CN110261239A - Body force-face power-temperature couples the force application apparatus of lower material mechanical performance test - Google Patents
Body force-face power-temperature couples the force application apparatus of lower material mechanical performance test Download PDFInfo
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- CN110261239A CN110261239A CN201910539157.4A CN201910539157A CN110261239A CN 110261239 A CN110261239 A CN 110261239A CN 201910539157 A CN201910539157 A CN 201910539157A CN 110261239 A CN110261239 A CN 110261239A
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- 239000000463 material Substances 0.000 title claims abstract description 40
- 238000011056 performance test Methods 0.000 title claims abstract description 18
- 238000012360 testing method Methods 0.000 claims abstract description 82
- 239000011888 foil Substances 0.000 claims abstract description 16
- 230000005484 gravity Effects 0.000 claims abstract description 12
- 239000000523 sample Substances 0.000 claims abstract description 8
- 229910052573 porcelain Inorganic materials 0.000 claims description 21
- 230000001808 coupling effect Effects 0.000 claims description 4
- 238000003032 molecular docking Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 230000005619 thermoelectricity Effects 0.000 claims 1
- 230000008878 coupling Effects 0.000 abstract description 9
- 238000010168 coupling process Methods 0.000 abstract description 9
- 238000005859 coupling reaction Methods 0.000 abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 2
- 230000035882 stress Effects 0.000 description 15
- 238000010438 heat treatment Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000007786 learning performance Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/18—Performing tests at high or low temperatures
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0026—Combination of several types of applied forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0226—High temperature; Heating means
Abstract
The invention discloses the force application apparatus that a kind of body force-face power-temperature couples lower material mechanical performance test.The top of pull rod is connected with the heavy frame of hypergravity experimental cabin, and pull rod bottom end is connected through collet with test specimen upper end, and test specimen lower end is screwed into area loading blocks and affixed；Different sides power is applied to test specimen by the centrifugal force of the area loading blocks combination centrifuge different rotating speeds of different weight；Face power loading blocks lower end surface is placed on buffer unit, and the end of probe of three thermocouples is welded at the different location of test specimen, and foil gauge, which is mounted on, to be welded on test specimen, and the output end of three thermocouples and foil gauge is drawn by conducting wire is connected to external signal picker.The force application apparatus that the present invention uses under Elevated Gravity, it can be used for material mechanical performance under test volume power-face power-temperature coupling environment, material mechanical performance test is difficult under the conditions of can effectively solving the problems, such as hypergravity, face power, hot test, it is simple with structure, operation scheme and the higher advantage of safety coefficient.
Description
Technical field
The present invention relates under material mechanical performance the field of test technology more particularly to a kind of body force-face power-temperature coupling
The force application apparatus of material mechanical performance test.
Background technique
High-pressure turbine working blade is on active service as one of aero-engine and gas turbine hot-end component key components
When long-term work high temperature, high pressure, high revolving speed, cycling alternating load etc. couple loading environment under, be that operating condition is most disliked in engine
Bad rotatable parts, use reliability directly affect overall performance.Moving turbine blade is around engine axis high speed when military service
Rotation, effect are the position of combustion gas to be converted to the mechanical work of rotor with thermal energy, so being on active service using combustion gas expansion work
Moving turbine blade is primarily subjected to the coupling of centrifugal load, thermal force, aerodynamic loading and oscillating load in journey.Centrifugal load
The centrifugal stress of generation, belongs to body force, the bending structure blade for being overlapped long-pending superimposing thread not exclusively with radial line, while generating diameter
To tensile stress, distorting stress and bending stress.The thermal stress that thermal force generates is closely related with geometrical constraint, and geometrical constraint is got over
More, thermal stress is bigger.The aerodynamic force that aerodynamic loading generates, is a kind of surface distribution pressure, belongs to area power, it is each to act on blade
A surface is in uneven distribution along Ye Gao and leaf width direction.Therefore, moving turbine blade is in radial tensile stress, distorting stress, curved
Shear-deformable, stretcher strain and torsional deformation occurs simultaneously under the coupling of transverse stress and thermal stress, this is clearly different from reality
Test the deformational behavior under the uniaxial stress state of room.
