CN110455485B - Device for testing thermal environment impact performance of composite blade under multi-point impact excitation - Google Patents
Device for testing thermal environment impact performance of composite blade under multi-point impact excitation Download PDFInfo
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- CN110455485B CN110455485B CN201910771869.9A CN201910771869A CN110455485B CN 110455485 B CN110455485 B CN 110455485B CN 201910771869 A CN201910771869 A CN 201910771869A CN 110455485 B CN110455485 B CN 110455485B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- 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
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- 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
- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
- G01N3/307—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated by a compressed or tensile-stressed spring; generated by pneumatic or hydraulic means
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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
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/36—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by pneumatic or hydraulic means
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- 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
- G01N2203/0001—Type of application of the stress
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- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
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- G01N2203/0044—Pneumatic means
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- 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
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- G—PHYSICS
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- 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
- G01N2203/025—Geometry of the test
- G01N2203/0258—Non axial, i.e. the forces not being applied along an axis of symmetry of the specimen
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- 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
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0641—Indicating or recording means; Sensing means using optical, X-ray, ultraviolet, infrared or similar detectors
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- 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
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
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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
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
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Abstract
The invention relates to a device for testing the thermal environment impact performance of a composite blade under multi-point impact excitation, which comprises: the device comprises a power supply module, a measuring module, a multi-point impact module, a clamping module, a thermal environment module, a projectile recovery module and a platform body module; the thermal environment module is arranged on the platform body module and used for providing an adjustable high-temperature test environment; the clamping module is arranged in the thermal environment module and used for clamping and fixing a blade test piece to be tested; the multipoint impact module is arranged on the platform body module and used for simultaneously launching a plurality of projectile impact blade test pieces; the power supply module is used for supplying power to the multipoint impact module; the pill recovery module is arranged in the thermal environment module and is positioned behind the clamping module and used for recovering the pills; the measuring module is used for measuring vibration size, shot tracks, impact force and noise. The device realizes multi-point impact excitation and thermal excitation simultaneously, simulates the situation that multiple points are impacted simultaneously in the actual work of the composite material blade, and provides more real and reliable experimental data for an impact experiment.
Description
Technical Field
The invention belongs to the field of impact dynamics, and relates to a device for testing thermal environment impact performance of a composite blade under multi-point impact excitation.
Background
With the rapid progress and development of aerospace technologies, the demand for high-performance aerospace materials is gradually increased, and for a long time, research on high-speed mechanical related materials such as aircrafts and the like usually focuses on the static or low-speed characteristics of the materials, so that some problems are gradually exposed, and some serious consequences are caused. Such as many airplane bird strikes that first appeared at the end of the last century in the united states. With the rapid development of global aviation traffic, the events are more and more interesting to relevant scholars, so that the theory of impact dynamics begins to develop rapidly, and the experiment of impact dynamics is developed.
The impact dynamics experiment aims at simulating the response state of materials to high-speed impact in various environments, and a set of related professional experimental equipment is required, most of the experimental equipment which is widely applied at present is a Hopkinson pressure bar, and a device which is improved on the basis of the experimental device is widely produced and used, wherein the compression and shearing impact loads are simultaneously applied to a test piece through typical modification such as V-shaped improvement on the head parts of an incident rod and a transmission rod in the patent CN 200810017503.4; the split hopkinson pressure bar in patent CN201420107552.8 can be adapted to test pieces with various specifications. However, the two patents do not take any consideration of the test environment, which is often quite different from the actual situation;
patent CN208537320U adopts vertical drop hammer structure to accomplish the impact excitation to used one kind to prevent the emergence of the secondary impact situation in the vertical impact experiment based on photoelectric switch control's energy-absorbing pad, but this protecting against shock device structure is complicated, and is strict to relevant part performance requirement, and the cost is higher.
Patent CN201710896598.0 has adopted the light gas big gun as the impact power source, utilizes mechanical structure can load predetermined axial pressure and predetermined impact force simulation multiple mechanical environment to the sample, but this patent does not consider the thermal environment of test piece, and in fact, the aerodynamic heating environment that parts such as most steam turbine blades face when operating condition can produce apparent influence to the performance of material. The impact in high temperature environment has unique mechanical characteristics and should be one of the indispensable factors in the impact experiment.
In addition, the above experimental devices are the same as most other existing devices, and the impact sources are single-point impact, however, sometimes, for example, when considering the bird impact problem, many kinds of birds present a group movement phenomenon with certain array behavior, which often generates more than one flying bird impact phenomenon, such problem obviously has completely different mechanical properties from single-point impact, and an experimental device capable of realizing simultaneous multi-point impact should be designed to simulate such problem.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide a device for testing the thermal environment impact performance of a composite material blade under multi-point impact excitation, so as to perform a service reliability test of the blade under the multi-point impact excitation under a high-temperature condition.
