CN206727895U - A kind of inverter - Google Patents
A kind of inverter Download PDFInfo
- Publication number
- CN206727895U CN206727895U CN201720323528.1U CN201720323528U CN206727895U CN 206727895 U CN206727895 U CN 206727895U CN 201720323528 U CN201720323528 U CN 201720323528U CN 206727895 U CN206727895 U CN 206727895U
- Authority
- CN
- China
- Prior art keywords
- rotating shaft
- fuselage
- cavity
- axle
- blowning installation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
It the utility model is related to a kind of inverter, including fuselage, rotated along its length in the fuselage and be provided with rotating shaft, cavity is provided with the rotating shaft, the side wall of the rotating shaft is provided through the through hole connected with cavity, the both ends of the rotating shaft are respectively arranged with the blowning installation and getter device connected with cavity, and the utility model has the advantages that：It can be blown using blowning installation in cavity, the dust of fuselage interior is blown afloat, dust is set to swim in fuselage interior, then getter device is started, getter device can produce getter action to through hole, and then will float in aerial dust suction through hole, and then be drawn into cavity, cleared up the dust in fuselage；Meanwhile exchanged by the way that the air in fuselage to carrying out air-breathing in fuselage, can be accelerated with extraneous, and then play the effect for accelerating cooling.
Description
Technical field
Electricity field is the utility model is related to, more particularly to a kind of inverter.
Background technology
Direct current is transformed into alternating current using thyristor circuit, this reverse process corresponding to rectification, is defined as inverse
Become.Direct current can be transformed into alternating current by inverter, and be sent in power network alternating current is counter.
Chinese patent if Authorization Notice No. is " CN205178482U " discloses a kind of inverter, it is generally the case that
Can all be provided with the thermovent for radiating on the shell of this kind of inverter, however when machine in an idle state when, radiating
Fan at mouthful is in halted state, and now the dust in extraneous air easily enters in machine at thermovent, and then may
The performance of machine can be influenceed, this problem is badly in need of solving.
Utility model content
The purpose of this utility model is to provide a kind of inverter that can remove the dust in fuselage.
Above-mentioned technical purpose of the present utility model technical scheme is that：A kind of inverter, bag
Fuselage is included, is rotated along its length in the fuselage and is provided with rotating shaft, cavity, the side of the rotating shaft are provided with the rotating shaft
Wall is provided through the through hole connected with cavity, and the both ends of the rotating shaft are respectively arranged with the blowning installation connected with cavity and suction
Device of air.
By using above-mentioned technical proposal, when having dust in fuselage, can be blown using blowning installation in cavity, gas from
Through hole is discharged, and is blown in fuselage interior, and the dust of fuselage interior is blown afloat, dust is swum in fuselage interior, is turned by rotating
Maximization gas can be made when being blown from through hole for axle and the contact area of fuselage interior, more dusts is floated
In fuselage interior, then start getter device, getter device can produce getter action to through hole, and then will float in atmosphere
Dust suction through hole in, and then be drawn into cavity, cleared up the dust in fuselage；Meanwhile by entering in fuselage
Row air-breathing, the air that can accelerate in fuselage exchanges with extraneous, and then plays the effect for accelerating cooling.
Preferably, the both ends on the shaft length direction are respectively arranged with the bearing being fixed on rotating shaft on fuselage,
The both ends of the rotating shaft are plugged within the bearing respectively, and the getter device and blowning installation are respectively sleeved on bearing.
By using above-mentioned technical proposal, bearing is fixed on fuselage, and rotating shaft plugs within the bearing, and now rotating shaft can
Rotated in fuselage, simultaneously as blowning installation and getter device are set on bearing, therefore rotating shaft is while rotating, energy
Enough air-breathing or air blowings into cavity.
Preferably, be circumferentially provided with fluted disc along it in the rotating shaft, motor is provided with the fuselage, on the motor
It is provided with the gear that axis of rotation is moved with fluted disc mating band.