But the performance data of current aero engine turbine blades material is mainly from the mechanical property of laboratory standard test specimen
It can data.Although standard specimen mechanical performance data can design for blade strength provide experimental basis to a certain extent, with
Practical blade is compared, standard specimen during performance test can not concentrated expression centrifugal load-thermal force coupling condition to leaf
The influence of piece microstructure and crack propagation path.So the prior art, which has lacked, to be surveyed according to engine blade work condition environment
The device and mode of the mechanical property of test material material.
Summary of the invention
The present invention need to be to solve to be made for body force under the conditions of above-mentioned hypergravity, hot test-face power-temperature coupling
It the problem of with lower material properties test, provides that a kind of assembly is simple, coefficient easy to use, safe is high, and can be used for hypergravity work
The force application apparatus of the Mechanics Performance Testing of condition.
The present invention will couple material properties test under environment for high revolving speed-high temperature and provide a kind of body force-face power-temperature coupling
The force application apparatus of lower material mechanical performance test is closed, the key for solving material at high temperature Mechanics Performance Testing under high speed rotation state is difficult
Topic.Using the device, the mechanics of materials under environment is coupled by body force-face power-temperature under Elevated Gravity, can be obtained in real time
Performance data.
The technical solution adopted by the present invention is that:
The force application apparatus is placed in hypergravity experimental cabin, and the force application apparatus includes pull rod, wire fixing device, folder
Head, test specimen, tightens nut and face power loading blocks at thermocouple；The top of pull rod is connected with the heavy frame of hypergravity experimental cabin, pull rod
Be mainly used to bear material properties test during body force and face force coupling action generation tensile stress；Pull rod bottom end is through collet
It is connected with test specimen upper end, test specimen is the sample of material mechanical performance to be tested；Test specimen lower end is equipped with external screw thread, test specimen lower end it is outer
It is threaded into the threaded hole of area loading blocks and is fastenedly connected by tightening nut；Area loading blocks specially have adjustable
The block structure for saving own wt, applies test specimen by the centrifugal force of the area loading blocks combination centrifuge different rotating speeds of different weight
Add different sides power；Face power loading blocks lower end surface is placed on buffer unit, and buffer unit is placed in the bottom of hypergravity experimental cabin；Three
The end of probe of root thermocouple is welded at the different location of test specimen, and foil gauge, which is mounted on, to be welded on test specimen, three thermocouples and
The output end of foil gauge is drawn by conducting wire is connected to external signal picker, is equipped with multiple wire fixing devices in the middle part of pull rod, leads
Line draws through wire fixing device and fixes position.
The collet upper surface and lower end surface are equipped with threaded hole, and pull rod bottom end screws on the collet being connected to
In the threaded hole of end face, also there are external screw thread, the spiral shell for screwing into the collet upper surface being connected to of test specimen upper end in test specimen upper end
In pit.
The pull rod top is equipped with outward flange, offers on outward flange for connecting material mechanical property test cabin load
The fixing threaded hole of device, bolt pass through the bearing that material mechanical performance experimental cabin is fixed on pull rod top by fixing threaded hole.
The wire fixing device includes the first fixed ring, the second fixed ring, fixed porcelain seat and porcelain seat guard member；First is fixed
Ring and the second fixed ring all have half round cut, and docking is formed and is sleeved between the first fixed ring and the second fixed ring half round cut
Circular port outside pull rod；Porcelain seat guard member is fixed by bolts in the second fixed ring side, porcelain seat guard member and the second fixed ring
Between be clamped with fixed porcelain seat, the perforative hole of output lead for thermocouple and foil gauge is offered on fixed porcelain seat.