The invention provides a device for testing the thermal environment impact performance of a composite blade under multi-point impact excitation, which comprises: the device comprises a power supply module, a measuring module, a multi-point impact module, a clamping module, a thermal environment module, a projectile recovery module and a platform body module;
the thermal environment module is arranged on the platform body module and used for providing an adjustable high-temperature test environment;
the clamping module is arranged in the thermal environment module and used for clamping and fixing a blade test piece to be tested;
the multipoint impact module is arranged on the platform body module and used for simultaneously launching a plurality of bullets to impact the blade test piece from different angles;
the power supply module is used for supplying power to the multipoint impact module to launch the shot;
the pill recovery module is arranged in the thermal environment module and is positioned behind the clamping module and used for recovering the pills;
the measuring module is used for measuring vibration size, shot tracks, impact force and noise.
In the device for testing the thermal environment impact performance of the composite blade under multi-point impact excitation, the multi-point impact module comprises: the device comprises an adjustable gun barrel mechanism, a flowmeter, an internal valve mechanism, a gun barrel, a pressure gauge and a gun barrel support;
the gun barrel support is fixed on the platform body module, the gun barrel is fixed on the gun barrel support, the upper end of the tail of the gun barrel is provided with an air inlet, an air discharging port and a pressure gauge, the air inlet and the air discharging port are hermetically connected with the power supply module through hoses, and the flow meter is arranged at the upper end of the head of the gun barrel;
the adjustable gun barrel mechanism is arranged at the front end of the gun barrel and comprises a plurality of gun barrels, a gun barrel mounting seat, a support column fixed on the gun barrel mounting seat, a plurality of angle adjusting modules and a plurality of gas path adjusting modules; the gun barrels are respectively connected with the gun barrel mounting seats through revolute pairs, and the air passages of the gun barrels are communicated with the air passages of the gun barrel mounting seats; the tail part of the gun barrel is provided with a projectile filling port, the head part of the gun barrel is provided with a laser collimator, and the front end of the gun barrel is connected with support columns arranged at the centers of a plurality of gun barrels through an angle adjusting module; the gun barrel mounting seat is provided with a plurality of mounting grooves for accommodating the gas path adjusting module, the gas path adjusting module comprises a rotary chute pair, a curved bar, a connecting rod, a gas path opening and closing adjusting slider and an adjusting switch, the rotary chute pair is arranged in the mounting grooves, the adjusting switch is arranged outside the mounting grooves, one end of the rotary chute pair extends out of the mounting grooves and is connected with the adjusting switch, the other end of the rotary chute pair is connected with the gas path opening and closing adjusting slider sequentially through the curved bar and the connecting rod, gas ports communicated with corresponding gun barrels are formed in the mounting grooves, and the gas path opening and closing adjusting slider can be indirectly controlled to slide along the mounting grooves by toggling the adjusting switch so as to close or open the;
the inner valve mechanism is arranged inside the front end of the gun barrel and comprises two circular valve plates, a plurality of vent holes are formed in each circular valve plate, the circular valve plates are installed in the annular grooves in the inner wall of the gun barrel, and the contact ratio of the vent holes and the circular valve plates is changed by rotating the circular valve plates so as to control the opening and closing of the gas circuit.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the angle adjusting module comprises: the gun barrel adjusting slide rail, the connecting base, the internal thread hole column, the external thread column and the gun barrel adjusting slide block are arranged on the gun barrel adjusting slide rail; the gun barrel adjusting slide rail is fixed at the front end of the gun barrel, the gun barrel adjusting slide block slides in a matched mode with the gun barrel adjusting slide rail, the other end of the gun barrel adjusting slide block is fixedly connected with the external thread column, the external thread column is matched with the internal thread hole column, the bottom of the internal thread hole column is connected with the connecting base through a revolute pair, the connecting base is fixed on the supporting column, and the adjusting of the impact direction of each gun barrel can be achieved through rotating the internal thread hole column.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the thermal environment module comprises: the heating system comprises a hot box, a plurality of heating pipes arranged on the inner wall of the hot box and a sensor feedback circuit; the top of hot case seals through thermal-insulated upper tank lid, and hot case front side is opened and is equipped with the shot incident port, and shot incident port department covers has heat-resisting printing opacity mantle, and box both sides wall is equipped with heat-resisting glass observation window, and hot bottom of the case face is for leaking hopper-shaped inclined plane, and the bottom surface center is equipped with the opening and communicates with the recovery pipeline, and the opening part is equipped with electromagnetic relay control door.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the clamping module comprises a vibration bearing table with a through hole in the center, a plurality of clamp bases are uniformly arranged around the through hole, the clamp bases are connected with the vibration bearing table through vibration springs arranged at four corners, a clamp body used for fixing the blade test piece is arranged on each clamp base, four conducting rods are arranged on each vibration bearing table, each conducting rod penetrates out of the through hole in the rear wall of the heat box and then is connected with an adjusting plate arranged behind the heat box, two positioning slide blocks are fixedly connected to the bottom surface of each adjusting plate and matched with positioning guide rails on the table body module, and the positioning slide blocks can be fixed at different positions on the positioning guide rails so as to adjust different experimental distances between the blade test piece and a light gas gun.
