CN105352732B - A kind of compound static(al) and fatigue tester of aerial engine fan axis - Google Patents
A kind of compound static(al) and fatigue tester of aerial engine fan axis Download PDFInfo
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- CN105352732B CN105352732B CN201510893968.6A CN201510893968A CN105352732B CN 105352732 B CN105352732 B CN 105352732B CN 201510893968 A CN201510893968 A CN 201510893968A CN 105352732 B CN105352732 B CN 105352732B
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Abstract
The present invention relates to aero-engine Axle Parts stryctyrak test fields, more particularly to the compound static(al) and fatigue tester of a kind of aerial engine fan axis.The compound static(al) and fatigue tester of aerial engine fan axis, including：Braced frame；Fan shaft fixture；The top of fan shaft is fixedly connected with the top beam of braced frame；It is fixedly connected with the bottom end of fan shaft at the top of moment of flexure disk；It is respectively hinged on the outer ring surface of moment of flexure disk at the top of multiple moment of flexure load cylinders, bottom is hinged with the pedestal of braced frame respectively；There are two symmetrical torque load cylinders for tool on the outer ring surface of torque plate；Axial force load cylinder is hingedly arranged between the axial bottom of torque plate and pedestal；Force snesor.The present invention inputs feature for four kinds of load of fan shaft, using vertical stepped construction, can realize rotation moment of flexure, main torque and/or the load for vibrating torque, axial force so that exerciser integrated level is high, more adaptable.
Description
Technical field
The present invention relates to aero-engine Axle Parts stryctyrak test fields, more particularly to a kind of aero-engine
The compound static(al) and fatigue tester of fan shaft.
Background technology
The load that base bearing is received when engine works is more complicated, is affected to main shaft fatigue life, it should be examined
The service load of worry has torque, axial force, vibration torque and moment of flexure.Engine blower axis is the component part of main shaft, by right
The analysis of the edge-restraint condition of fan shaft and suffered load condition, four kinds of load act on fan wheel disc, and then are transmitted to
On fan shaft.
Wherein, the load for rotating moment of flexure now mainly has rotating eccentricity balancing disk and rotating hydraulic pressurized strut two ways.The
In a kind of load mode, the tensile force of motor pulley, which can apply load, cause eccentric force to influence, load and its frequency size
It is restricted (clump weight centrifugal couple i.e. load；Load frequency, that is, motor speed), in the rotating speed of up to 3000RPM (when 50Hz)
Under, unbalanced high speed balancing disk not can guarantee in load accuracy and safety.And in the second load mode, it needs to design
Special hydraulic pressure and electric interfaces rotating device, follow-up maintenance is of high cost, heavy workload, and in addition hydraulic unit is in high speed rotation
Working condition whether stablize the high speed centrifugation power being attached to it is still necessary to verify in pressurized strut and also accordingly to be calculated and be handled.
The two carries out the rotation of bending load by motor drag, and the environment of strong electromagnetic radiation also will produce shadow to the measuring precision
It rings.In addition, after applying bending load to subjects, it can cause testpieces that certain deformation occurs, this is to same purpose to examination
Torque and axial force composition on part influence each other, it is also desirable to a set of decoupling device.
Or the load for vibrating torque is realized by shake table (hydraulic pressure or electromagnetism) or using a pair of symmetrical pressurized strut.
Although shake table is capable of providing the oscillating load that frequency is not less than 50Hz, but shake table does not provide open control exploitation generally and connects
Mouthful, it is difficult to realize Seamless integration- and the timing synchronization with other load；And it vibrates torque and uses different pressurized struts from main torque
Implement, and collective effect can cause the coupling with main torque on the same torque arm of force, it is necessary to which design is to main torque
Following device is for decoupling.