The force application apparatus is placed in the Elevated Gravity of centrifuge.
It is also equipped with high temperature furnace, heavy frame, signal picker and wiring frame in the hypergravity Laboratory Module, in high temperature furnace
Intracavity bottom places buffer unit, places heavy frame in high temperature furnace inner cavity top, in the heavy frame and buffering dress of high temperature furnace chamber
The force application apparatus is placed between setting；The conducting wire of signal picker output leads centrifuge principal axis diversion by wiring frame and weak signal
The connection of scheming main shaft conducting slip ring, then connect with ground observing and controlling center；High temperature furnace is provided with three road forceful electric power independent loops, three Lu Qiang
The heater that internal different zones are heated in electrically independent circuit control is heated at high temperature, and three, ground forceful electric power independent loop is passed through
Centrifuge principal axis leads the wiring frame that centrifuge principal axis leads centrifuge principal axis conducting slip ring access hypergravity Laboratory Module.
The beneficial effects of the present invention are:
The force application apparatus that the present invention uses under Elevated Gravity can be used for test volume power-face power-temperature coupling environment
Lower material mechanical performance, material mechanical performance test is difficult under the conditions of can effectively solving the problems, such as hypergravity, face power, hot test,
It is simple with structure, operation scheme and the higher advantage of safety coefficient.The device is suitble under 1g-2000g Elevated Gravity, temperature
From -1250 DEG C of room temperature.
Detailed description of the invention
Fig. 1 is force application apparatus main view；
Fig. 2 is the structure three-view diagram of pull rod；
Fig. 3 is the schematic diagram of wire fixing device.
Fig. 4 is the structural schematic diagram of Elevated Gravity mechanical property testing system of the present invention.
In figure: pull rod 1, collet 3, thermocouple 4, test specimen 5, tightens nut 6, face power loading blocks 7 at wire fixing device 2；Gu 2-1.
Determine screw hole；The first fixed ring of 3-1.；The second fixed ring of 3-2；3-3 fixes porcelain seat；3-4 porcelain seat guard member.
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples.
As shown in Figure 1, force application apparatus is placed in hypergravity experimental cabin, force application apparatus includes pull rod 1, wire fixing device 2, collet
3, thermocouple 4, test specimen 5, deflation nut 6 and face power loading blocks 7；The top of pull rod 1 is connected with the heavy frame of hypergravity experimental cabin,
Pull rod 1 is mainly used to the tensile stress of body force and the generation of face force coupling action during receiving material properties test；1 bottom end of pull rod
It is connected through collet 3 with 5 upper end of test specimen, for fixing test specimen 5, test specimen 5 is the sample of material mechanical performance to be tested.
5 lower end of test specimen is equipped with external screw thread, in the threaded hole for screwing into area loading blocks 7 of 5 lower end of test specimen and leads to
It crosses deflation nut 6 to be fastenedly connected, connects test specimen 5 and face power loading blocks 7 by tightening nut 6, tighten nut 6 and be used to connect test specimen
5 and face power loading blocks 7；Area loading blocks 7 are specially the block structure with adjustable own wt, and area loading blocks 7 are super
Face power is applied to test specimen 5 by the centrifugal force that own wt generates under gravity environment, passes through 7 knot of area loading blocks of different weight
The centrifugal force for closing centrifuge different rotating speeds applies different sides power to test specimen 5；Power loading blocks 7 lower end surface in face is placed on buffer unit
On, buffer unit is placed in the bottom of hypergravity experimental cabin, and the buffer unit of specific implementation uses buffer stopper, and buffer unit prevents power
The fracture of test specimen 5 generates destruction to test specimen cabin during learning performance test；The end of probe of three thermocouples 4 is welded on test specimen 5 not
At position, for testing the experimental temperature of test specimen 5, foil gauge, which is mounted on, to be welded on test specimen 5, and thermocouple 4 and foil gauge are used
Come test experiments temperature and strain, the output end of three thermocouples 4 and foil gauge is drawn by conducting wire to be connected to external signal and adopt
Storage is equipped with multiple wire fixing devices 2 in the middle part of pull rod 1, and conducting wire draws through wire fixing device 2 and fixes position.