In the device for testing the thermal environment impact performance of the composite blade under multi-point impact excitation, the shot recovery module comprises a supporting plate, a buffer box and fine sand arranged in the buffer box, the supporting plate is fixed in the hot box and positioned behind the clamping module, the buffer box is fixed on the supporting plate, a shot receiving opening is formed in the front side of the buffer box and covered with a heat-resistant soft film, a sand containing opening is formed in the upper side of the buffer box, a sand discharging door is formed in the lower side of the buffer box and controlled to be opened and closed by an electromagnetic relay, and through holes are formed in four corners of the supporting plate for the conduction rods to penetrate out.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the power supply module is a movable integrated high-pressure gas cylinder and is connected with a corresponding gas inlet of a light gas gun barrel through a hose to supply compressed gas.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the measuring module comprises: the high-speed camera is positioned above the hot box, the laser vibration meter is positioned above the gun barrel, and the noise sensors are arranged on the front outer wall and the rear outer wall of the hot box.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the noise sensor is arranged in the spacer bush and fixed on the front outer wall and the rear outer wall of the hot box through the spacer bush, the hot box is provided with a sliding groove in the box wall opposite to the noise sensor, and a sliding block is arranged in the sliding groove.
In the device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation, the laser vibration meter is arranged on the arc-shaped support frame through the support sliding block, the arc-shaped support frame is arranged above the gun barrel, and the support sliding block can slide along the arc-shaped track on the arc-shaped support frame, so that the arc-shaped motion of the laser vibration meter is realized.
The device for testing the thermal environment impact performance of the composite material blade under multi-point impact excitation simultaneously realizes that the multi-point impact excitation and the thermal excitation simulate the situation that multiple points are impacted simultaneously in the actual work of the composite material blade vividly, and provides more real and reliable experimental data for an impact experiment.
Drawings
FIG. 1 is an overall structure diagram of a composite blade thermal environment impact performance testing device under multi-point impact excitation according to the present invention;
FIG. 2 is a block diagram of a multi-point impact module;
FIG. 3 is a diagram of an adjustable gun barrel mechanism;
FIG. 4 is a block diagram of an angle adjustment module;
FIG. 5 is an overall view of the gas path adjustment module;
FIG. 6 is a block diagram of a single gas path conditioning module;
FIG. 7 is a structural view of an internal valve mechanism;
FIG. 8 is a view of a clamping module;
FIG. 9 is a view showing the inside structure of the hot box;
FIG. 10 is a block diagram of a high speed camera above the hot box;
FIG. 11 is a schematic diagram of a laser vibrometer above the inflator;
FIG. 12 is a detail view I of the hot box side noise sensor;
FIG. 13 is a detail view II of the hot box side noise sensor;
in the figure: 1, a multi-point impact module; 2, a platform body module; 3 a pellet recovery module; 4, clamping the module; 5, a thermal environment module; 6, a measuring module; 7, an adjustable gun barrel mechanism; 8, a flow meter; 9 an internal valve mechanism; 10 gun barrels; 11 an air inlet; 12 a pressure gauge; 13 air discharge port; 14 barrel supports; 15 a projectile loading port; 16 an adjustment switch; 17 gun barrel mounting seats; 18 gun barrels; 19 laser sight; 20 gun barrel adjusting slide rails; 21 a middle support column; 22 connecting the base; 23, a hole column with internal threads; 24 externally threaded posts; 25 gun barrel adjusting slide blocks; 26 rotating the chute pair; 27 a curved bar; 28 connecting rods; 29 air ports; 30 air passage open-close adjusting slide blocks; 31 a first circular valve plate; 32 second circular valve plate; 33 adjusting plate; 34 positioning the sliding block; 35 a conductive rod; 36 a vibration spring; 37 a clamp body; 38 a clamp base; 39 vibrating the carrier table; 40 positioning the guide rail; 41 a buffer tank; 42 a box cover; 43 a support plate; 44 heating the tube; 45, heating a box; 46 a projectile entrance port; 47 an observation window; 48 electromagnetic relay control door; 49 a recovery pipeline; 50 a first support frame; 51 a longitudinal guide rail; 52 a transverse slide block; 53 high-speed video camera; 54 cross-guide rails; 55 a longitudinal slide block; 56 arc-shaped supporting frames; 57 supporting the slide; 58 laser vibrometer; 59 a noise sensor; 60 spacer sleeves; 61 sliding chutes; 62 slide block.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings.
