CN205317480U - High -speed rotor blade flies to take off test device - Google Patents

Abstract

The utility model provides a high -speed rotor blade flies to take off test device, it includes: actuating system, vacuum fuel detonation suppressant system, lubrication and cooling system and monitoring and control system, driving motor is connected with the rotor test piece through transition drive mechanism, and vacuum fuel detonation suppressant system includes a vacuum chamber, still is equipped with one in the vacuum chamber and flies to lose the protection casing, flies to lose a rotatory space of the interior formation rotor of protection casing and a blade and flies to lose the protection space, and rotor rotation space and blade fly to separate through the buffering baffle between the mistake protection space. Flying in the vacuum chamber is equipped with the buffering baffle in losing the protection casing, but the blade can stop in the blade flies to lose the protection space after the blade on the rotor test piece flew to take off, and the blade that flies like this to take off just can not bump with rotatory rotor test piece, but assurance test can the normal clear like this, and the while is effective assurance test personnel and testing equipment's safety also to ensure the rotation security of engine rotor, provide the technological means of important real example foundation for engine design stereotypes.

Description

High speed rotor blade flies off assay device

Technical field

This utility model relates to aeroengine rotor mechanical test technical field, flies off assay device for simulated engine rotor fan blade when high speed rotating particularly to a kind of.

Background technology

Along with the continuous progress of scientific and technical development and society, the requirement of safety in production is become more and more higher by people, and particularly the safety of high-speed rotating machine is increasingly subject to people's attention. Device many employings high-speed rotating equipments such as automobile engine flywheel, Centrufugal compressor impeller, turbocharger rotor, aeroengine rotor are tested its intensity and safety. As Chinese utility model patent (patent No.: 201320527462.X) discloses a kind of high speed rotating testing machine, including test cavity, it is contained in test cavity body for testing the rotor-support-foundation system that rotor carries out testing, drives the drive system of rotor-support-foundation system and control the revolution speed control system of rotor-support-foundation system rotating speed; Drive system includes: drive motor; The speeder that also rotor driven system high-speed rotates it is connected with drive motor; Rotor-support-foundation system includes: test rotor fixture; Main shaft, is connected with test rotor fixture and is driven rotation by speeder; Antivibrator, is enclosed within main shaft external support main shaft; Test cavity is with vacuum orifice; In test cavity body, surrounding rotor system is provided with multilamellar containing ring, and each containing passes through between ring to be arranged on the spacing block connection containing ring end. Rotor, using high speed rotating rotor as subjects, is accelerated by this utility model by acceleration system, model rotor duty under high speed rotating, the performance requirement of the test resistance to high speed centrifugation load effect of rotor.

But for aeroengine rotor, except carrying out high speed rotating test, also need to carry out rotor fan blade and fly off test (FanBladeOut, it is called for short FBO), need fan blade is come off the imbalance produced and engine destructive is analyzed research by shock loading, thus verify aeroplane engine function contain damaged part at least operate 15 seconds missing of ignition, and its install joint also do not lose efficacy.Under the circumference of the high-speed rotation, rotor rotational characteristic after leaf abscission is carried out test checking, guarantee the rotation safety of rotor, can provide the technological means of important excess syndrome foundation for electromotor design typification, therefore blade flies off test and has vital effect in the design of aero-engine. Model rotor fan blade flies off experimental technique and has highly difficult, high technology content and high risk feature. At blade from after rotor flies off, the operating mode of rotor can from general high speed rotating time operating mode can produce very big different, therefore existing high speed rotating testing equipment has been difficult to this rotor fan blade and has flown off test. It is all directly be connected rotor with electromotor to test that current rotor fan blade flies off test, and the cost of test thus can be made to be greatly improved.

Utility model content

The shortcoming of prior art in view of the above, the purpose of this utility model is in that to provide a kind of rotor blade flying off test for simulating fan blade to fly off assay device.