In conclusion at least there is following deficiency in existing exerciser：
1) it, is directed to torque, axial force, vibration torque and moment of flexure, needs to be loaded using different exercisers, load behaviour
Make complexity, cost is higher；2), existing exerciser or the difference due to targeted subjects, equipment load type, load energy
Power and load and execution mechanism (such as two cavity pressure difference simulation load of pressurized strut) are not properly suited for fan shaft experiment；3), due to setting
Defect is counted, introduces additional additional force (such as eccentric force, centrifugal force) in rotation bending load load, main torque is turned round with vibration
Coupling between square causes control system complicated, and moment of flexure and torque (containing axial force) decoupling are incomplete to protect between four kinds of load
Demonstrate,prove the accurate load of each load；4), since the degree of automation is relatively low, when can not be according to stringent loading spectrum between different loads
The progress of sequence logic is compound, and maintenance cost and check time overhead are huge, and equipment operating efficiency is low.
Invention content
The object of the present invention is to provide a kind of compound static(al) of aerial engine fan axis and fatigue testers, to solve
Above-mentioned at least one technical problem.
The technical scheme is that：
A kind of compound static(al) and fatigue tester of aerial engine fan axis, including：
Braced frame has horizontal pedestal, top beam and the vertical column for being used to support the top beam；
Fan shaft fixture is fixed on the column of the braced frame, and the fan shaft of engine is vertically
It is rotatably arranged on inside the fan shaft fixture；
First fixed part is located at the vertical top of fan shaft fixture, is used for the top of the fan shaft and the branch
The top beam of support frame frame is fixedly connected；
Second fixed part is located at the fan shaft fixture vertically below, and top is fixedly connected with the bottom end of the fan shaft；
Moment of flexure disk, axial top are fixedly connected with the bottom of second fixed part；
Multiple moment of flexure load cylinders, the axis of each moment of flexure load cylinder is perpendicular to horizontal plane, multiple moments of flexure
The top end of load cylinder is located in the same horizontal plane, and multiple moment of flexure load cylinders uniformly divide along same circumferencial direction
Cloth, in addition, be respectively hinged on the outer ring surface of the moment of flexure disk at the top of multiple moment of flexure load cylinders, bottom respectively with institute
The pedestal for stating braced frame is hinged, and moment of flexure load is realized by multiple moment of flexure load cylinders；
Third fixed part is located at the moment of flexure disk vertically below, and top is fixedly connected with the axial bottom of the moment of flexure disk；
Torque plate is located at the third fixed part vertically below, and axial top and the bottom of the third fixed part are fixed
It connects, there are two radially projecting and symmetrical support arms for tool on the outer ring surface of the torque plate；
The axis of two torque load cylinders, each torque load cylinder is parallel with horizontal plane, one of institute
The one end for stating torque load cylinder is fixedly connected with the end of a support arm on the torque plate, the other end and the braced frame
A root post it is hinged；One end and the end of another support arm on the torque plate of another torque load cylinder are fixed
Connection, the other end and another root post of the braced frame are hinged；Two torque load cylinders are with the torque plate
Central point is distributed for origin symmetry, realizes main torque by torque load cylinder and/or vibrates the load of torque；
Axial force load cylinder, one end and the axial bottom of the torque plate are hinged, the other end and the braced frame
Pedestal is hinged, and the load of axial force is realized by axial force load cylinder；
Force snesor is separately positioned on each moment of flexure load cylinder, the torque load cylinder and the axial direction
On power load cylinder.
Preferably, there are two bearing blocks, the fan shaft to pass through for coaxial arrangement from top to bottom inside the fan shaft fixture
Two bearings are rotatably arranged on two bearing blocks, to simulate the boundary constraint when fan shaft is really installed.
Preferably, first fixed part is set tooth flange, the top beam at the top of the set tooth flange with the braced frame
It is bolted to connection, bottom is fixedly connected with the fan shaft top.
Preferably, second fixed part is two-way flange transfer panel, and top and the bottom end of the fan shaft pass through bolt
It is fixedly connected, bottom and the axial top of the moment of flexure disk are bolted to connection.
Preferably, eight ears, each ears and a moment of flexure are evenly arranged on the excircle of the moment of flexure disk
The top of load cylinder is hinged.
Preferably, piston rod one end of the moment of flexure load cylinder passes through flanged joint, institute with described force snesor one end
The other end ball-type for stating force snesor is hinged on the ears of the moment of flexure disk.
Preferably, the third fixed part is candan universal joint.