As shown in FIG. 1, the device for testing the thermal environment impact performance of the composite blade under multi-point impact excitation of the invention comprises: the device comprises a power supply module, a measuring module 6, a multi-point impact module 1, a clamping module 4, a thermal environment module 5, a pill recovery module 3 and a platform body module 2.
The thermal environment module 5 is arranged on the stage body module 2 and used for providing an adjustable high-temperature test environment. And the clamping module 4 is arranged in the thermal environment module 5 and used for clamping and fixing a blade test piece to be tested. The multipoint impact module 1 is arranged on the table body module 2 and used for simultaneously launching a plurality of shots to impact the blade test piece from different angles. The power supply module is a movable integrated high-pressure gas cylinder, is connected with a corresponding gas inlet of the light gas gun barrel through a hose, supplies compressed gas, and further supplies power to the multi-point impact module 1 to launch the shot. The pill recovery module 3 is arranged in the thermal environment module 5 and is positioned behind the clamping module 4 for recovering the pills. The measuring module 6 is used for measuring vibration size, projectile track, impact force and noise.
As shown in fig. 2, the multipoint impact module 1 includes: an adjustable gun barrel mechanism 7, a flowmeter 8, an internal valve mechanism 9, a gun barrel 10, a pressure gauge 12 and a gun barrel support 14. The gun barrel support 14 is fixed on the platform body module 2, the gun barrel 10 is fixed on the gun barrel support 14, the upper end of the tail of the gun barrel 10 is provided with an air inlet 11, an air discharging port 13 and a pressure gauge 12, the air inlet 11 and the air discharging port 13 are both connected with the power supply module in a sealing mode through hoses to achieve air compression and transmission, and the flow meter 8 is installed at the upper end of the head of the gun barrel 10.
As shown in fig. 3, the adjustable gun barrel mechanism 7 is installed at the front end of the gun barrel 10, and includes a plurality of gun barrels 18, a gun barrel mounting seat 17, a support column 21 fixed on the gun barrel mounting seat 17, a plurality of angle adjusting modules, and a plurality of air path adjusting modules. The plurality of gun barrels 18 are respectively connected with the gun barrel mounting seat 17 through revolute pairs, and the air passages of the gun barrels are communicated; the tail part of the gun barrel 18 is provided with a bullet loading opening 15 to realize bullet loading. The head of the gun barrel 18 is provided with a laser sighting device 19 for pre-positioning the shot impact position. The front end of the gun barrel 18 is connected to a support column 21 provided at the center of the plurality of gun barrels 18 through an angle adjusting module.
As shown in fig. 4, the angle adjusting module includes: the gun barrel adjusting slide rail 20, the connecting base 22, the internal thread hole column 23, the external thread column 24 and the gun barrel adjusting slide block 25. The gun barrel adjusting slide rail 20 is fixed at the front end of the gun barrel 18, the gun barrel adjusting slide block 25 slides in a matched mode with the gun barrel adjusting slide rail 20, the other end of the gun barrel adjusting slide block is fixedly connected with the external thread column 24, the external thread column 24 is matched with the internal thread hole column 23, the bottom of the internal thread hole column 23 is connected with the connecting base 22 through a revolute pair, the connecting base 22 is fixed on the supporting column 21, and the impact direction of each gun barrel can be adjusted by rotating the internal thread hole column 23.
As shown in fig. 5 and 6, the gun barrel mounting seat 17 is provided with a plurality of mounting grooves for accommodating the gas path adjusting module, the gas path adjusting module comprises a rotary sliding groove pair 26, a curved rod 27, a connecting rod 28, a gas path open-close adjusting slider 30 and an adjusting switch 16 arranged outside the mounting grooves, the rotary sliding groove pair 26 is provided with one end extending out of the mounting groove to be connected with the adjusting switch 16, the other end of the rotary sliding groove pair 26 is connected with the gas path open-close adjusting slider 30 sequentially through the curved rod 27 and the connecting rod 28, the mounting groove is internally provided with a gas port 29 communicated with the corresponding gun barrel 18, and the gas path open-close adjusting slider 30 can be indirectly controlled to slide along the mounting groove by toggling the corresponding adjusting switch 16 to close or open the corresponding gas port 29 so as to control whether the corresponding.
