CN108151421A - A kind of aviation coolant cold source system - Google Patents
A kind of aviation coolant cold source system Download PDFInfo
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- CN108151421A CN108151421A CN201810109435.8A CN201810109435A CN108151421A CN 108151421 A CN108151421 A CN 108151421A CN 201810109435 A CN201810109435 A CN 201810109435A CN 108151421 A CN108151421 A CN 108151421A
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- pump group
- pole ring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
- F25D17/00—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces
- F25D17/02—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces for circulating liquids, e.g. brine
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of aviation coolant cold source system, including head and the tail supercharging liquid storage component connected in sequence, pump group, heat load, radiator and filter assemblies；Supercharging liquid storage component, pump group, heat load, radiator are sequentially connected by pipeline with filter assemblies and form the circulatory system；It is disposed with safety valve, second pressure sensor and temperature sensor on pipeline between pump group and heat load along the direction of heat load from pump group；Outlet pipe is connected on the liquid outlet of the safety valve, reservoir is provided with below the outlet of outlet pipe；Temperature and pressure with the coolant for ensuring to enter heat load in allowed limits, so as to ensure liquid cooling system trouble-free operation, increases the service life of parts for needing to cool down.
Description
Technical field
The invention belongs to aviation cooling technology fields, and in particular to a kind of aviation coolant cold source system.
Background technology
Since the coolant of aviation coolant cold source system has corrosivity (such as 65# coolants), and medium mostly
Unlubricated performance, when coolant is after supercharging liquid storage component supercharging, then is extracted out by the pump housing, since the output power of the pump housing could not
Adjustment in time, so the pressure of the coolant often flowed out from pump housing outlet is more than the pressure that the parts to cool down is needed to bear,
It is deformed so as to cause parts, influences the normal use of each parts.
Invention content
It is an object of the invention to the output power for the pump housing existing for above-mentioned aviation coolant cold source system could not and
When the adjustment the problem of pressure of the output liquid of pump is caused to be more than the pressure that the parts that cool down of needs are born, present invention offer one
Kind aviation coolant cold source system.
The technical solution adopted by the present invention is as follows：
A kind of aviation coolant cold source system including head and the tail supercharging liquid storage component connected in sequence, pump group, heat load, dissipates
Thermal and filter assemblies；Supercharging liquid storage component, pump group, heat load, radiator are sequentially connected with filter assemblies by pipeline
And form the circulatory system；
Safety valve, second are disposed with along the direction of heat load from pump group on pipeline between pump group and heat load
Pressure sensor and temperature sensor；
Outlet pipe is connected on the liquid outlet of the safety valve, liquid storage is provided with below the outlet of outlet pipe
Slot.
It further limits, the supercharging liquid storage component includes liquid reserve tank, is set gradually from one end to the other side in liquid reserve tank
There are displacement sensor, pressurized spring and piston component.
It further limits, fluid injection valve, first pressure sensor and level sensing is provided on the liquid storage box body
Device.
It further limits, the filter assemblies include filter, live for cutting off the bypath valve of filter and oil return
Door；
It further limits, the pump group is connected with controller.
It further limits, the pump group joins driving motor pump group using magnetic, and magnetic connection driving motor pump group includes being sequentially connected with
Pump group part, magnetic connection driving structure and electric machine assembly；
The magnetic connection driving structure includes magnetic connection drive component and the screen for preventing the magnetic field diffusion of magnetic connection drive component
Component is covered, the magnetic connection drive component includes driven magnetic pole ring assemblies and active pole ring component, the driven magnetic pole ring assemblies
It is fixedly connected with the pump group part, the active pole ring component is fixedly connected with the electric machine assembly；
Be provided with non-magnetic isolation cover between driven magnetic pole ring assemblies and active pole ring component, driven magnetic pole ring assemblies and
Active pole ring component is coaxially disposed.