Preferably, piston rod one end of the torque load cylinder and described force snesor one end ball-type are hinged, the power
The sensor other end and the support arm of the torque plate pass through flanged joint.
Preferably, the work in the axial force load cylinder is arranged in the force snesor on the axial force load cylinder
On stopper rod.
Preferably, the compound static(al) of the aerial engine fan axis and fatigue tester further include：
Hydraulic servo coordinated loading control device, for the moment of flexure load cylinder, the torque load cylinder and institute
Axial force load cylinder is stated to be controlled.
The advantage of the invention is that：
The compound static(al) and fatigue tester of the aerial engine fan axis of the present invention, for four kinds of load inputs of fan shaft
Feature can be realized the load of rotation moment of flexure by moment of flexure load cylinder, be passed through torque load cylinder using vertical stepped construction
It realizes main torque and/or vibrates the load of torque, moreover it is possible to realize the load of axial force by axial force load cylinder again so that examination
It is high to test device integrated level, it is more adaptable.
Description of the drawings
Fig. 1 is the structural schematic diagram of the compound static(al) and fatigue tester of aerial engine fan axis of the present invention；
Fig. 2 be aerial engine fan axis of the present invention compound static(al) and fatigue tester in fan axle clamp tool part knot
Structure schematic diagram；
Fig. 3 be aerial engine fan axis of the present invention compound static(al) and fatigue tester in prominent moment of flexure load oil emphatically
The structural schematic diagram of cylinder part；
Fig. 4 be aerial engine fan axis of the present invention compound static(al) and fatigue tester in prominent torque load oil emphatically
The structural schematic diagram of cylinder part；
Fig. 5 be aerial engine fan axis of the present invention compound static(al) and fatigue tester in prominent axial force load emphatically
The structural schematic diagram of oil cylinder part.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without creative efforts, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as protecting the present invention
The limitation of range.
Below in conjunction with the accompanying drawings 1 to Fig. 5 to the compound static(al) and fatigue tester of aerial engine fan axis of the present invention do into
One step is described in detail.
The present invention provides a kind of compound static(al) of aerial engine fan axis and fatigue testers, including braced frame 1
And the components such as fan shaft fixture 2, moment of flexure disk 4, torque plate 5, oil cylinder, force snesor being arranged in braced frame 1, for pair
The fan shaft 3 of engine carries out rotation moment of flexure, main torque, vibration torque and the load of axial force load.
A variety of suitable shape and structures may be used in braced frame 1, have horizontal pedestal 11, top beam 12 and for branch
The vertical column 13 of support beam 12.In the present embodiment, preferably braced frame 1 includes that a horizontal base 11 and one are pushed up by more
The horizontal head cover that beam 12 is constituted, horizontal head cover are fixed at 11 top of horizontal base, water by least 13 level of four columns
An open accommodation space is formed between flat deck roof and horizontal base 11, so that follow-up each component is installed；Column 13
Length can be tested according to different length fan shaft 3 and be selected, also, be connected by bolt between head cover and column 13
It connects, cap height can also be changed by increasing and decreasing steel pad between；Further, in order to reinforce the structure of braced frame 1
Strength and stability can also set up oblique support beam between column 13 and pedestal 11.
Fan shaft fixture 2 is located in the accommodation space of the composition of above-mentioned braced frame 1, is fixed at the vertical of braced frame 1
On column 13, and the fan shaft 3 of engine is vertically rotatably arranged on inside fan shaft fixture 2.Fan shaft fixture 2 can be
A variety of suitable shapes, in the present embodiment, preferably inside fan shaft fixture 2 coaxial arrangement from top to bottom there are two bearing block 23,
It is from top to bottom first bearing seat and second bearing seat respectively, fan shaft 3 is rotatably arranged on two bearings by two bearings 24
On seat 23, to simulate boundary constraint when fan shaft 3 is really installed, the installation knot of fan shaft fixture 2 and fan shaft 3 that is to say
Structure imitate completely the structure (including the assembly of selected structural member, intensity and rigidity) when true fan shaft 3 is installed be made and
At the structure of follow-up load load test can be made more acurrate.Further, the outside of fan shaft fixture 2 passes through bolt and four
Root post 13 is fixedly connected.