As shown in fig. 7, the internal valve mechanism 9 is disposed inside the front end of the barrel 10, and includes two circular valve plates tightly attached together, wherein the first circular valve plate 31 and the second circular valve plate 32 are provided with a plurality of vent holes, the first circular valve plate 31 and the second circular valve plate 32 are installed in an annular groove on the inner wall of the barrel, and the circular valve plates are rotated to change the overlap ratio of the vent holes, thereby controlling the opening and closing of the air path.
As shown in fig. 9, the thermal environment module 5 includes: the heating box 45, the heating pipes 44 arranged on the inner wall of the heating box 45 and the sensor feedback circuit realize the control of the temperature in the box through the heating pipes 44 on the inner wall of the box body and the external sensor feedback circuit. The top end of the hot box 45 is sealed through the heat-insulating upper box cover 42, a shot entrance port 46 is formed in the front side of the hot box 45, and a heat-resistant light-transmitting soft film covers the shot entrance port 46, so that the correct positioning of the infrared aiming device 19 on the impact point of the blade test piece is ensured, and the heat exchange inside and outside the hot box 45 after the shot entrance is reduced. Two side walls of the box body are provided with heat-resistant glass observation windows 47 for relevant test recording instruments to perform test recording. The bottom surface of the hot box is a funnel-shaped inclined surface, the center of the bottom surface is provided with an opening and communicated with a recovery pipeline 49, and the opening is provided with an electromagnetic relay control door 48.
As shown in fig. 8, the clamping module 4 includes a vibration bearing table 39 with a through hole at the center, a plurality of clamp bases 38 are uniformly arranged around the through hole, the clamp bases 38 are connected with the vibration bearing table 38 through vibration springs 36 arranged at four corners, a clamp body 37 for fixing the blade test piece is arranged on the clamp base 38, four conducting rods 35 are arranged on the vibration bearing table 38, the conducting rods 35 are connected with an adjusting plate 33 arranged behind a hot box after penetrating out of the through hole on the rear wall of the hot box 45, two positioning sliders 34 are fixedly connected to the bottom surface of the adjusting plate 33, the positioning sliders 34 are matched with positioning guide rails 40 on the table body module 2, the positioning sliders 34 can be fixed at different positions on the positioning guide rails 40, so as to adjust different experimental distances between the blade test piece and the light gas gun, and realize tests of the blade test piece under different boundary conditions by changing the number of.
As shown in fig. 9, the pellet recovering module 3 includes a supporting plate 43, a buffer box 41 and fine sand disposed in the buffer box 41, the supporting plate 43 is fixed in the hot box 45 and located behind the clamping module 4, the buffer box 41 is fixed on the supporting plate 43, a pellet receiving opening is opened at the front side of the buffer box 41 and covered with a heat-resistant soft film, a sand loading opening is opened at the upper side of the buffer box 41 for filling sand, and a sand discharging door is opened at the lower side and is controlled to be opened and closed by an electromagnetic relay. Through holes are formed in four corners of the supporting plate 43 for the conduction rods 35 to penetrate out. The pill punctures the blade test piece and the pellicular entering buffer box 41, realizes the buffering, rethread hot box 45 bottom funnel-shaped inclined plane landing to electromagnetism relay control door 48 department after arranging husky door and discharging, gets into recovery pipeline 49 after controlling electromagnetism relay control door 48 to open. The recovery pipeline 49 is spirally wound and fixed in the inner cavity of the table body module 2, the upper opening of the recovery pipeline 49 is over against the normally closed electromagnetic relay control door 48 at the bottom of the hot box, the lower opening reaches the bottom surface of the cavity, the bottom surface of the cavity is an inclined surface, and the side surface of the guide table body module 2 is provided with an opening, so that the recovery and the reutilization of the shot and the fine sand are realized.
The measurement module 6 comprises three separate parts: a high-speed camera positioned above the hot box 45, a laser vibrometer positioned above the gun barrel 10 and noise sensors arranged on the front and rear outer walls of the hot box.
The high speed camera portion is shown in fig. 10. The part is positioned right above the hot box 45 and mainly comprises a first support frame 50, a longitudinal guide rail 51, a high-speed camera 53, a transverse guide rail 54, a longitudinal slide block 55 and a transverse slide block 52, and the high-speed camera can freely move in one plane to shoot the blades.
The laser vibrometer portion is shown in FIG. 11. The part is positioned right above the gun barrel 10 and mainly comprises an arc-shaped support frame 56, a support slide block 57 and a laser vibration meter 58. The supporting slide block 57 can slide along the arc-shaped track on the arc-shaped supporting frame 56, so that the laser vibration meter 58 can move along the arc-shaped track.