For achieving the above object and other relevant purposes, this utility model provides a kind of high speed rotor blade to fly off assay device, comprising: drive system, described drive system is used for driving rotor test part high speed rotating; Vacuum anti-explosion system, described vacuum anti-explosion system includes a vacuum chamber, being provided with vacuum extractor and testpieces mounting bracket in described vacuum chamber, described testpieces mounting bracket is for supporting rotor test part at the trial, and described vacuum extractor is for carrying out evacuation process to described vacuum chamber; Fly to lose protective cover, the described mistake protective cover that flies is positioned at described vacuum chamber, described fly to lose in protective cover form a rotor revolution space and a blade flies to lose protective zone, described rotor revolution space and described blade fly to be separated by buffering dividing plate between mistake protective zone, during test, the fan section of rotor test part is positioned at described rotor revolution space; Lubricating and cooling system, described lubricating and cooling system provides lubricating oil for the bearing on the bearing and testpieces mounting bracket of described drive system; Monitoring and control system, described drive system, vacuum anti-explosion system, lubricating and cooling system are all connected with described monitoring and control system, and described monitoring and control system are for being controlled described drive system, vacuum anti-explosion system, lubricating and cooling system, monitor.

Preferably, described transition drive mechanism includes the first diaphragm coupling, output shaft, the second diaphragm coupling, one end of described output shaft is connected with the motor shaft of described drive motor by described first diaphragm coupling, and the other end of described output shaft is connected by the rotating shaft of described second diaphragm coupling with described rotor test part.

Preferably, it is additionally provided with an overload protective device between described output shaft and described first diaphragm coupling.

Preferably, described output shaft be connected with laser displacement sensor, described testpieces mounting bracket is provided with vibrating sensor.

Preferably, described vacuum chamber includes nacelle and lower nacelle two parts, and described upper nacelle is semicircular structure, and described lower nacelle is square structure, and described upper nacelle seals with described lower nacelle and coordinates.

Preferably, described vacuum chamber seals with described output shaft and coordinates, described lower nacelle is provided with an adpting flange, described adpting flange is provided with blind flange, the installing hole of the described output shaft described blind flange of traverse, the rear and front end of described installing hole is provided with axle sleeve, is provided with sealing ring between two axle sleeves, and described output shaft is coordinated with the sealing of described installing hole by described sealing ring.

Preferably, the bottom of described vacuum chamber is grade slab, described grade slab is provided with the bottom mounting bar of a frame-like, described bottom mounting bar is fixed on described grade slab, described bottom mounting bar seals with described grade slab and coordinates, the side plate of described lower nacelle is fixing with described bottom mounting bar to be connected, and is provided with sealing ring between side plate and the described bottom mounting bar of described lower nacelle.

Preferably, the described mistake protective cover that flies includes a circular protective cover shell, described buffering dividing plate is that circle is embedded in described protective cover shell, described buffering dividing plate surrounds described rotor revolution space, forming described blade between described protective cover shell and described buffering dividing plate to fly to lose protective zone, described blade flies to lose the top of protective zone and sidewall is provided with lead.

Preferably, described lubricating and cooling system includes, by main fuel tank, oil pump, cooler, filter, being provided with degassing tower and gs-oil separator in described main fuel tank.

As mentioned above, high speed rotor blade of the present utility model flies off assay device and has the advantages that this high speed rotor blade flies off assay device by drive system rotor driven testpieces high speed rotating, the test that the fan blade on rotor test part flies off is simulated in vacuum chamber, flying in vacuum chamber is lost in protective cover and is provided with buffering dividing plate, blade on rotor test part can rest on blade and fly to lose in protective zone by blade after flying off, the blade so flown off would not collide with the rotor test part rotated, so can be normally carried out by guarantee test, also can effectively ensure that the safety of testing crew and testing equipment simultaneously. simultaneously by monitoring and the operation of whole device can be controlled and detect by control system, thus can effectively ensure that the operation that this assay device is safe and reliable, rotor rotational characteristic after leaf abscission is carried out test checking, to guarantee the rotation safety of engine rotor, provide the technological means of important excess syndrome foundation for electromotor design typification.

Accompanying drawing explanation

Fig. 1 is the structured flowchart of this utility model embodiment.

Fig. 2 is the overall structure schematic diagram of this utility model embodiment.

Fig. 3 is the structural representation of this utility model embodiment drive system.

Fig. 4 is the structural representation of this utility model embodiment arrestment mechanism.

Fig. 5 is the front view of this utility model embodiment vacuum chamber.

Fig. 6 is the side view of this utility model embodiment vacuum chamber.

Fig. 7 is the sealing schematic diagram bottom this utility model embodiment vacuum chamber.

Fig. 8 is the sealing mechanism schematic diagram of this utility model embodiment vacuum chamber and output shaft.