3 upper surface of collet and lower end surface are equipped with threaded hole, and 1 bottom end of pull rod screws into 3 upper end of collet being connected to
In the threaded hole in face, also there are external screw thread, the spiral shell for screwing into 3 upper surface of collet being connected to of 5 upper end of test specimen in 5 upper end of test specimen
In pit, so that 1 bottom end of pull rod is connected through collet 3 with 5 upper end of test specimen.Collet 3 is used to fix test specimen 5, is mainly used to hold
The tensile stress that body force and face force coupling action generate during by material properties test.
As shown in Fig. 2, 1 top of pull rod is equipped with outward flange, offer on outward flange for connecting material mechanical property test
The fixing threaded hole 2-1 of cabin bearing, bolt pass through fixing threaded hole 2-1 and material mechanical performance test are fixed on 1 top of pull rod
The bearing in cabin.
As shown in figure 3, wire fixing device 2 includes the first fixed ring 3-1, the second fixed ring 3-2, fixed porcelain seat 3-3 and porcelain seat
Guard member 3-4；First fixed ring 3-1 and the second fixed ring 3-2 all has half round cut, and the first fixed ring 3-1 and second is fixed
Docking forms the circular port being sleeved on outside pull rod 1 between ring 3-2 half round cut, and pull rod 1 is cylindrical bar；Porcelain seat guard member 3-4 is logical
The bolt for crossing two sides is fixed on the second side fixed ring 3-2, is clamped between porcelain seat guard member 3-4 and the second fixed ring 3-2 solid
Determine porcelain seat 3-3, bolt also passes through fixed porcelain seat 3-3, the output for thermocouple 4 and foil gauge is offered on fixed porcelain seat 3-3
The perforative hole of conducting wire.
Wire fixing device 2 is used to fix the extension lead of thermocouple and foil gauge, prevents them in mechanical test process interrupt
It splits.
Force application apparatus is placed in the Elevated Gravity of centrifuge.Hypergravity experimental cabin is the mechanics of materials under Elevated Gravity
Energy experimental cabin, is placed in the hanging basket of centrifuge.
As shown in figure 4, being also equipped with high temperature furnace, heavy frame, signal picker and cloth in specific implementation hypergravity Laboratory Module
Coil holder, places buffer unit in high temperature furnace intracavity bottom, heavy frame is placed in high temperature furnace inner cavity top, in holding for high temperature furnace chamber
Force application apparatus is placed between power frame and buffer unit；The conducting wire of signal picker output passes through wiring frame and weak signal diversion scheming
Main shaft leads the connection of centrifuge principal axis conducting slip ring, then connect with ground observing and controlling center；High temperature furnace is provided with three road forceful electric power and independently returns
Road, the heater 18 that internal different zones are heated in the control of three road forceful electric power independent loops is heated at high temperature, by three, ground forceful electric power
Independent loop leads centrifuge principal axis by centrifuge principal axis and leads the wiring that centrifuge principal axis conducting slip ring accesses hypergravity Laboratory Module
Frame；Centrifuge principal axis leads centrifuge principal axis and leads centrifuge principal axis conducting slip ring to be connected with powering shelf.I.e. by wiring frame, by first
A forceful electric power independent loop is connected with heating zone on high temperature furnace, and second forceful electric power independent loop is connected with heating zone in high temperature furnace,
Third forceful electric power independent loop is connected with heating zone under high temperature furnace.