The noise sensor portion is shown in fig. 12 and 13. The part is positioned on the front and rear outer walls of the hot box and mainly comprises a noise sensor 59, a spacer 60, a sliding groove 61 and a sliding block 62. Four noise sensors 59 are respectively fixed on the front face and the rear face of the hot box, because the noise sensors cannot be placed in a hot environment, the noise sensors are placed on the outer wall of the hot box through a spacer sleeve 60, a sliding groove 61 is formed in the inner portion of the box wall of the hot box opposite to the noise sensors, and a sliding block 62 is arranged in the sliding groove. When the shot impacts the test piece, the sliding blocks 62 in the sliding grooves on the front wall and the rear wall move instantly to enable the noise sensor 59 to start receiving noise signals, after the noise sensor detects sound information, the sliding blocks 62 move again, the notches are closed, in this way, the sound information when the shot impacts the test piece can be measured, and the energy lost when the sound is transmitted in the hot box can be measured through the front noise sensor and the rear noise sensor.
The experimental process of the composite material blade thermal environment impact performance test device under multi-point impact excitation is as follows:
step 1: after each experimental device is correctly assembled, selecting the impact position and boundary conditions of a blade test piece, and fixing the blade test piece on a vibration bearing table through a fixture body;
step 2: connecting the light gas gun with a gas source; selecting whether to start temperature control of the hot box; and moving the high-speed camera and the laser vibration meter to a specified to-be-tested place, adjusting the posture of the laser vibration meter, and capturing the vibration of the surface of the tested blade in the normal direction. The notch at the noise sensor ensures a closed state. Meanwhile, other preparation works are done;
and step 3: the bullet loading and the shooting angle are adjusted as follows:
3.1 during single-point impact, one of the gun barrels 18 is selected, the corresponding air path is opened by using the corresponding adjusting switch 16, the internal thread hole column 23 in the rotation angle adjusting module is rotated, and the gun barrel is positioned at a preset launching angle by matching with an infrared laser collimator.
3.2 during the multiple spot impact, select a plurality of in the gun barrel 18, use corresponding regulating switch 16 to open and correspond the gas circuit, every internal thread hole post 23 that corresponds in the rotation angle adjusting module cooperates the infrared laser sight, makes every gun barrel all be in predetermined launch angle.
And 4, step 4: shot launching is realized by controlling the circular valve plates 31 and 32, and the recording of experimental data is started. The specific recording process is as follows:
measuring contact impact force by using a force sensor in the projectile to research impedance; observing the displacement and damage form of the blade by a high-speed camera; measuring the displacement or the speed of the blade by using a laser vibration meter, outputting a time domain response, and further obtaining a frequency response function to analyze system parameters such as the inherent frequency and the damping ratio of each order of the blade; the noise sensors can measure the sound information when the projectile impacts the test piece, and the energy lost by sound propagating in the hot box can be measured by the front and rear noise sensors.
And 5:
5.1 after the experimental record is finished, the control system opens the electromagnetic relay doors at the bottom of the sandbox and the hot box in sequence, so that the shot entering the sandbox and the fine sand enter the recovery pipeline together.
5.2 the fine sand containing the shot and entering the bottom in the experiment table through the recovery pipeline flows to the side opening of the experiment table under the action of the bottom inclined plane in the experiment table, enters a prepared external container, and realizes the recycling of the shot and the fine sand.
Step 6: and (5) closing each experimental device and analyzing experimental data.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the scope of the present invention, which is defined by the appended claims.