Fig. 9 is the structural representation that this utility model embodiment flies to lose protective cover.

Figure 10 is the vertical structure schematic diagram that this utility model embodiment flies to lose protective cover.

Element numbers explanation

1, drive system 11, drive system mounting seat 12, floor installation plate 13, drive motor the 14, first diaphragm coupling 15, overload protective device 16, arrestment mechanism 161, brake 162, spring bearing 17, output shaft 18, torque sensor the 19, first diaphragm coupling 20, support.

2, vacuum anti-explosion system 21, vacuum chamber 22, fly to lose protective cover 211, upper nacelle 212, lower nacelle 213, bottom mounting bar 214, bottom sealing ring 215, blind flange 216, axle sleeve 217, sealing ring 218, hanger 219, switching mechanism 220, trip bolt 221, machined surface 222, adpting flange 223, sealing ring 224, sealing ring 225, trip bolt 226, protective cover shell 227, cabin section gusset 228, buffering dividing plate 229, padded coaming 230, top stereotype 231, side stereotype 232, blade flies to lose protective zone 233, rotor revolution space.

3, lubricating and cooling system 4, monitoring and control system 5, rotor test part 50, the rotating shaft 51 of rotor test part, testpieces mounting bracket 52, testpieces mounting bracket 53, rotating shaft position-limited rack 6, ground 7, grade slab 8, test specimen installing plate.

Detailed description of the invention

By particular specific embodiment, embodiment of the present utility model being described below, those skilled in the art the content disclosed by this specification can understand other advantages of the present utility model and effect easily.

Refer to Fig. 1 to Figure 10. Notice, the structure of this specification institute accompanying drawings depicted, ratio, size etc., all only in order to coordinate the disclosed content of description, understand for those skilled in the art and read, it is not limited to the enforceable qualifications of this utility model, therefore do not have technical essential meaning, the adjustment of the modification of any structure, the change of proportionate relationship or size, under not affecting effect that this utility model can be generated by and the purpose that can reach, all should still drop on the disclosed technology contents of this utility model and obtain in the scope that can contain. Simultaneously, in this specification cited as " on ", D score, "left", "right", " centre " and " one " etc. term, it is merely convenient to understanding of narration, and it is not used to limit the enforceable scope of this utility model, the change of its relativeness or adjustment, changing under technology contents without essence, when being also considered as the enforceable category of this utility model.

As shown in Figure 1, this utility model provides a kind of high speed rotor blade to fly off assay device, it includes mainly including drive system 1, vacuum anti-explosion system 2, lubricating and cooling system 3 and monitoring and 4 four parts of control system, and drive system 1, vacuum anti-explosion system 2, lubricating and cooling system 3 are all connected with monitoring and control system 4. Wherein drive system 1 is mainly used in driving high speed rotor testpieces 5 high speed rotating, makes the fan blade on high speed rotor testpieces 5 fly off. Vacuum anti-explosion system 2 ensures that simulation high speed rotor testpieces fan blade flies off working condition tests safety, reduces fan blade air blast frictional heating and power attenuation. Lubricating and cooling system 3 supplies lubricating oil to equipment in drive system and high speed rotor testpieces and it is lubricated and cools down. Monitor control system 4 shows for the relevant parameter of high speed rotor testpieces, drive system, vacuum anti-explosion system and lubricating and cooling system, reports to the police, controls, regulates and interlock logic protection, concentrates on control station and controls to run and monitoring.

As in figure 2 it is shown, this assay device is arranged on ground 6, ground 6 is provided with grade slab 7, and grade slab 7 is connected with ground by bolt, and drive system 1, vacuum anti-explosion system 2 are arranged on grade slab 7. Drive system 1 includes floor installation plate 12, floor installation plate 12 is provided with drive system mounting seat 11, drive system mounting seat 11 is a unsplit bedplate, floor installation plate 12 is provided with T-slot, drive system mounting seat 11 is connected by T-slot screw is fixing with floor installation plate 12, drive system mounting seat 11 adopts unsplit bedplate, is so easy to assembling and the debugging of equipment.