It further limits, the driven magnetic pole ring assemblies include the first hollow cylinder, and active pole ring component includes second
Hollow cylinder, first hollow cylinder one end end face upper edge its circumferencial direction offer first annular mounting groove, first annular installation
The axis of slot is overlapped with the first hollow cylinder axis；Second hollow cylinder one end end face upper edge its circumferencial direction offers the second ring
Shape mounting groove, the axis of the second annular mounting groove are overlapped with the axis of the second hollow cylinder；
Multiple magnets are both provided in first annular mounting groove and in the second annular mounting groove along respective circumferencial direction, often
Along the first hollow cylinder, (axial direction is set the magnetic pole of one magnet, and arbitrary neighborhood magnet is towards the one of non-magnetic isolation cover
The magnetic pole at end is opposite；Each described magnet is shirt cobalt magnet.
It further limits, the shield assembly includes the first shielding group for shielding the driven magnetic pole ring assemblies magnetic field
Part and the secondary shielding component for shielding the active pole ring component magnetic field；
First shield assembly includes third shading ring and secondary shielding cylinder, and it is empty that the secondary shielding component includes third
Heart cylinder, the third shading ring be set to the first hollow cylinder deviate from the driven magnetic pole ring assemblies one end, described second
Shielding cylinder is sheathed on outside the non-magnetic isolation cover, and one end end face of the third hollow cylinder offers annular groove, and described
Two hollow cylinders are set in annular groove；The notch direction of second annular mounting groove and the notch direction of annular groove are directed toward same
One direction.
It further limits, the pump group part includes pump case, the pump shaft and pump gear that are set in pump case, outside pump shaft
Rotor assembly is arranged with, compensation bushing is arranged with outside rotor assembly；The pump shaft uses ceramic bearing；The pump gear is using resistance to
Corrosion hard alloy is made.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
1. the present invention can carry out the coolant that pump group comes out the adjusting of pressure so that pressure is less than the maximum of heat load
Pressure is born, ensures that heat load can work normally, and the temperature and pressure that postcooling liquid is adjusted through excess pressure can be monitored, really
Guarantor enters the pressure and temperature of heat load in allowed limits；The liquid come out from the liquid outlet of safety valve enters liquid storage
In slot, avoid pollution environment and cause the waste of coolant.
2. the distance of pressurized spring movement can be accurately reacted, so as to react the pressure that coolant in liquid reserve tank is increased
Power is conducive to that the output power of pump group is adjusted so that the pressure for the coolant that pump group comes out is as possible in the range of permission
It is interior, the opening of safe safety valve is reduced, so as to reduce the discharge of coolant, the waste of coolant is reduced, reaches cost-effective
Effect.
3. fluid injection valve is for supplementing new coolant, the body generated for compensation system coolant due to temperature change
Product variation.
4. filter assemblies avoid entrance being caused to block up pump group for filtering the fine particle that coolant is taken out of from heat load
Plug so that coolant can not smooth circulation, bypath valve be used for by filter cut out coolant circulation system and cause cooling
Fluid circulation can recycle, for meeting an urgent need.
5. controller corrects phase sequence and guarantor for detecting the phase sequence and overcurrent of motor and signal connector into pump group
Phase shortage circuit is protected, and will ensure that the motor of pump group and signal connector are not influenced by electric current.
6. pump group replaces traditional rigid connection structure using magnetic connection driving structure, traditional dynamic sealing is converted into quiet close
Envelope, and rigid connection is converted into contactless flexible connection, so as to avoid the hair of " run, drip, leak " phenomenon of the pump housing
It is raw；Driven magnetic pole ring assemblies and the coaxial arrangement of active pole ring component, can overcome pump group part by unilateral larger axial magnetic
The imbalance of pump group part caused by push-pull effort, so as to slow down the abrasion of the pump shaft of pump group part.
7. driven magnetic pole ring assemblies and active pole ring component are circumferentially distributed by multiple magnetic poles, and the two of arbitrary neighborhood
The magnetic pole of a magnet is on the contrary, enable to the function between active magnetic pole component and driven magnetic pole component that must can be used for as far as possible
Coolant is driven, the loss of function is reduced, meets the requirement of the functional density of driving of the pump group to liquid.