Claims (9)
1. The utility model provides a compound material blade thermal environment impact performance test device under multiple spot impact excitation which characterized in that includes: the device comprises a power supply module, a measuring module, a multi-point impact module, a clamping module, a thermal environment module, a projectile recovery module and a platform body module;
the thermal environment module is arranged on the platform body module and used for providing an adjustable high-temperature test environment;
the clamping module is arranged in the thermal environment module and used for clamping and fixing a blade test piece to be tested;
the multipoint impact module is arranged on the platform body module and used for simultaneously launching a plurality of bullets to impact the blade test piece from different angles;
the power supply module is used for supplying power to the multipoint impact module to launch the shot;
the pill recovery module is arranged in the thermal environment module and is positioned behind the clamping module and used for recovering the pills;
the measuring module is used for measuring vibration, shot tracks, impact force and noise;
the multi-point impact module includes: the device comprises an adjustable gun barrel mechanism, a flowmeter, an internal valve mechanism, a gun barrel, a pressure gauge and a gun barrel support;
the gun barrel support is fixed on the platform body module, the gun barrel is fixed on the gun barrel support, the upper end of the tail of the gun barrel is provided with an air inlet, an air discharging port and a pressure gauge, the air inlet and the air discharging port are hermetically connected with the power supply module through hoses, and the flow meter is arranged at the upper end of the head of the gun barrel;
the adjustable gun barrel mechanism is arranged at the front end of the gun barrel and comprises a plurality of gun barrels, a gun barrel mounting seat, a support column fixed on the gun barrel mounting seat, a plurality of angle adjusting modules and a plurality of gas path adjusting modules; the gun barrels are respectively connected with the gun barrel mounting seats through revolute pairs, and the air passages of the gun barrels are communicated with the air passages of the gun barrel mounting seats; the tail part of the gun barrel is provided with a projectile filling port, the head part of the gun barrel is provided with a laser collimator, and the front end of the gun barrel is connected with support columns arranged at the centers of a plurality of gun barrels through an angle adjusting module; the gun barrel mounting seat is provided with a plurality of mounting grooves for accommodating the gas path adjusting module, the gas path adjusting module comprises a rotary chute pair, a curved bar, a connecting rod, a gas path opening and closing adjusting slider and an adjusting switch, the rotary chute pair is arranged in the mounting grooves, the adjusting switch is arranged outside the mounting grooves, one end of the rotary chute pair extends out of the mounting grooves and is connected with the adjusting switch, the other end of the rotary chute pair is connected with the gas path opening and closing adjusting slider sequentially through the curved bar and the connecting rod, gas ports communicated with corresponding gun barrels are formed in the mounting grooves, and the gas path opening and closing adjusting slider can be indirectly controlled to slide along the mounting grooves by toggling the adjusting switch so as to close or open the;
the inner valve mechanism is arranged inside the front end of the gun barrel and comprises two circular valve plates, a plurality of vent holes are formed in each circular valve plate, the circular valve plates are installed in the annular grooves in the inner wall of the gun barrel, and the contact ratio of the vent holes and the circular valve plates is changed by rotating the circular valve plates so as to control the opening and closing of the gas circuit.
2. The apparatus for testing thermal environment impact performance of a composite blade under multi-point impact excitation according to claim 1, wherein the angle adjusting module comprises: the gun barrel adjusting slide rail, the connecting base, the internal thread hole column, the external thread column and the gun barrel adjusting slide block are arranged on the gun barrel adjusting slide rail; the gun barrel adjusting slide rail is fixed at the front end of the gun barrel, the gun barrel adjusting slide block slides in a matched mode with the gun barrel adjusting slide rail, the other end of the gun barrel adjusting slide block is fixedly connected with the external thread column, the external thread column is matched with the internal thread hole column, the bottom of the internal thread hole column is connected with the connecting base through a revolute pair, the connecting base is fixed on the supporting column, and the adjusting of the impact direction of each gun barrel can be achieved through rotating the internal thread hole column.
3. The apparatus for testing thermal environment impact performance of a composite blade under multi-point impact excitation according to claim 1, wherein the thermal environment module comprises: the heating system comprises a hot box, a plurality of heating pipes arranged on the inner wall of the hot box and a sensor feedback circuit; the top of hot case seals through thermal-insulated upper tank lid, and hot case front side is opened and is equipped with the shot incident port, and shot incident port department covers has heat-resisting printing opacity mantle, and box both sides wall is equipped with heat-resisting glass observation window, and hot bottom of the case face is for leaking hopper-shaped inclined plane, and the bottom surface center is equipped with the opening and communicates with the recovery pipeline, and the opening part is equipped with electromagnetic relay control door.
4. The device for testing thermal environment impact performance of composite material blades under multi-point impact excitation according to claim 3, wherein the clamping module comprises a vibration bearing table with a through hole in the center, a plurality of clamp bases are uniformly arranged around the through hole, the clamp bases are connected with the vibration bearing table through vibration springs arranged at four corners, a clamp body for fixing the blade test piece is arranged on each clamp base, four conducting rods are arranged on each vibration bearing table, the conducting rods penetrate through the through holes in the rear wall of the heat box and then are connected with an adjusting plate arranged behind the heat box, two positioning slide blocks are fixedly connected to the bottom surface of the adjusting plate, the positioning slide blocks are matched with positioning guide rails on the table body module, the positioning slide blocks can be fixed on the positioning guide rails at different positions, and then different experimental distances between the blade test piece and the light gas cannon are adjusted.
5. The device for testing the thermal environment impact performance of the composite blade under the excitation of the multipoint impact as claimed in claim 3, wherein the shot recovery module comprises a supporting plate, a buffer box and fine sand arranged in the buffer box, the supporting plate is fixed in the thermal box and located behind the clamping module, the buffer box is fixed on the supporting plate, a shot receiving opening is formed in the front side of the buffer box and covered with a heat-resistant soft film, a sand containing opening is formed in the upper side of the buffer box, a sand discharging door is formed in the lower side of the buffer box and controlled to be opened and closed by an electromagnetic relay, and through holes are formed in four corners of the supporting plate for a conduction rod to penetrate through.