As it is shown on figure 3, drive system 1 includes a drive motor 13, drive motor 13 is high-speed three phase asynchronous motor, adopts Frequency Converter Control to regulate its rotating speed. Drive motor 13 is connected with high speed rotor testpieces by transition drive mechanism, and drive motor 13 drives high speed rotor testpieces high speed rotating by transition drive mechanism. Transition drive mechanism includes the first diaphragm coupling 14, overload protective device 15, output shaft the 17, second diaphragm coupling 19.The motor shaft of drive motor 13 is connected with overload protective device 15 by the first diaphragm coupling 14, and overload protective device 15 is connected with output shaft 17, and output shaft 17 is connected with the rotating shaft 50 of rotor test part by the second diaphragm coupling 19.

First diaphragm coupling 14 is set between motor shaft and output shaft 17, the second diaphragm coupling 19 is set between the rotating shaft 50 of output shaft 17 and high speed rotor testpieces, make to be formed between axle and axle to flexibly connect. First diaphragm coupling the 14, second diaphragm coupling 19 is for adopting elastic diaphragm coupling. Elastic diaphragm coupling, while high speed rotating transmits moment of torsion, relies on the elastic metallic membranous disc deformation of specific profile to absorb misaligning and shock loading of two machines. Output shaft 17 is provided with torque sensor 18, owing to measuring the output moment of torsion of output shaft.

At high speed rotor testpieces 5 in the process of running up, fan blade come off produce imbalance and shock loading can trigger the multiple self-excited vibration of whole high speed rotor system, cause flexure and the internal stress of high speed rotor, equipment is made to produce the sharply increase of vibration and noise, accelerate the abrasion of the part such as bearing and axle envelope, the major accident that the drive system such as parts gross distortion, fracture are destroyed time serious, can be caused. Causing that drive system destructive insident occurs to prevent high speed rotor testpieces fan blade from coming off, drive system is provided with overload protective device 15 between motor shaft and output shaft 17. Overload protective device 15 selects torque limiter; torque limiter is a kind of mechanical overload protection device; it is installed on powerdriven driving side and by between driving side; transmission moment of torsion exceedes setting value and will disengage; so that powerdriven active and passive side separates, plant equipment is made to exempt from the damage transshipped and cause. The Overload torque of torque limiter can be adjusted as required, and overload moment can provide electrical signals to monitoring and control system 4, thus Control experiment device makes fast reaction.

In order to can make output shaft 17 fast braking when being in an emergency, this transition drive mechanism is additionally provided with the arrestment mechanism 16 for described output shaft is braked. As shown in Figure 4, this arrestment mechanism 16 includes three groups of brakes 161, so can increase braking moment. Brake 161 adopts electromagnetic brake, brake 161 directly with monitor and control system 4 is connected, by monitoring and control system 4 controls its action. Further respectively have spring bearing 162 in the both sides of brake 161, so can place output shaft and shake occurs in braking procedure.

When testing, rotor test part 5 is arranged on a test specimen installing plate 8, test specimen installing plate 8 is integral slab, plate upper surface designing T groove, rotor test part 5 is supported on test specimen installing plate 8 by testpieces mounting bracket 51,52, testing part mounting bracket 51,52 and be screwed on T-slot, two supports can move forward and backward in T-slot, adapts to the requirement of different engine mounting positions. Test specimen installing plate 8 is additionally provided with two armature spindle stop collars 53 being set in rotor test part rotating shaft, armature spindle stop collar 53 is used for supporting rotor test part, it is provided with rubber bumper in armature spindle stop collar 53, rubber bumper can fly to lose the deformation preset clearance produced for blade, can effectively prevent armature spindle 50 from producing large deformation, cause the damage of armature spindle 50.

Vacuum anti-explosion system 2 includes a vacuum chamber 21, it is provided with vacuum extractor in vacuum chamber 21, vacuum environment can be made to be formed in vacuum chamber 21 by vacuum extractor, so fan blade air blast frictional heating and power attenuation can be reduced when rotor test part 5 high speed rotating in vacuum chamber.Vacuum extractor includes a vacuum pump, and vacuum pump is inflated to vacuum chamber by an electric butterfly valve, installs an adjustment valve, be used for regulating air inflow between electric butterfly valve and vacuum chamber. Installing a vent valve on vacuum chamber pipeline, vent valve is opened, and extraneous air enters vacuum chamber and pressure balance in vacuum chamber.