8. the first shield assembly and secondary shielding component are respectively used to prevent driven magnetic pole ring assemblies and active pole ring group
The magnetic field of part is leaked, and is met in aviation to the requirement of Electro Magnetic Compatibility.
9. ceramic wear-resisting performance and corrosion resistance and good, can extend the physical life of pump shaft, corrosion-resisting hard-alloy is resistance to
Corrosive nature is good, can extend the service life of pump gear；Compensation bushing is used to fill up the rotor caused by temperature change
Gap between component and pump case, so as to which coolant be avoided to reveal.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the schematic diagram of the present invention；
Fig. 2 is the schematic diagram for being pressurized liquid storage component；
Fig. 3 is the structure diagram of filter assemblies；
Fig. 4 is the operation principle schematic diagram of controller；
Fig. 5 is the structure diagram of magnetic connection driving motor pump group；
Fig. 6 is the schematic diagram of magnetic connection driving structure；
Fig. 7 is the structure diagram of driven magnetic pole ring assemblies；
Fig. 8 is the view in A directions in Fig. 7；
Fig. 9 is the structure diagram of active pole ring component；
Figure 10 is the view in B directions in Fig. 9；
Figure 11 is pump group
Wherein：1- is pressurized liquid storage component 101- liquid reserve tanks；102- piston components；103- pressurized springs；104- displacement sensings
Device；105- liquid level sensors；106- first pressure sensors；107- fluid injection valve；2- heat loads；3- radiators；4- pump groups；
401- pump group parts；4011- pump shafts；4012- pump cases；4013- rotor assembly；4014- compensates bushing；402- magnetic connection driving knot
Structure；The driven magnetic pole ring assemblies of 4021-；The first hollow cylinders of 40211-；40212- magnets；40213- third shading rings；40214-
First annular mounting groove；40215- secondary shielding cylinders；4022- active pole ring components；The second hollow cylinders of 40221-；40223-
Third hollow cylinder；The second annular mounting grooves of 40224-；40225- annular grooves；The non-magnetic isolation covers of 4023-；403- motor groups
Part；5- safety valves；51- reservoirs；6- second pressure sensors；7- temperature sensors；8- filter assemblies；801- by-passing valves
Door；802- filters；803- oil return valve；9- controllers.
Specific embodiment
All features or disclosed all methods disclosed in this specification or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.It elaborates below in conjunction with the accompanying drawings to the present invention.
Embodiment one
The technical solution of the present embodiment is：A kind of aviation coolant cold source system, including head and the tail supercharging storage connected in sequence
Liquid component 1, pump group 4, heat load 2, radiator 3 and filter assemblies 8；It is pressurized liquid storage component 1, pump group 4, heat load 2, heat dissipation dress
3 are put sequentially to connect by pipeline with filter assemblies 8 and form the circulatory system；
On pipeline between pump group 4 and heat load 2 safety valve is disposed with along the direction of heat load 2 from pump group 4
5th, second pressure sensor 6 and temperature sensor 7；
Outlet pipe is connected on the liquid outlet of the safety valve 5, liquid storage is provided with below the outlet of outlet pipe
Slot 51.
As shown in Figure 1, the coolant being stored in supercharging liquid storage component 1 is extracted out by pump group 4 into being recycled in pipeline,
When the pressure that pump group 4 exports is higher than setting pressure, safety valve 5 starts, and the coolant of a part is discharged into reservoir 51,
So that pressure reduction in pipeline is in the range of allowing, for being cooled down to heat load 2, by the cold of heat load 2
But liquid is radiated by radiator 3, is finally filtered by filter assemblies 8, is flowed back to supercharging liquid storage component 1, is completed coolant
One cycle, second pressure sensor is for detecting the pressure of coolant after safety valve 5, for judging safe work
Whether door 5 works normally, and temperature sensor 7 is used to detect the temperature of coolant, and the temperature for avoiding enter into heat load is excessively high, so as to
So that cooling effect is deteriorated so that the heat build-up of heat load 2 leads to 2 overtemperature of heat load, it has to be stopped；Reservoir 51
For receiving the coolant come out from safety valve 5, avoiding pollution environment and causing the waste of coolant.