In specific implementation, three independent control temperature extension leads for controlling high temperature furnace are accessed into signal picker, signal
Collector is digital signal from analog-signal transitions by the temperature signal of receiving；Digital signal passes through wiring frame and signal slip ring
Connection, then connect with ground observing and controlling center.
The Mechanics Performance Testing course of work of apparatus of the present invention is as follows:
Step 1: test specimen 5 is connected to 1 lower end of pull rod with collet 3, thermocouple 4 and foil gauge are welded on test specimen 5；
Step 2: then hypergravity Laboratory Module is placed in the hanging basket of centrifuge, high temperature is placed in hypergravity Laboratory Module
Furnace, high temperature furnace intracavity bottom place buffer unit, heavy frame are placed in high temperature furnace inner cavity top, in the heavy frame of high temperature furnace chamber
Force application apparatus is placed between buffer unit, installs the test specimen 5 for needing to heat；
Step 3: the conducting wire for the thermocouple for being welded on 5 surface temperature measurement of test specimen is connected with signal picker, signal picker
The analog signal of temperature and strain will be received, and is digital signal by analog-signal transitions；
Step 4: three, ground forceful electric power independent loop is connected respectively to the upper, middle and lower heating zone of high temperature furnace, so that high temperature
The heating zone of furnace upper, middle and lower three is independently heated, and different heating temperatures is arranged in different heating zones；
Step 5: install tachometer in centrifuge shaft, by the tacho signal line being mounted in centrifuge shaft with it is weak
Signal leads centrifuge principal axis and leads the connection of centrifuge principal axis conducting slip ring, controls high temperature furnace using three thermocouples on heating device
Real time temperature and the rate of heat addition control centrifuge speed using tachometer, are applied to answering on test specimen 5 using following formula calculating
Power F:
F=ma=mR (2 π N/60)2
Wherein, m is the quality of test specimen 5；A is centrifugal acceleration, and R is the effective distance that test specimen 5 arrives centrifuge shaft axis；
N is the revolving speed of centrifuge.
The present invention is in test specimen test process, test specimen stress are as follows: while by temperature, the centrifugal stress for generation of being self-possessed
The face power generated with face power loading blocks.
The features of the present invention:
1) by being welded on the foil gauge of test specimen active section, stress-strain of the test specimen under stress can be obtained in real time
Curve, and then the dynamic stress-strain curve for obtaining material under centrifugal force-high temperature coupling can be tested, obtain the mechanics of materials
Results of property；
2) centrifugal force can be changed by control speed dynamic in experimentation, and then the face power that can be applied on test specimen；
3) by change face power loading blocks weight, change the face power being applied on test specimen；
4) temperature different by 3rd area of thermocouple energy independent control heating device realizes samming heating or gradient-heated,
And then the Temperature Distribution of test specimen 5 can be set as needed.
The present invention assembly it is simple, easy to use, by thermocouple and foil gauge can obtain in real time sample surfaces temperature and
Stress variation solves the problems, such as that material mechanical performance test can not be carried out under Elevated Gravity.The present invention is suitble to 1g-
Under 2000g Elevated Gravity, temperature is detected in the range of -1250 DEG C of room temperature.