Further, 3 top of fan shaft inside fan shaft fixture 2 is set and (stretches out 2 first bearing seat 23 of fan shaft fixture
The part of upper surface), also it is fixedly connected with the top beam 12 of braced frame 1 by the first fixed part 21 positioned at its vertical top.
First fixed part 21 can be a variety of suitable connection structures, and in the present embodiment, the first fixed part 21 is set tooth flange, covers tooth method
Blue top and the top beam 12 of braced frame 1 are bolted to connection, and bottom is fixedly connected with 3 top of fan shaft；Also, it is covering
Tooth flange base is provided with external tooth, matches with the internal tooth on 3 top of fan shaft, to realize be fixedly connected with fan shaft 3 it is (similar
In spline fitted).
The axial top of moment of flexure disk 4 is fixedly connected by the second fixed part 22 with fan shaft bottom；Equally, the second fixed part
22 can be a variety of suitable connection structures, and in the present embodiment, the second fixed part 22 is two-way flange transfer panel, top and fan
The bottom end of axis 3 is bolted to connection, and bottom and the axial top of moment of flexure disk 4 are bolted to connection.
Further, multiple moment of flexure load cylinders 41 are provided on 4 outer ring surface of moment of flexure disk；Specifically, each moment of flexure load
The axis of oil cylinder 41 is located in the same horizontal plane perpendicular to horizontal plane, the top end of multiple moment of flexure load cylinders 41, 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 cylinders 41 is respectively hinged at
On the outer ring surface of moment of flexure disk 4, bottom is hinged with the pedestal of braced frame 1 11 respectively.It should be noted that when braced frame 1
Column 13 is excessively high, when 41 length of moment of flexure load cylinder is inadequate, can also be set between 41 bottom of moment of flexure load cylinder and pedestal 11
Some supporting blocks are set to be supported.
The quantity of moment of flexure load cylinder 41 can be arranged as required to be multiple, and its connection type with moment of flexure disk 4
It can carry out suitable selection as needed, be to be evenly arranged with eight ears on the excircle of moment of flexure disk 4 in the present embodiment
43, each 45 ° of interval, each ears 43 and the top of a moment of flexure load cylinder 41 are hinged, and pass through eight moment of flexure load cylinders
41 synergy generates a turning pair field (usual speed is not less than 50Hz), to simulate reality on moment of flexure disk 4
Now rotate bending load.In addition, being also set up on each moment of flexure load cylinder 41, there are one force snesors 7, specifically curved
Piston rod one end of square load cylinder 41 passes through flanged joint, the other end ball of the force snesor 7 with 7 one end of force snesor
Type is hinged on the ears 43 of moment of flexure disk 4.
Torque plate 5 can be a variety of suitable shapes, and in the present embodiment, also there are two radially convex for tool on its outer ring surface
Go out and symmetrical support arm 51；Torque plate 5 is arranged in the axial bottom of moment of flexure disk 4 by third fixed part 42；Specifically, third
Fixed part 42 is located at moment of flexure disk vertically below, preferably candan universal joint, and candan universal joint 6, which plays, does not limit torque (containing axial
Power) it is communicated up but limits the purpose that moment of flexure is transmitted downwards, realize the mutual decoupling between moment of flexure and torque (containing axial force)；Cross
The top of universal joint is fixedly connected with the axial bottom of moment of flexure disk 4, and the bottom and the axial top of torque plate 5 of candan universal joint are fixed
Connection.
Torque load cylinder 52 is two, and the axis of each torque load cylinder 52 is parallel with horizontal plane；One of them
One end of torque load cylinder 52 is fixedly connected with the end of a support arm 51 on torque plate 5, the other end and the one of braced frame 1
Root post 13 is hinged；One end of another torque load cylinder 52 is fixedly connected with the end of another support arm 51 on torque plate 5,
The other end and another root post 13 of braced frame 1 are hinged；In addition, two torque load cylinders 52 are with the central point of torque plate 5
It is distributed for origin symmetry and the axis direction of preferred original state (when not loading) torque load cylinder 52 is perpendicular to support arm 51
Axis.