Embodiment two
On the basis of embodiment one, the technical solution of the present embodiment is：The supercharging liquid storage component 1 includes liquid reserve tank
101, it is disposed with displacement sensor 104, pressurized spring 103 and piston component from one end to the other side in liquid reserve tank 101
102。
As shown in Fig. 2, displacement sensor 104 measures the distance that pressurized spring 103 moves, so as to react in liquid reserve tank 101
The increased pressure of coolant number, for increase into pump group 4 coolant pressure so that pump group 4 export cooling
The pressure of liquid is unlikely to too low.
Embodiment three
On the basis of embodiment one, the technical solution of the present embodiment is is provided with fluid injection on 101 babinet of liquid reserve tank
Valve 107, first pressure sensor 106 and liquid level sensor 105.
As shown in Fig. 2, first pressure sensor 106 is used to measure the pressure of coolant in liquid reserve tank 101, fluid injection valve
107, for supplementing the amount of the coolant in liquid reserve tank 101, avoid the variation of coolant volume caused by temperature change, liquid level
Sensor 105 reacts the variation of coolant volume in liquid reserve tank 101.
Example IV
On the basis of embodiment one or two or three, the technical solution of the present embodiment is：The filter assemblies 8 include filtering
Device 802, for cutting off the bypath valve 801 of filter 802 and oil return valve 803.
As shown in figure 3, filter assemblies 8 are avoided for filtering the fine particle that coolant is taken out of from heat load to pump group 4
Cause blocked inlet so that coolant can not smooth circulation, bypath valve 801 followed for filter 802 to be cut out coolant
Loop system and coolant circulation system is recycled, for meeting an urgent need.
Embodiment five
On the basis of example IV, the technical solution of the present embodiment is：The pump group 4 is connected with controller 9.
As shown in Figure 1, controller 9 is corrected for detecting the phase sequence and overcurrent of motor and signal connector into pump group 4
Phase sequence and protection phase shortage circuit, and will ensure that the motor of pump group 4 and signal connector are not influenced by electric current；As shown in figure 4,
The fundamental diagram of device 9 in order to control.
Embodiment six
On the basis of embodiment one, the pump group 4 joins driving motor pump group using magnetic, and magnetic connection driving motor pump group includes
Pump group part 401 connected in sequence, magnetic connection driving structure 402 and electric machine assembly 403；
The magnetic connection driving structure includes magnetic connection drive component and the screen for preventing the magnetic field diffusion of magnetic connection drive component
Component is covered, the magnetic connection drive component includes driven magnetic pole ring assemblies 4021 and active pole ring component 4022, the driven magnetic
Polar ring component 4021 is fixedly connected with the pump group part 401, and the active pole ring component 4022 is solid with the electric machine assembly 403
Fixed connection；
Non-magnetic isolation cover 4023 is provided between driven magnetic pole ring assemblies 4021 and active pole ring component 4022, it is driven
Magnetic pole ring assemblies 4021 and active pole ring component 4022 are coaxially disposed.
As shown in Figure 5 and Figure 6, active pole ring component 4022 rotates under the drive of electric machine assembly 403, active pole ring
Component 4022 drives driven magnetic pole ring assemblies 4021 to rotate, so that the impeller rotation in pump group part 401, thus by coolant
Traditional dynamic sealing instead of traditional rigid connection structure, is converted into static seal, and rigid connection is converted by extraction and supercharging
For contactless flexible connection, so as to avoid the generation of " run, drip, leak " phenomenon of the pump housing；Driven magnetic pole ring assemblies 4021
It is coaxially disposed with active pole ring component 4022, pump group part 401 can be overcome to be caused by unilateral larger axial magnetic push-pull effort
Pump group part 401 imbalance, so as to slow down the abrasion of the pump shaft of pump group part 401.