6. The device for testing the thermal environment impact performance of the composite material blade under the multi-point impact excitation according to claim 1, wherein the power supply module is a movable integrated high-pressure gas cylinder and is connected with a corresponding gas inlet of a light gas gun barrel through a hose to supply compressed gas.
7. The apparatus for testing thermal environment impact performance of a composite blade under multi-point impact excitation according to claim 1, wherein the measuring module comprises: the high-speed camera is positioned above the hot box, the laser vibration meter is positioned above the gun barrel, and the noise sensors are arranged on the front outer wall and the rear outer wall of the hot box.
8. The apparatus for testing the thermal environment impact performance of a composite material blade under multi-point impact excitation according to claim 7, wherein the noise sensor is arranged in the spacer bush and fixed on the front and rear outer walls of the thermal box through the spacer bush, the thermal box is provided with a sliding groove in the inner part of the box wall opposite to the noise sensor, and a sliding block is arranged in the sliding groove.
9. The apparatus for testing thermal environment impact performance of composite material blades under multi-point impact excitation according to claim 7, wherein the laser vibration meter is mounted on the arc-shaped support frame through a support slider, the arc-shaped support frame is mounted above the gun barrel, and the support slider can slide along the arc-shaped track on the arc-shaped support frame, so as to realize the arc-shaped motion of the laser vibration meter.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103712765A (en) * | 2013-12-30 | 2014-04-09 | 北京航空航天大学 | Impact testing machine |
| RU158233U1 (en) * | 2015-07-20 | 2015-12-27 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") | INSTALLATION FOR TESTING OBJECTS FOR INTEGRATED THERMOMECHANICAL INFLUENCES |
| CN207197937U (en) * | 2017-09-11 | 2018-04-06 | 广州大学 | A kind of Hopkinson bar experimental provision |
| CN107966259A (en) * | 2017-10-30 | 2018-04-27 | 东北大学 | The impact of fiber-reinforced composite thin-wall member and hot composite test device |
| CN108444665A (en) * | 2018-03-16 | 2018-08-24 | 北京化工大学 | Rotating vane excitation system and apparatus for rotating vane vibration test system |
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN109781515A (en) * | 2019-04-02 | 2019-05-21 | 山西省计量科学研究院 | A kind of high speed impact test bullet percussion lock |
| CN109781383A (en) * | 2019-02-28 | 2019-05-21 | 大连理工大学 | The novel more sail bodies of one kind are connected into water light-gas gun emission experiment device |
| CN109827735A (en) * | 2019-04-02 | 2019-05-31 | 湘潭大学 | A kind of high-temperature vibrating analog machine |
| CN209209538U (en) * | 2018-12-12 | 2019-08-06 | 天津天鼓罗茨鼓风机有限公司 | A kind of full-automation air bubble angle adjustment device |
-
2019
- 2019-08-21 CN CN201910771869.9A patent/CN110455485B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103712765A (en) * | 2013-12-30 | 2014-04-09 | 北京航空航天大学 | Impact testing machine |
| RU158233U1 (en) * | 2015-07-20 | 2015-12-27 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") | INSTALLATION FOR TESTING OBJECTS FOR INTEGRATED THERMOMECHANICAL INFLUENCES |
| CN207197937U (en) * | 2017-09-11 | 2018-04-06 | 广州大学 | A kind of Hopkinson bar experimental provision |
| CN107966259A (en) * | 2017-10-30 | 2018-04-27 | 东北大学 | The impact of fiber-reinforced composite thin-wall member and hot composite test device |
| CN108444665A (en) * | 2018-03-16 | 2018-08-24 | 北京化工大学 | Rotating vane excitation system and apparatus for rotating vane vibration test system |
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN209209538U (en) * | 2018-12-12 | 2019-08-06 | 天津天鼓罗茨鼓风机有限公司 | A kind of full-automation air bubble angle adjustment device |
| CN109781383A (en) * | 2019-02-28 | 2019-05-21 | 大连理工大学 | The novel more sail bodies of one kind are connected into water light-gas gun emission experiment device |
| CN109781515A (en) * | 2019-04-02 | 2019-05-21 | 山西省计量科学研究院 | A kind of high speed impact test bullet percussion lock |
| CN109827735A (en) * | 2019-04-02 | 2019-05-31 | 湘潭大学 | A kind of high-temperature vibrating analog machine |
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