As shown in Figure 5,6, vacuum chamber 21 is divided into nacelle 211 and lower nacelle 212 two parts, is provided with O RunddichtringO 217 between upper nacelle 211 and lower nacelle 212, seals and coordinate between upper nacelle 211 with lower nacelle 212. Upper nacelle 211 is provided with hanger 218, is provided with switching mechanism 219 between upper nacelle 211 and lower nacelle 212, and upper nacelle 211 is upper and lower closing mechanism with lower nacelle 212. Although adopting the external pressure that in this mechanism, nacelle 211 is born little, but lifting surface area be big, it is therefore desirable to being designed as reinforced structure. Using space for the ease of installation test part and increase, upper nacelle 211 is semicircular structure, and lower nacelle 212 is square structure.

As it is shown in fig. 7, the bottom surface of lower nacelle 212 is grade slab 7, grade slab 7 is provided with the bottom mounting bar 213 of a frame-like, and bottom mounting bar 213 is fixed on grade slab, is sealed by bottom sealing ring 214 and coordinate between bottom mounting bar 213 with grade slab 7. The side plate of lower nacelle 212 is fixing with bottom mounting bar 213 to be connected, and is provided with sealing ring between side plate and the bottom mounting bar 213 of lower nacelle 212. Side plate in lower nacelle has a machined surface 221, machined surface 221 is provided with screw hole, the bottom surface of lower nacelle side plate and bottom mounting bar side-fit, and sink in the mounting bar 213 of bottom, connected by trip bolt 220 between bottom surface and the bottom mounting bar of lower nacelle side plate, so can ensure the precision that lower cabin is installed. It addition, the external pressure that during evacuation, nacelle is born, bottom mounting bar 213 also functions to the effect supported. One annular O-ring seals (or planar seal ring) of Plane Installation on the mounting bar 213 of bottom, lower bilge facial planes is pressed on sealing ring, is around screwed bottom bottom on mounting bar. This sealing means is flat seal, thus can guarantee that the reliability of sealing.

When testing, rotor test part 5 is placed in this vacuum chamber 21, and output shaft 17 will extend in vacuum chamber 21 and be connected with rotor test part 5. In order to ensure the sealing of vacuum chamber 21, as shown in Figure 8, lower nacelle 212 is welded an adpting flange 222, adpting flange 222 outer surface is machined surface, should ensure that flatness, being arranged on adpting flange 222 by blind flange 215, end face O-ring seals 224 seals, and along the circumferential direction installs 16 trip bolt 225 supported flange lids and realizes sealing. The installing hole of output shaft 17 traverse blind flange 215, the axle sleeve 216 of copper is set inside and outside installing hole, axle sleeve 216, for the guiding of output shaft 17, arranges a high-temperature resistant seal ring 223 between two axle sleeves 216 and coordinates with the sealing of vacuum chamber 21 to realize output shaft 17. This mechanism is adopted to be easy in installation process, the adjustment of output shaft and rotor test part shaft concentricity, also allow for sealing simultaneously.

Be additionally provided with in vacuum chamber 21 one fly lose protective cover 22, when rotor test part is placed in vacuum chamber 21, the fan section of rotor test part be positioned at this fly lose protective cover 22, fly lose protective cover 22 for cushion and collect blade fly lose fragment. Such as Fig. 9, shown in 10, fly to lose protective cover 22 and include a circular protective cover shell 226, on the inner peripheral surface of protective cover shell 226, ecto-entad is sequentially provided with padded coaming 229, top stereotype 230 and buffering dividing plate 228, be additionally provided with side stereotype 231 in the both sides of protective cover 226, top stereotype 230, side stereotype 231 are fixed on cabin section gusset 227 each through screw.The space formed in circular protective cover shell 226 is divided into blade to fly to lose protective zone 232 and rotor revolution space 233 two parts by buffering dividing plate 228, rotor revolution space 233 is centrally located, blade flies to lose protective zone 232 and is positioned at rotor revolution space 233 periphery, and both separate by cushioning dividing plate 228. At the trial, on rotor test part, blade-carrying fan section is positioned at rotor revolution space 233. Top stereotype 230, side stereotype 231 lay respectively at the top and two sides that fly to lose protective zone 232.