Embodiment seven
On the basis of embodiment six, the technical solution of the present embodiment is：The driven magnetic pole ring assemblies 4021 include the
One hollow cylinder 40211, active pole ring component 4022 include the second hollow cylinder 40221,40211 one end of the first hollow cylinder
Upper edge its circumferencial direction in end face offers first annular mounting groove 40214, the axis of first annular mounting groove 40214 and the first sky
40211 axis of heart cylinder overlaps；Second hollow cylinder, 40221 one end end face its circumferencial direction of upper edge offers the second annular installation
Slot 40224, the axis of the second annular mounting groove 40224 are overlapped with the axis of the second hollow cylinder 40221；
It is both provided in first annular mounting groove 40214 and in the second annular mounting groove 40224 along respective circumferencial direction
Multiple magnets 40212, the magnetic pole of each magnet 40212 are set along the axial direction of the first hollow cylinder 40211, arbitrary neighborhood
The magnetic pole of magnet 40212 towards one end of non-magnetic isolation cover 4023 is opposite；Each described magnet 40212 is shirt cobalt magnet.
As shown in Fig. 7-Figure 10, the first hollow cylinder 40211 and the second hollow cylinder 40221 are by low-carbon steel material system
Into, in stationary state, the N poles of the magnet of active pole ring component 4022 and the S of the magnet of driven magnetic pole ring assemblies 4021
Pole attracts each other and is in line, when active pole ring component 4022 rotates under the drive of external force, driven magnetic pole ring assemblies
4021, due to the effect of frictional force and transmission part resistance, still in stationary state, cause active pole ring component 4022 opposite
Driven magnetic pole ring assemblies 4021 deviate certain angle, and due to the presence of this angle, the N of active pole ring component 4022 is extremely right
The S poles of driven magnetic pole ring assemblies 4021 are there are one pulling function, while the N of active pole ring component 4022 is extremely to driven pole ring
There are one impetuses for the previous N poles of component 4021, make trend of the driven magnetic pole ring assemblies 4021 there are one and then rotation；
When the N poles of active pole ring component 4022 be located just at driven magnetic pole ring assemblies 4021 adjacent two magnet it
Between when, the push-pull effort of generation reaches maximum, non-magnetic in transmission process so as to which driven magnetic pole ring assemblies 4021 be driven to rotate
Isolation cover 4023 separates driven magnetic pole ring assemblies 4021 and active pole ring component 4022, and magnetic field line is across non-magnetic isolation
The power of active pole ring component 4022 and movement are transmitted to driven magnetic pole ring assemblies 4021 by cover 4023, it is achieved thereby that without connecing
Tactile sealing transmission；
The structure of such kind of drive is simple, enabling stable transmission, the stabilization for being conducive to driving effectively carry out, often
One magnet is shirt cobalt magnet, since shirt cobalt magnet is one kind in rare-earth permanent magnet, has light weight, small, high
The advantages of magnetic energy product and big torque, critical operating temperatures are high, can work over a wide temperature range, so as to adapt to aeronautical environment
Temperature change, extend magnetic connection driving structure service life.
Embodiment eight
On the basis of embodiment seven, the technical solution of the present embodiment is：The shield assembly includes described for shielding
First shield assembly in driven 4021 magnetic field of magnetic pole ring assemblies and for shielding 4022 magnetic field of active pole ring component
Secondary shielding component；
First shield assembly includes third shading ring 40213 and secondary shielding cylinder 40215, the secondary shielding component
Including third hollow cylinder 40223, the third shading ring 40213 is set to the first hollow cylinder 40211 away from described driven
One end of magnetic pole ring assemblies 4021, the secondary shielding cylinder 40215 are sheathed on outside the non-magnetic isolation cover 4023, the third
One end end face of hollow cylinder 40223 offers annular groove 40225, and second hollow cylinder 40221 is set to annular groove
In 40225；Same side is directed toward in the notch direction of second annular mounting groove 40224 and the notch direction of annular groove 40225
To.