By using above-mentioned technical proposal, after starting motor, motor can drive pinion rotation, because gear can be with tooth
Disk coordinates, therefore band active toothed disk rotates while pinion rotation, and because fluted disc being circumferentially provided in rotating shaft along rotating shaft, therefore
Fluted disc can drive axis of rotation while rotating, therefore axis of rotation can be driven by starting motor.
Preferably, also include the delay control circuit for controlling getter device and blowning installation alternation.
By using above-mentioned technical proposal, blowning installation and getter device alternation can be controlled using control circuit,
After being blown afloat the dust in fuselage, then it is inhaled into cavity, it is more convenient by the control use of circuit.
Preferably, the length direction of the cavity interior edge rotating shaft is provided with dividing plate, the cavity includes being separated by dividing plate
Air blowing chamber and suction muffler, the blowning installation connects with air blowing chamber, and the getter device connects with suction muffler.
By using above-mentioned technical proposal, cavity can be divided into air blowing chamber and suction muffler by dividing plate, blowning installation by certain
After dust at one is blown afloat, with the rotation of rotating shaft, the through hole connected with suction muffler turns to the opening position, by the dust at this
Suck in suction muffler；Because both suction muffler and air blowing chamber are separated, dust is inhaled into suction muffler during air-breathing, when
When being blown at air blowing chamber to through hole, the dust in suction muffler will not be blown out again, prevented to causing secondary dirt in fuselage
Dye.
Preferably, described one end for blowing chamber is provided with the first sealing plate, the other end and blowning installation of the air blowing chamber
Connection, one end away from the first sealing plate of the suction muffler are provided with the second sealing plate, the other end of the suction muffler and suction
Device of air connects.
By using above-mentioned technical proposal, when the blowning installation for being connected to air blowing chamber one end carries out air blowing work to air blowing intracavitary
Used time, because the suction muffler of the end is sealed by the second sealing plate, therefore the gas that can prevent from blowing out in blowning installation enters
In suction muffler, it is blown the dust in suction muffler；Similarly, the first sealing plate can separate getter device and air blowing chamber, prevent
Only the blowing effect of blowning installation is influenceed by getter device.
Preferably, the rotating shaft includes being rotatably connected on first axle and the second axle in fuselage respectively, the cavity and
Through hole is all disposed within first axle and the second axle, the connection of the end of the blowning installation and first axle, the getter device and the
The end connection of two axles.
By using above-mentioned technical proposal, during work, first axle is responsible for blowing from through hole, and the dust in fuselage is blown
Rise, the second axle is responsible for air-breathing, and the dust floated in fuselage is drawn into the cavity in the second axle from through hole, by first axle and
Second axle works simultaneously, makes air blowing and air-breathing while carries out, improves operating efficiency.
Preferably, the rotating shaft is circumferentially provided with the hairbrush for clearing up dust along it.
By using above-mentioned technical proposal, when air blowing in fuselage may some places can not be blown to, or due to ash
The absorption affinity of dirt and fuselage is bigger to cause dust not blown afloat, and by installing hairbrush, hairbrush can sweep up dust, improves
The effect of cleaning.
In summary, the utility model has the advantages that：, can be empty using blowning installation when having dust in fuselage
Blown in chamber, gas is discharged from through hole, and is blown in fuselage interior, and the dust of fuselage interior is blown afloat, dust is swum in fuselage
Inside, can make maximization gas when being blown from through hole and the contact area of fuselage interior by rotating shaft, make more
More dusts can swim in fuselage interior, then start getter device, and getter device can produce getter action to through hole, enter
And will float in aerial dust suction through hole, and then be drawn into cavity, cleared up the dust in fuselage；Together
When, exchanged by the way that the air in fuselage to carrying out air-breathing in fuselage, can be accelerated with extraneous, and then play the effect for accelerating cooling
Fruit.
