint, and the other end ball-type of described force snesor (7) is hinged on the ears (43) of described moment of flexure dish (4).
7. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, described 3rd fixed part (42) is candan universal joint.
8. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, piston rod one end and described force snesor (7) one end ball-type of described moment of torsion load cylinder (52) are hinged, and the support arm (51) of described force snesor (7) other end and described torque plate (5) passes through Flange joint.
9. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, it is characterized in that, the described force snesor (7) on described axial force load cylinder (6) is arranged on the piston rod of described axial force load cylinder (6).
10. the compound static(al) of aerial engine fan axle according to claim 1 and fatigue tester, is characterized in that, also comprise:
Hydraulic servo coordinated loading control device, for controlling described moment of flexure load cylinder (41), described moment of torsion load cylinder (52) and described axial force load cylinder (6).
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| CN201510893968.6A CN105352732B (en) | 2015-12-08 | 2015-12-08 | A kind of compound static(al) and fatigue tester of aerial engine fan axis |
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| CN201510893968.6A CN105352732B (en) | 2015-12-08 | 2015-12-08 | A kind of compound static(al) and fatigue tester of aerial engine fan axis |
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| CN105527092B (en) * | 2016-02-29 | 2018-03-30 | 西安航空动力股份有限公司 | The main load part entirety static strength certification test system and method for aero-engine |
| CN105527092A (en) * | 2016-02-29 | 2016-04-27 | 西安航空动力股份有限公司 | Aero-engine main force bearing component overall static strength assessment test system and method |
| CN107575432A (en) * | 2017-09-29 | 2018-01-12 | 北京乐冶液压气动设备技术有限公司 | Hydraulic loading device with a variety of loading force output modes |
| CN107575432B (en) * | 2017-09-29 | 2019-07-12 | 北京乐冶液压气动设备技术有限公司 | Hydraulic loading device with a variety of loading force output modes |
| CN108709709A (en) * | 2018-05-07 | 2018-10-26 | 西南交通大学 | A kind of multi-axes vibration test platform loading device |
| CN108627407A (en) * | 2018-06-11 | 2018-10-09 | 中国航发哈尔滨东安发动机有限公司 | First half sleeve assembly high-cycle fatigue test device |
| CN109520685A (en) * | 2018-10-25 | 2019-03-26 | 中国飞机强度研究所 | A kind of bearing support assembly, rigidity calibration system and method |
| CN110017977B (en) * | 2019-03-29 | 2021-02-26 | 航天科工防御技术研究试验中心 | Component detection combined loading device and detection method |
| CN110017977A (en) * | 2019-03-29 | 2019-07-16 | 航天科工防御技术研究试验中心 | A kind of component detection combination loading device and detection method |
| CN110095284A (en) * | 2019-04-17 | 2019-08-06 | 上海贝序汽车科技有限公司 | A kind of engine blower shaft member endurance test mechanism |
| CN110282154A (en) * | 2019-06-11 | 2019-09-27 | 中国飞机强度研究所 | A kind of engine installation system test of static strength bogusware |
| CN110261085A (en) * | 2019-06-27 | 2019-09-20 | 华南理工大学 | A kind of testing stand of test pulley decoupler durability |
| CN111811800A (en) * | 2020-06-30 | 2020-10-23 | 东风马勒热系统有限公司 | Durable testing arrangement of silicone oil fan flange axle bending moment |
| CN112067188A (en) * | 2020-08-26 | 2020-12-11 | 东北电力大学 | Flexible pull rod type series connection inter-dimension decoupling wireless passive sensor |
| CN112067188B (en) * | 2020-08-26 | 2021-09-10 | 东北电力大学 | Flexible pull rod type series connection inter-dimension decoupling wireless passive sensor |
| CN112525503A (en) * | 2020-11-04 | 2021-03-19 | 中国航发贵州黎阳航空动力有限公司 | A multi-direction mechanical properties detection device for aeroengine part |
| CN112798437A (en) * | 2020-12-28 | 2021-05-14 | 中国航发沈阳发动机研究所 | Intermediate casing test load loading device |
| CN112798437B (en) * | 2020-12-28 | 2024-01-02 | 中国航发沈阳发动机研究所 | Intermediate case test load loading device |
| CN112880993A (en) * | 2021-01-18 | 2021-06-01 | 中国航发沈阳发动机研究所 | Loading device and method for static force and fatigue test load of main shaft of aircraft engine |
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