As shown in Fig. 7-Figure 10, the first shield assembly is used to preventing the magnetic field of driven magnetic pole ring assemblies 4021 to external diffusion,
Secondary shielding component is used to prevent 4022 magnetic field of active pole ring component to external diffusion；The third shading ring 40213 is used to hinder
Only driven magnetic pole ring assemblies 4021 are away from the diffusion in the magnetic field of one end of non-magnetic isolation cover 4023, the secondary shielding cylinder
40215 for preventing the diffusion in the magnetic field of driven pole ring group circumferential direction, and third hollow cylinder 40223 is used to prevent active pole ring
Component 4022 ensures equipment away from the circumferential magnetic field diffusion in one end of non-magnetic isolation cover 4023 and active pole ring component 4022
Normal operation prolongs the service life.
Embodiment nine
On the basis of embodiment six, the technical solution of the present embodiment is：The pump group part 401 include pump case 4012,
Pump shaft 4011 and the pump gear being set in pump case 4012, pump shaft 4011 are arranged with rotor assembly 4013, rotor assembly outside
Compensation bushing 4014 is arranged with outside 4013；The pump shaft 4011 uses ceramic bearing；The pump gear is closed using corrosion-resistant hard
Gold is made.
As shown in figure 11, ceramic wear-resisting performance and corrosion resistance and good can extend the physical life of pump shaft 4011, corrosion resistant
Hard alloy corrosion resistance and good is lost, the service life of pump gear can be extended；Compensation bushing 4014 is used to fill up due to temperature
Gap caused by variation between rotor assembly 4013 and pump case 4012, so as to which coolant be avoided to reveal.
Claims (9)
1. a kind of aviation coolant cold source system, which is characterized in that including head and the tail supercharging liquid storage component (1) connected in sequence, pump
Group (4), heat load (2), radiator (3) and filter assemblies (8)；It is pressurized liquid storage component (1), pump group (4), heat load (2), dissipates
Thermal (3) is sequentially connected by pipeline with filter assemblies (8) and forms the circulatory system；
On pipeline between pump group (4) and heat load (2) safety is disposed with along the direction of heat load (2) from pump group (4)
Valve (5), second pressure sensor (6) and temperature sensor (7)；
Outlet pipe is connected on the liquid outlet of the safety valve (5), reservoir is provided with below the outlet of outlet pipe
(51)。
A kind of 2. aviation coolant cold source system according to claim 1, which is characterized in that the supercharging liquid storage component
(1) including liquid reserve tank (101), liquid reserve tank (101) is interior to be disposed with displacement sensor (104), supercharging from one end to the other side
Spring (103) and piston component (102).
A kind of 3. aviation coolant cold source system according to claim 2, which is characterized in that liquid reserve tank (101) case
Fluid injection valve (107), first pressure sensor (106) and liquid level sensor (105) are provided on body.
4. according to a kind of aviation coolant cold source system of claim 1-3 any one of them, which is characterized in that the filtering group
Part (8) including filter (802), for cutting off the bypath valve of filter (802) (801) and oil return valve (803).
5. a kind of aviation coolant cold source system according to claim 4, which is characterized in that the pump group (4) is connected with
Controller (9).
6. a kind of aviation coolant cold source system according to claim 1, which is characterized in that the pump group (4) is using magnetic
Join driving motor pump group, magnetic connection driving motor pump group include pump group part connected in sequence (401), magnetic connection driving structure (402) with
And electric machine assembly (403)；
The magnetic connection driving structure includes magnetic connection drive component and the shielding group for preventing the magnetic field diffusion of magnetic connection drive component
Part, the magnetic connection drive component include driven magnetic pole ring assemblies (4021) and active pole ring component (4022), the driven magnetic
Polar ring component (4021) is fixedly connected with the pump group part (401), the active pole ring component (4022) and the motor group
Part (403) is fixedly connected；
Non-magnetic isolation cover (4023) is provided between driven magnetic pole ring assemblies (4021) and active pole ring component (4022), from
Dynamic magnetic pole ring assemblies (4021) and active pole ring component (4022) coaxial arrangement.