Brief description of the drawings
Fig. 1 is the structural representation of embodiment 1, for embodying the position of rotating shaft；
Fig. 2 is the structural representation of roller end in embodiment 1, for embodying the position of cavity；
Fig. 3 is the circuit theory diagrams of delay control circuit in embodiment 1, for embodying the connection side of delay control circuit
Formula；
Fig. 4 is the circuit theory diagrams of blowning installation and control device in embodiment 1, for embodying blowning installation and air-breathing dress
Put annexation in circuit；
Fig. 5 is the structural representation of the first end of rotating shaft in embodiment 2, for embodying shape and the position of the first sealing plate
Put；
Fig. 6 is the structural representation at the second end of rotating shaft in embodiment 2, for embodying shape and the position of the second sealing plate
Put；
Fig. 7 is the structural representation of embodiment 3, for embodying the position of first axle and the second axle.
In figure, 1, fuselage；11st, blowning installation；12nd, getter device；14th, motor；15th, gear；2nd, rotating shaft；21st, through hole；
22nd, bearing；23rd, fluted disc；24th, first axle；25th, the second axle；26th, hairbrush；3rd, cavity；31st, dividing plate；32nd, air blowing chamber；33rd, air-breathing
Chamber；34th, the first sealing plate；35th, the second sealing plate；4th, delay control circuit；5th, thermovent.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
This specific embodiment is only that it is not to limitation of the present utility model, ability to explanation of the present utility model
Field technique personnel can make the modification of no creative contribution to the present embodiment as needed after this specification is read, but
As long as all protected in right of the present utility model by Patent Law.
Embodiment 1：A kind of inverter, as depicted in figs. 1 and 2, the shape of fuselage 1 is in cuboid, and the outside of fuselage 1 is passed through
Wear and be equipped with thermovent 5.The length direction of the interior edge fuselage 1 of fuselage 1 is rotatably connected to rotating shaft 2, and cavity 3 is offered inside rotating shaft 2,
The side wall of rotating shaft 2 circumferentially runs through the through hole 21 for offering and being connected with cavity 3, length direction distribution of the through hole 21 along rotating shaft 2 along it.
The both ends that fuselage 1 is located at the length direction of rotating shaft 2 are separately installed with bearing 22, and rotating shaft 2 is plugged in bearing 22.The both ends of rotating shaft 2
Blowning installation 11 and getter device 12 are connected to, blowning installation 11 is air blower, and getter device 12 is asepwirator pump.Blow and fill
Put 11 and getter device 12 be respectively sleeved on bearing 22.The outside of fuselage 1 is also equipped with motor 14, in the rotary shaft of motor 14
Gear 15 is connected with, gear 15 is located at the inside of fuselage 1.The fluted disc 23 coordinated with gear 15 is connected with rotating shaft 2, makes rotating shaft 2
It can be rotated by motor 14.
As shown in figure 3, delay control circuit 4 includes the first relay KM1, the second relay KM2, the first delay relay
Device KT1, the second time-delay relay KT2.First relay KM1 includes first coil, the first normal open switch SM11, first normally closed opened
Close SM12；Second relay KM2 includes the second coil, the second normally closed switch SM21, the second normal open switch SM22；First delay after
Electrical equipment KT1 includes the first delay coil, the first normally closed delay switch ST11, the first normally opened delay switch ST12；Second delay after
Electrical equipment KT2 includes the second delay coil, the second normally opened delay switch ST21, the second normally closed delay switch ST22.Wherein, first is normal
Close the normally closed delay switch ST22 of delay switch ST11 and second and disconnect instantaneous closo for delay；First normally opened delay switch ST12
It is timing closing moment disconnection type with the second normally opened delay switch ST21.The one of delay control circuit 4 is terminated with power supply VCC, separately
One end is grounded, and power supply VCC is in series with normally closed button S2, normally opened button S1, the first normally closed delay switch ST11, the first relay
KM1, the second normally closed switch SM21.It is parallel with normal open switch S1 on the first normal open switch SM11, the first normal open switch SM11 simultaneously
Join the second normally opened delay switch ST21.The first normally opened delay switch ST12, second normally closed is parallel between normally closed button S2 and ground
Delay switch ST22, the second relay KM2, second is parallel with the first normally closed switch SM12, the first normally opened delay switch ST12
Normal open switch SM22.The first normal open switch SM11 and the first time-delay relay KT1 are parallel between normally closed button S2 and ground, it is normally closed
The second normal open switch SM22 and the second time-delay relay KT2 are also parallel between button S2 and ground.