Claims (6)
1. the force application apparatus that a kind of body force-face power-temperature couples lower material mechanical performance test, it is characterised in that: described
Force application apparatus is placed in hypergravity experimental cabin, and the force application apparatus includes pull rod (1), wire fixing device (2), collet (3), thermoelectricity
Even (4), test specimen (5) tighten nut (6) and face power loading blocks (7)；The top of pull rod (1) and the heavy frame of hypergravity experimental cabin
It is connected, pull rod (1) is mainly used to the tensile stress of body force and the generation of face force coupling action during receiving material properties test；It draws
Bar (1) bottom end is connected through collet (3) with test specimen (5) upper end, and test specimen (5) is the sample of material mechanical performance to be tested；Test specimen (5)
Lower end is equipped with external screw thread, in the threaded hole for screwing into area loading blocks (7) of test specimen (5) lower end and by tightening nut
(6) it is fastenedly connected；Area loading blocks (7) are specially the block structure with adjustable own wt, pass through the area of different weight
Loading blocks (7) combine the centrifugal force of centrifuge different rotating speeds to apply different sides power to test specimen (5)；Face power loading blocks (7) lower end surface
It is placed on buffer unit, buffer unit is placed in the bottom of hypergravity experimental cabin；The end of probe of three thermocouples (4) is welded on examination
At the different location of part (5), foil gauge, which is mounted on, to be welded on test specimen (5), the output end of three thermocouples (4) and foil gauge by
Conducting wire, which is drawn, is connected to external signal picker, is equipped with multiple wire fixing devices (2) in the middle part of pull rod (1), conducting wire is filled through solidus
(2) are set to draw and fix position.
2. the force dress that a kind of body force according to claim 1-face power-temperature couples lower material mechanical performance test
It sets, it is characterised in that: collet (3) upper surface and lower end surface are equipped with threaded hole, the company of screwing into of pull rod (1) bottom end
In the threaded hole of collet (3) upper surface being connected to, also there are external screw thread, the company of screwing into of test specimen (5) upper end in test specimen (5) upper end
In the threaded hole of collet (3) upper surface being connected to.
3. the force dress that a kind of body force according to claim 1-face power-temperature couples lower material mechanical performance test
It sets, it is characterised in that: pull rod (1) top is equipped with outward flange, offers on outward flange for connecting material mechanical property
The fixing threaded hole (2-1) of experimental cabin bearing, bolt pass through fixing threaded hole (2-1) and material power are fixed on pull rod (1) top
Learn the bearing in performance test cabin.
4. the force dress that a kind of body force according to claim 1-face power-temperature couples lower material mechanical performance test
It sets, it is characterised in that: the wire fixing device (2) includes the first fixed ring (3-1), the second fixed ring (3-2), fixed porcelain seat
(3-3) and porcelain seat guard member (3-4)；First fixed ring (3-1) and the second fixed ring (3-2) all have half round cut, and first is solid
Determine docking formation between ring (3-1) and the second fixed ring (3-2) half round cut and is sleeved on the circular port of pull rod (1) outside；Porcelain seat is protected
Guard (3-4) is fixed by bolts in the side the second fixed ring (3-2), porcelain seat guard member (3-4) and the second fixed ring (3-2) it
Between be clamped with fixed porcelain seat (3-3), offer on fixed porcelain seat (3-3) and passed through for the output lead of thermocouple (4) and foil gauge
The hole worn.
5. the force dress that a kind of body force according to claim 1-face power-temperature couples lower material mechanical performance test
It sets, it is characterised in that: the force application apparatus is placed in the Elevated Gravity of centrifuge.