Padded coaming 229 adopts high-density foam plate, for flying to lose the buffering of blade. Blade flies to lose to top stereotype 230 by the plastic deformation absorption energy of stereotype, and two side seating side stereotypes 231 are used for the buffering of side. The buffering dividing plate 228 of innermost layer adopts 5mm wrought aluminium plate, fly lose blade initially pass through buffering dividing plate 228 carry out first time buffering, then collide again on stereotype, it is achieved two-stage cushion. Fly off blade first penetrate buffering dividing plate 228 tentatively cushion, flying after preliminary buffering is lost blade and then collides with top stereotype 230, utilize lead to produce plastic deformation and absorb the energy flying to lose blade, the flying to lose blade or embed in lead or fall into the blade formed by top stereotype 230, buffering dividing plate 228 and side stereotype 231 of collision rift flies to lose in protective zone 232, so can avoid flying losing blade again to fall to return and the blade of other high-speed motion on rotor test part collides, thus ensureing that whole test can be properly functioning.

Lubricating and cooling system 3 is mainly used in providing lubricating oil to the bearing on high speed rotor testpieces and the bearing in drive system, and lubricating system is made up of main fuel tank, oil pump, cooler, filter, disastershutdown protection device etc. Oil pump feed mouth is after cooling system, filter, controlled by a total inlet valve, main oil supply pipe provides multichannel oil supply loop, mainly has testpieces lubricant passage way in vacuum chamber, drive motor lubricant passage way and equipment spring bearing lubricant passage way (including: testpieces two-way, the outer testpieces two-way of vacuum chamber, drive motor lubrication two-way, equipment spring bearing two-way in vacuum chamber). For the lubrication under vacuum environment in vacuum chamber, in order to ensure the reliable oil return of lubricating oil, degassing tower and gs-oil separator can be set in main fuel tank, run, together with the degassed vacuum pumping pump group of gear oil pump and oil, the dissolved gas contained in lubricating oil, it is to avoid it is overflowed under vacuum conditions affects lubricant effect. Cooler adopts concentrates fog lubrication cooling scheme, concentrates fog lubrication cooler, and fuel consumption is little, and lubrication, cooling fully, are installed simple, easy to maintenance. Concentrating fog lubrication cooler is a kind of oil foglubrication, cooling system, is made up of lubricating pump, nozzle, controller and lubrication adnexa. This lubrication device can supply accurate mist lubrication oil continuously, and lubricated body carries out oil foglubrication, cooling, regulates nozzle and can control spray form state, reaches spraying fine and closely woven, and uniformly, oiling is accurate in atomization. In order to prevent power-off, power-off, a top petrol tank can be set and be connected with the working connection of lubricating and cooling system.

Monitoring and control system 4 are divided into control portion unit and detection unit two parts. Control unit controls for the start and stop order of rotor test part, drive system, vacuum anti-explosion system and lubricating and cooling system, running status relevant parameter, regulates and interlock logic protection. System start-up order: rotor test part 5 is installed centering and completed, confirms that vacuum chamber 21 is closed, first starts vacuum extractor, evacuation restarts lubricating and cooling system after terminating, and finally starts drive system, and stopping order is according to starting reverse order operation.Vacuum chamber unlocking condition is that in vacuum chamber, pressure, equal to environment atmospheric pressure, can be opened. The control logic of this control unit is set to interlock logic control, it is ensured that system coordination and safe operation. Being realized by contact position sensor as vacuum cabin door Guan Bi checks, once hatch door is not reliably locked, test stops immediately, and locks all control knobs of hardware-software, simultaneously display " hatch door is opened " prompting over the display, until hatch door locking. It addition, the unlatching of hatch door is carried out chain control with main shaft by speed probe and vacuum pressure sensor, only in the speed of mainshaft is lower than the rotating speed safety value set, cabin, pressure is higher than the pressure security value set, and hatch door just can be opened.

Control unit adopts distribution-central combination control mode, and namely slave computer and the combined mode of host computer, directly can be configured the control parameter of each system component, revise on host computer, works again through the slave computer PLC each system component of control. It is available that control unit should be provided with manual/auto two kinds of operator schemes. Whole pilot system control part concentrates on control in-house operation, control and measurement, TT&C system in control room includes upper and lower machine, Non-follow control cabinet, controls power line, holding wire, data acquisition display processing system, instrument cabinet, monitoring display device, printer etc., and explosion proof window is set, measure to facilitate operator, at home, assay device is carried out real-time data monitoring, operate and test.