As shown in figure 4, the first normal open switch SM11 connects with blowning installation 11, the second normal open switch SM22 and getter device
12 series connection.
Application method：When having dust in fuselage 1, start motor 14, make motor 14 drive rotating shaft 2 to rotate, then press often
Open button S1 start-up studies control circuit 4.Now the first relay KM1 is obtained electric, the first normal open switch SM11 obtain it is electric, realize from
Lock, and blowning installation 11 is started working.Blowning installation 11 can blow afloat dust, make dust floating in atmosphere.First is normally closed
Switch SM12 to disconnect, the first time-delay relay KT1 obtains electric.Blowning installation 11 worked after a period of time, the first normally closed delay switch
ST11 disconnects, and the first relay KM1 power-off, blowning installation 11 stops, the first normally opened delay switch ST12 closures.Now second after
Electrical equipment KM2 obtain it is electric, the second normally closed switch SM21 disconnect make the first normal open switch SM11 disconnect, the second normal open switch SM22 closure,
Getter device 12 is started working.Getter device 12 can will float aerial dust and is drawn into from through hole 21 in cavity 3.Inhale
Device of air 12 worked after a period of time, and the second normally closed delay switch ST22 disconnects, the second normally opened delay switch ST21 closures, and first
Relay KM1 obtains electric, makes the alternation of blowning installation 11.
Embodiment 2：A kind of inverter, the structure of the present embodiment 2 is substantially the same manner as Example 1, and its difference is, such as schemes
Shown in 5 and Fig. 6, the length direction of the interior edge rotating shaft 2 of rotating shaft 2 is provided with dividing plate 31, and cavity 3 is divided into axial symmetry by dividing plate 31
Two parts, respectively air blowing chamber 32 and suction muffler 33.One end of the length direction of air blowing chamber 32 is provided with can be by air blowing chamber 32
First sealing plate 34 of sealing, the one end of air blowing chamber 32 away from the first sealing plate 34 connects with blowning installation 11.Suction muffler 33 is remote
One end from the first sealing plate 34 is provided with and can connect the second sealing plate 35 of the end part seal, the other end of suction muffler 33
There is getter device 12.Blowning installation 11 and getter device 12 are respectively sleeved on bearing 22.
Application method：The application method of the present embodiment 2 is substantially the same manner as Example 1, and its difference is, during use first with
The drive shaft 2 of motor 14 rotates, and then starts blowning installation 11 and getter device 12.Gas in blowning installation 11 passes through air blowing
Chamber 32 blows out through hole 21, and the dust in fuselage 1 is blown afloat.When the through hole 21 that is connected with suction muffler 33 is turned to close to being insufflated
When at dust, dust is inhaled into suction muffler 33.
Embodiment 3：A kind of inverter, the structure of the present embodiment 3 is substantially the same manner as Example 1, and its difference is, such as schemes
Shown in 7, rotating shaft 2 includes the axle 25 of first axle 24 and second being rotatably installed in fuselage 1, and first axle 24 and the second axle 25 are mutually equal
Go and be fitted with fluted disc 23 between the two, two fluted discs 23 all match with gear 15.All opened in the axle 25 of first axle 24 and second
The through hole 21 connected provided with cavity 3 and with cavity 3.Hairbrush 26 is installed along its circumference in first axle 24, hairbrush 26 is also along
The length direction distribution of one axle 24.The end of first axle 24 and the end of the second axle 25 are connected to blowning installation 11 and air-breathing
Device 12.