A kind of 7. aviation coolant cold source system according to claim 6, which is characterized in that the driven magnetic pole ring assemblies
(4021) including the first hollow cylinder (40211), active pole ring component (4022) includes the second hollow cylinder (40221), the
Its circumferencial direction of one hollow cylinder (40211) one end end face upper edge offers first annular mounting groove (40214), first annular peace
The axis of tankage (40214) is overlapped with the first hollow cylinder (40211) axis；On second hollow cylinder (40221) one end end face
The second annular mounting groove (40224) is offered along its circumferencial direction, the axis of the second annular mounting groove (40224) and second hollow
The axis of cylinder (40221) overlaps；
It is both provided in first annular mounting groove (40214) and in the second annular mounting groove (40224) along respective circumferencial direction
Multiple magnets (40212), the magnetic pole of each magnet (40212) set along the axial direction of the first hollow cylinder (40211), appoint
The magnetic pole of adjacent magnets of anticipating (40212) towards one end of non-magnetic isolation cover (4023) is opposite；Each described magnet (40212)
For shirt cobalt magnet.
8. a kind of aviation coolant cold source system according to claim 7, which is characterized in that the shield assembly includes using
In the first shield assembly for shielding driven magnetic pole ring assemblies (4021) magnetic field and for shielding the active pole ring group
The secondary shielding component in part (4022) magnetic field；
First shield assembly includes third shading ring (40213) and secondary shielding cylinder (40215), the secondary shielding component
Including third hollow cylinder (40223), the third shading ring (40213) is set to the first hollow cylinder (40211) away from institute
One end of driven magnetic pole ring assemblies (4021) is stated, the secondary shielding cylinder (40215) is sheathed on the non-magnetic isolation cover
(4023) outside, one end end face of the third hollow cylinder (40223) offers annular groove (40225), second open circles
Cylinder (40221) is set in annular groove (40225)；The notch direction of second annular mounting groove (40224) and annular groove
(40225) it is directed toward same direction in notch direction.
A kind of 9. aviation coolant cold source system according to claim 6, which is characterized in that pump group part (401) packet
The pump shaft (4011) and pump gear for include pump case (4012), being set in pump case (4012), pump shaft (4011) are arranged with outside
Rotor assembly (4013), rotor assembly (4013) are arranged with compensation bushing (4014) outside；The pump shaft (4011) is using ceramic shaft
It holds；The pump gear is made of corrosion-resisting hard-alloy.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810109435.8A CN108151421A (en) | 2018-02-05 | 2018-02-05 | A kind of aviation coolant cold source system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810109435.8A CN108151421A (en) | 2018-02-05 | 2018-02-05 | A kind of aviation coolant cold source system |
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2018
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|---|---|---|---|---|
| US5525039A (en) * | 1993-07-21 | 1996-06-11 | Roy E. Roth Company | Hermetically sealed magnetic drive pump |
| DE10161368A1 (en) * | 2001-12-14 | 2003-07-10 | Messer Griesheim Gmbh | Cryogenic cooling of aerosol product mixtures, especially for filling pharmaceutical dosed aerosols, comprises controlled thermal contact with vaporized cooling gas in heat exchanger |
| JP3124651U (en) * | 2006-06-13 | 2006-08-24 | 株式会社島津製作所 | Liquid cooling system for aircraft equipment |
| CN202310420U (en) * | 2011-09-29 | 2012-07-04 | 湖北航达科技有限公司 | Integrated liquid feed device |
| CN207907572U (en) * | 2018-02-05 | 2018-09-25 | 成都弗格森液压机电有限公司 | A kind of aviation coolant liquid cold source system |
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