Monitoring means shows for pilot system running state parameter monitors with warning etc., concentrates on control station and controls to run and monitoring. Mainly include drive system output speed and moment of torsion, output shaft vibration displacement, testpieces operating condition real-time video, vacuum chamber pressure, lubricating oil supplying temperature, flow and pressure, motor operating parameter (voltage, electric current, frequency, efficiency etc.), vacuum chamber open and-shut mode is monitored. Monitoring means can show each monitoring parameter, initialization system operational parameter control (such as climb curve) in real time, has fault alarm function, sets fault alarm value, has the correlation functions such as the storage of Monitoring Data, playback, output. Duty passes through monitor and each Sensor monitoring. Trystate in monitor or acquisition explosion-proof vacuum cabin, is shown on monitor screen; Each sensor acquisition to data tolerance all can be set, once beyond tolerance, system automatically starts buzzer and sends alarm, and makes corresponding display on software.

This high speed rotor blade is adopted to fly off assay device when testing, first rotor test part is placed in the testpieces mounting bracket 52 of vacuum chamber 21, and make blade-carrying fan section on rotor test part 5 be positioned at the rotor revolution space 233 flying to lose protective cover, the rotating shaft making rotor test part 5 is connected with drive system, and is arranged to the sensor of detection rotor test part rotary state in vacuum chamber. Sensor can arrange multiple, as being arranged below laser displacement sensor at the rotating shaft of rotor test part and output shaft 17, is provided with vibrating sensor in testpieces mounting bracket 51,52.

After high speed rotor testpieces installs, close vacuum chamber 21, start vacuum extractor and vacuum chamber 21 is carried out evacuation process, according to vacuum level requirements: less than 1000Pa, traffic requirement: S > 440L/min, after this vacuum chamber seals, air leakage is few, and flow nargin takes 1.2 times, then actual selection flow is: 528L/s.Then start lubricating and cooling system and provide lubricating oil to drive system and testpieces mounting bracket, make bearing be in lubrication, the state of cooling. Then start the drive motor 13 of drive system, drive high speed rotor testpieces 5 high speed rotating in vacuum chamber 21; When high speed rotor testpieces rotary speed reaches a threshold value (>=20000r/min), defective blade on high speed rotor testpieces will fly off, wear out under the effect of inertia and centrifugal force buffering dividing plate enter into blade fly lose protective zone, and rest on blade fly lose protective zone; Fly off blade first penetrate buffering dividing plate 228 tentatively cushion, flying after preliminary buffering is lost blade and then collides with top stereotype 230, utilize lead to produce plastic deformation and absorb the energy flying to lose blade, the flying to lose blade or embed in lead or fall into the blade formed by top stereotype 230, buffering dividing plate 228 and side stereotype 231 of collision rift flies to lose in protective zone 232, so can avoid flying losing blade again to fall to return and the blade of other high-speed motion on high speed rotor testpieces collides, thus ensureing that whole test can be properly functioning.

When rotor test part is in the process of running up, fan blade come off produce imbalance and shock loading, trigger the multiple self-excited vibration of whole rotor system, cause flexure and the internal stress of high speed rotor testpieces, equipment is made to produce the sharply increase of vibration and noise, armature spindle and output shaft run-out simultaneously all can become big, the magnitude of vibrations of rotor test part so can be measured by vibrating sensor, the deflection of axle is just can detect that by laser displacement sensor, and feed back to monitoring means, monitoring and control system 5 will start alarming logic interlocking, the drive motor making drive system is out of service, after whole rotor test part running down stops operating, close lubricating and cooling system, the vent valve opening vacuum anti-explosion system balances to pressure in cabin with atmospheric pressure, thus can open vacuum chamber and check rotor test part.

This high speed rotor blade flies off assay device and test method by drive system rotor driven testpieces high speed rotating, the test that the fan blade on rotor test part flies off is simulated in vacuum chamber, flying in vacuum chamber is lost in protective cover and is provided with buffering dividing plate, blade on high speed rotor testpieces can rest on blade and fly to lose in protective zone by blade after flying off, the blade so flown off would not collide with the rotor test part rotated, so can be normally carried out by guarantee test, also can effectively ensure that the safety of testing crew and testing equipment simultaneously. Simultaneously by monitoring and the operation of whole device can be controlled and detect by control system, thus can effectively ensure that the operation that this assay device is safe and reliable, rotor rotational characteristic after leaf abscission is carried out test checking, to guarantee the rotation safety of engine rotor, provide the technological means of important excess syndrome foundation for electromotor design typification. So, this utility model effectively overcomes various shortcoming of the prior art and has high industrial utilization.

Above-described embodiment only illustrative principle of the present utility model and effect thereof, not for restriction this utility model. Above-described embodiment all under spirit of the present utility model and category, can be modified or change by any those skilled in the art. Therefore, art has all equivalence modification or changes that usually intellectual completes under the spirit disclosed without departing from this utility model with technological thought such as, must be contained by claim of the present utility model.

Claims (8)

1. a high speed rotor blade flies off assay device, it is characterised in that comprising:

Drive system, described drive system is used for driving rotor test part high speed rotating;

Vacuum anti-explosion system, described vacuum anti-explosion system includes a vacuum chamber, being provided with vacuum extractor and testpieces mounting bracket in described vacuum chamber, described testpieces mounting bracket is for supporting rotor test part at the trial, and described vacuum extractor is for carrying out evacuation process to described vacuum chamber;

Fly to lose protective cover, the described mistake protective cover that flies is positioned at described vacuum chamber, described fly to lose in protective cover form a rotor revolution space and a blade flies to lose protective zone, described rotor revolution space and described blade fly to be separated by buffering dividing plate between mistake protective zone, during test, the fan section of rotor test part is positioned at described rotor revolution space;

Lubricating and cooling system, described lubricating and cooling system provides lubricating oil for the bearing on the bearing and testpieces mounting bracket of described drive system;

Monitoring and control system, described drive system, vacuum anti-explosion system, lubricating and cooling system are all connected with described monitoring and control system, and described monitoring and control system are for being controlled described drive system, vacuum anti-explosion system, lubricating and cooling system, monitor.

2. high speed rotor blade according to claim 1 flies off assay device, it is characterized in that: described drive system includes drive motor and transition drive mechanism, described transition drive mechanism includes the first diaphragm coupling, output shaft, the second diaphragm coupling, one end of described output shaft is connected with the motor shaft of described drive motor by described first diaphragm coupling, during test, the other end of described output shaft is connected by the rotating shaft of described second diaphragm coupling with described rotor test part.

3. high speed rotor blade according to claim 2 flies off assay device, it is characterised in that: described output shaft be connected with laser displacement sensor, described testpieces mounting bracket is provided with vibrating sensor.

4. high speed rotor blade according to claim 2 flies off assay device, it is characterized in that: described vacuum chamber includes nacelle and lower nacelle two parts, described upper nacelle is semicircular structure, and described lower nacelle is square structure, and described upper nacelle seals with described lower nacelle and coordinates.

5. high speed rotor blade according to claim 4 flies off assay device, it is characterized in that: described vacuum chamber seals with described output shaft and coordinates, described lower nacelle is provided with an adpting flange, described adpting flange is provided with blind flange, the installing hole of the described output shaft described blind flange of traverse, the rear and front end of described installing hole is provided with axle sleeve, is provided with sealing ring between two axle sleeves, and described output shaft is coordinated with the sealing of described installing hole by described sealing ring.

6. high speed rotor blade according to claim 5 flies off assay device, it is characterized in that: the bottom of described vacuum chamber is grade slab, described grade slab is provided with the bottom mounting bar of a frame-like, described bottom mounting bar is fixed on described grade slab, described bottom mounting bar seals with described grade slab and coordinates, the side plate of described lower nacelle is fixing with described bottom mounting bar to be connected, and is provided with sealing ring between side plate and the described bottom mounting bar of described lower nacelle.

7. high speed rotor blade according to claim 1 flies off assay device, it is characterized in that: described in fly to lose protective cover and include a circular protective cover shell, described buffering dividing plate is that circle is embedded in described protective cover shell, described buffering dividing plate surrounds described rotor revolution space, forming described blade between described protective cover shell and described buffering dividing plate to fly to lose protective zone, described blade flies to lose the top of protective zone and sidewall is provided with lead.

8. high speed rotor blade according to claim 1 flies off assay device, it is characterised in that: described lubricating and cooling system includes, by main fuel tank, oil pump, cooler, filter, being provided with degassing tower and gs-oil separator in described main fuel tank.