Equally, force snesor 7 there are one being also set up on each torque load cylinder 52, specifically, torque load cylinder 52
Piston rod one end and 7 one end ball-type of force snesor it is hinged, in addition, the support arm of force snesor 7 other end and torque plate 5
51 pass through flanged joint.Flexural pivot connection type can ensure to deform (windup-degree) under twisting action not to the accurate of torque load
Degree impacts；And it is possible to eliminate reaction force and responsive to axial force deformation of two torque load cylinders 52 to axial force
Lead to uncertain partical gravity.
In addition, the hydraulic actuator of two common chambers can be selected as in torque load cylinder 9 of the present invention, pass through the hydraulic pressure
Main torque and/or vibration torque load are realized in pressurized strut；In the present embodiment, it is also an option that three chamber starts being currently known
Cylinder each contains two sets of hydraulic servo valve actuating mechanisms, realizes that main torque loads using the big chamber of oil cylinder, is shaken using the realization of two small chamber
Dynamic torque loads, to realize main torque and vibrate the decoupling between torque.
6 one end of axial force load cylinder and the axial bottom of torque plate 5 are hinged, the pedestal 11 of the other end and braced frame 1
Hinged, 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) and fatigue tester of the aerial engine fan axis of the present invention, for four kinds of load inputs of fan shaft
Feature can realize the load of rotation moment of flexure using vertical stepped construction by moment of flexure load cylinder 41, and oil is loaded by torque
Cylinder 52 realizes main torque and/or vibrates the load of torque, moreover it is possible to the load of axial force is realized by axial force load cylinder 6 again,
So that exerciser integrated level is high, it is more adaptable.
Further, the compound static(al) of aerial engine fan axis of the invention and fatigue tester further include that high-performance is total
Word formula hydraulic servo coordinated loading control device, for being loaded to moment of flexure load cylinder 41, torque load cylinder 52 and axial force
Oil cylinder 6 is carried out automatically controlling according to default control sequence so that experiment spectrum sequential logic is accurate, the load simulated standard of power closed-loop control
Really, there can also be perfect load protection mechanism so that test efficiency is high.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all answer by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of the claims
It is accurate.
Claims (8)
1. the compound static(al) and fatigue tester of a kind of aerial engine fan axis, which is characterized in that including：
Braced frame (1) has horizontal pedestal (11), top beam (12) and the vertical column for being used to support the top beam (12)
(13)；
Fan shaft fixture (2) is fixed on the column (13) of the braced frame (1), and fan shaft (3) edge of engine
It is internal that vertical direction is rotatably arranged on the fan shaft fixture (2)；
First fixed part (21) is located at the vertical top of the fan shaft fixture (2), for by the top of the fan shaft (3) with
The top beam (12) of the braced frame (1) is fixedly connected；
Second fixed part (22), top are fixedly connected with the bottom end of the fan shaft (3)；
Moment of flexure disk (4), axial top are fixedly connected with the bottom of second fixed part (22)；
Multiple moment of flexure load cylinders (41), the axis of each moment of flexure load cylinder (41) are multiple described perpendicular to horizontal plane
The top end of moment of flexure load cylinder (41) is located in the same horizontal plane, and multiple moment of flexure load cylinders (41) are along same circle
Circumferential direction is uniformly distributed, in addition, being respectively hinged at the outer of the moment of flexure disk (4) at the top of multiple moment of flexure load cylinders (41)
On anchor ring, bottom is hinged with the pedestal of the braced frame (1) (11) respectively；
Third fixed part (42), top are fixedly connected with the axial bottom of the moment of flexure disk (4)；
Torque plate (5), axial top are fixedly connected with the bottom of the third fixed part (42), the outer shroud of the torque plate (5)
There are two radially projecting and symmetrical support arms (51) for tool on face；
The axis of two torque load cylinders (52), each torque load cylinder (52) is parallel with horizontal plane, wherein one
One end of a torque load cylinder (52) is fixedly connected with the end of the upper support arm (51) of the torque plate (5), another
End and a root post (13) for the braced frame (1) are hinged；One end of another torque load cylinder (52) with it is described
The end of another support arm (51) is fixedly connected on torque plate (5), another root post of the other end and the braced frame (1)
(13) hinged；Two torque load cylinders (52) are distributed by origin symmetry of the central point of the torque plate (5)；
Axial force load cylinder (6), one end and the axial bottom of the torque plate (5) are hinged, the other end and the braced frame
(1) pedestal (11) is hinged；
Force snesor (7) is separately positioned on each moment of flexure load cylinder (41), the torque load cylinder (52) and institute
It states on axial force load cylinder (6)；
There are two bearing blocks (23), the fan shaft (3) to pass through two for the internal coaxial arrangement from top to bottom of the fan shaft fixture (2)
A bearing (24) is rotatably arranged on two bearing blocks (23), to simulate the side when fan shaft (3) is really installed
Bound constrained；
Eight ears (43), each ears (43) and a moment of flexure are evenly arranged on the excircle of the moment of flexure disk (4)
The top of load cylinder (41) is hinged.
2. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
It is set tooth flange to state the first fixed part (21), passes through spiral shell with the top beam (12) of the braced frame (1) at the top of the set tooth flange
Bolt is fixedly connected, and bottom is fixedly connected with the fan shaft (3) top.
3. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
It is two-way flange transfer panel to state the second fixed part (22), and the bottom end at top and the fan shaft (3) is bolted to connection, bottom
Portion and the axial top of the moment of flexure disk (4) are bolted to connection.
4. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
The piston rod one end and the force snesor (7) one end for stating moment of flexure load cylinder (41) pass through flanged joint, the force snesor
(7) other end ball-type is hinged on the ears (43) of the moment of flexure disk (4).
5. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
It is candan universal joint to state third fixed part (42).
6. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
The piston rod one end for stating torque load cylinder (52) is hinged with the force snesor (7) one end ball-type, and the force snesor (7) is another
One end and the support arm (51) of the torque plate (5) pass through flanged joint.
7. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that institute
The force snesor (7) stated on axial force load cylinder (6) is arranged on the piston rod of the axial force load cylinder (6).
8. the compound static(al) and fatigue tester of aerial engine fan axis according to claim 1, which is characterized in that also
Including：
Hydraulic servo coordinated loading control device, for the moment of flexure load cylinder (41), the torque load cylinder (52) with
And the axial force load cylinder (6) is controlled.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN101368874A (en) * | 2008-09-26 | 2009-02-18 | 成都发动机（集团）有限公司 | Testing device for implementing main torque and vibrating torque to high speed rotary main shaft |
| CN201477007U (en) * | 2009-07-29 | 2010-05-19 | 中国航空动力机械研究所 | Fatigue test device for slender thin wall shaft |
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| CN103528812A (en) * | 2013-10-29 | 2014-01-22 | 成都发动机（集团）有限公司 | Shaft testing device capable of exerting two-stage combined tension-torsion loading simultaneously |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
| CN204086051U (en) * | 2014-10-17 | 2015-01-07 | 苏州东菱振动试验仪器有限公司 | The charger of torture test power |
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| JP3839983B2 (en) * | 1999-02-05 | 2006-11-01 | 株式会社鷺宮製作所 | Combined torsion / bending load testing machine |
| CN101368874A (en) * | 2008-09-26 | 2009-02-18 | 成都发动机（集团）有限公司 | Testing device for implementing main torque and vibrating torque to high speed rotary main shaft |
| CN101871826A (en) * | 2009-04-22 | 2010-10-27 | 项晓明 | Continuous test device for torsion moment/bending moment of valve and test method thereof |
| CN201477007U (en) * | 2009-07-29 | 2010-05-19 | 中国航空动力机械研究所 | Fatigue test device for slender thin wall shaft |
| CN103900811A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Rotation load applying device for tail rotor shaft fatigue test |
| CN103528812A (en) * | 2013-10-29 | 2014-01-22 | 成都发动机（集团）有限公司 | Shaft testing device capable of exerting two-stage combined tension-torsion loading simultaneously |
| CN204086051U (en) * | 2014-10-17 | 2015-01-07 | 苏州东菱振动试验仪器有限公司 | The charger of torture test power |
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| CN105352732A (en) | 2016-02-24 |
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