6. the force dress that a kind of body force according to claim 1-face power-temperature couples lower material mechanical performance test
It sets, it is characterised in that: it is also equipped with high temperature furnace, heavy frame, signal picker and wiring frame in the hypergravity Laboratory Module,
High temperature furnace intracavity bottom place buffer unit, high temperature furnace inner cavity top place heavy frame, high temperature furnace chamber heavy frame and
The force application apparatus is placed between buffer unit；The conducting wire of signal picker output passes through wiring frame and weak signal diversion scheming master
The connection of spindle guide centrifuge principal axis conducting slip ring, then connect with ground observing and controlling center；High temperature furnace is provided with three road forceful electric power independent loops,
The heater (18) that internal different zones are heated in the control of three road forceful electric power independent loops is heated at high temperature, and three, ground forceful electric power is only
Centrifuge principal axis is led by centrifuge principal axis and leads the wiring frame that centrifuge principal axis conducting slip ring accesses hypergravity Laboratory Module in vertical circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910539157.4A CN110261239B (en) | 2019-06-20 | 2019-06-20 | Force application device for testing mechanical properties of materials under coupling of volume force, surface force and temperature |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910539157.4A CN110261239B (en) | 2019-06-20 | 2019-06-20 | Force application device for testing mechanical properties of materials under coupling of volume force, surface force and temperature |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110261239A true CN110261239A (en) | 2019-09-20 |
| CN110261239B CN110261239B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910539157.4A Active CN110261239B (en) | 2019-06-20 | 2019-06-20 | Force application device for testing mechanical properties of materials under coupling of volume force, surface force and temperature |
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| CN (1) | CN110261239B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526851A (en) * | 2022-04-25 | 2022-05-24 | 中国飞机强度研究所 | Method for measuring thermal stress of metal-composite material mixed structure for airplane |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1928529A (en) * | 2005-09-09 | 2007-03-14 | 侯贵仓 | Test clamp for disc blade of aircraft engine |
| CN102539135A (en) * | 2011-12-31 | 2012-07-04 | 北京航空航天大学 | Thermal mechanical fatigue test system for hollow air-cooled turbine blade |
| CN202803325U (en) * | 2012-08-17 | 2013-03-20 | 湖南中宏重型机器有限公司 | Flexible vertical mill |
| CN103048185A (en) * | 2012-12-14 | 2013-04-17 | 华南理工大学 | Loading device of asphalt mixture cylinder specimen and test method thereof |
| CN103267682A (en) * | 2013-05-13 | 2013-08-28 | 东南大学 | Device and method for testing material creep under coupling action of tensile stress and environment |
| CN106525564A (en) * | 2016-11-03 | 2017-03-22 | 兰州大学 | Heat shock-mechanical coupling loading and testing system |
| CN207516030U (en) * | 2017-10-13 | 2018-06-19 | 人本集团有限公司 | The detection device of hub bearing of truck |
| CN109540690A (en) * | 2018-11-13 | 2019-03-29 | 河海大学 | A kind of pile-soil interface mechanical property testing device based on temperature control triaxial apparatus |
| CN210923331U (en) * | 2019-06-20 | 2020-07-03 | 浙江大学 | Force application device for testing mechanical properties of material under coupling of volume force, surface force and temperature |
-
2019
- 2019-06-20 CN CN201910539157.4A patent/CN110261239B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1928529A (en) * | 2005-09-09 | 2007-03-14 | 侯贵仓 | Test clamp for disc blade of aircraft engine |
| CN102539135A (en) * | 2011-12-31 | 2012-07-04 | 北京航空航天大学 | Thermal mechanical fatigue test system for hollow air-cooled turbine blade |
| CN202803325U (en) * | 2012-08-17 | 2013-03-20 | 湖南中宏重型机器有限公司 | Flexible vertical mill |
| CN103048185A (en) * | 2012-12-14 | 2013-04-17 | 华南理工大学 | Loading device of asphalt mixture cylinder specimen and test method thereof |
| CN103267682A (en) * | 2013-05-13 | 2013-08-28 | 东南大学 | Device and method for testing material creep under coupling action of tensile stress and environment |
| CN106525564A (en) * | 2016-11-03 | 2017-03-22 | 兰州大学 | Heat shock-mechanical coupling loading and testing system |
| CN207516030U (en) * | 2017-10-13 | 2018-06-19 | 人本集团有限公司 | The detection device of hub bearing of truck |
| CN109540690A (en) * | 2018-11-13 | 2019-03-29 | 河海大学 | A kind of pile-soil interface mechanical property testing device based on temperature control triaxial apparatus |
| CN210923331U (en) * | 2019-06-20 | 2020-07-03 | 浙江大学 | Force application device for testing mechanical properties of material under coupling of volume force, surface force and temperature |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526851A (en) * | 2022-04-25 | 2022-05-24 | 中国飞机强度研究所 | Method for measuring thermal stress of metal-composite material mixed structure for airplane |
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