Application method：The application method of the present embodiment 3 is substantially the same manner as Example 1, and its difference is, starts electricity during use
Machine 14 drives the axle 25 of first axle 24 and second to rotate simultaneously, and the hairbrush 26 while rotating of first axle 24 can be brushed on the fuselage 1, lead to
Cross hairbrush 26 to play the dust brush on fuselage 1, and then dust is swum in fuselage 1.
Claims (8)
1. a kind of inverter, including fuselage (1), it is characterised in that：Rotate and be provided with along its length in the fuselage (1)
Rotating shaft (2), the rotating shaft (2) is interior to be provided with cavity (3), and the side wall of the rotating shaft (2) is provided through what is connected with cavity (3)
Through hole (21), the both ends of the rotating shaft (2) are respectively arranged with the blowning installation (11) and getter device that are connected with cavity (3)
(12)。
A kind of 2. inverter according to claim 1, it is characterised in that：Both ends on rotating shaft (2) length direction
Be respectively arranged with the bearing (22) rotating shaft (2) being fixed on fuselage (1), the both ends of the rotating shaft (2) are plugged in bearing respectively
(22) in, the getter device (12) and blowning installation (11) are respectively sleeved on bearing (22).
A kind of 3. inverter according to claim 1, it is characterised in that：It is circumferentially provided with the rotating shaft (2) along it
Fluted disc (23), motor (14) is provided with the fuselage (1), be provided with the motor (14) and fluted disc (23) mating band turn
The gear (15) that axle (2) rotates.
A kind of 4. inverter according to claim 1, it is characterised in that：Also include for controlling getter device (12)
With the delay control circuit (4) of blowning installation (11) alternation.
A kind of 5. inverter according to claim 2, it is characterised in that：The length of cavity (3) the interior edge rotating shaft (2)
Direction is provided with dividing plate (31), and the cavity (3) includes the air blowing chamber (32) and suction muffler (33) separated by dividing plate (31), described
Blowning installation (11) connects with air blowing chamber (32), and the getter device (12) connects with suction muffler (33).
A kind of 6. inverter according to claim 5, it is characterised in that：It is close that one end of the air blowing chamber is provided with first
Shrouding (34), the other end of the air blowing chamber (32) are connected with blowning installation (11), and remote the first of the suction muffler (33) is close
One end of shrouding (34) is provided with the second sealing plate (35), and the other end of the suction muffler (33) is connected with getter device (12).
A kind of 7. inverter according to claim 1, it is characterised in that：The rotating shaft (2) includes being rotatablely connected respectively
First axle (24) and the second axle (25) in fuselage (1), the cavity (3) and through hole (21) be all disposed within first axle (24) and
On second axle (25), the blowning installation (11) is connected with the end of first axle (24), the getter device (12) and the second axle
(25) end connection.
A kind of 8. inverter according to claim 1, it is characterised in that：The rotating shaft (2) is circumferentially disposed useful along its
In the hairbrush (26) of cleaning dust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720323528.1U CN206727895U (en) | 2017-03-30 | 2017-03-30 | A kind of inverter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720323528.1U CN206727895U (en) | 2017-03-30 | 2017-03-30 | A kind of inverter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206727895U true CN206727895U (en) | 2017-12-08 |
Family
ID=60503364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720323528.1U Expired - Fee Related CN206727895U (en) | 2017-03-30 | 2017-03-30 | A kind of inverter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206727895U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110094493A (en) * | 2019-06-06 | 2019-08-06 | 浙江波士特机械有限公司 | Aeroassisted shift handle |
-
2017
- 2017-03-30 CN CN201720323528.1U patent/CN206727895U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110094493A (en) * | 2019-06-06 | 2019-08-06 | 浙江波士特机械有限公司 | Aeroassisted shift handle |
| CN110094493B (en) * | 2019-06-06 | 2024-01-19 | 浙江波士特集团有限公司 | Pneumatic auxiliary gear shifting handle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171208 Termination date: 20180330 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |