CN110401173B - Short-circuit fault isolation structure of aviation motor - Google Patents
Short-circuit fault isolation structure of aviation motor Download PDFInfo
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- CN110401173B CN110401173B CN201910652290.0A CN201910652290A CN110401173B CN 110401173 B CN110401173 B CN 110401173B CN 201910652290 A CN201910652290 A CN 201910652290A CN 110401173 B CN110401173 B CN 110401173B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/08—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors
- H02H7/085—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric motors against excessive load
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/08—Insulating casings
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Motor Or Generator Frames (AREA)
Abstract
The utility model provides an aeronautical motor's short-circuit fault isolation structure, includes electrically insulated end cover, insulating bolt, electrically insulated bearing, current detection device and normally closed switch. The electric insulation end covers are respectively arranged at the front end and the rear end of the motor shell and are fixed on the motor shell through insulation bolts. The electric insulation end cover is provided with three layers, wherein the inner layer and the outer layer are both metal layers, and the middle layer is an insulation layer. Each electric insulation end cover is provided with an inner layer of through holes and an outer layer of through holes, the through holes are coaxially and uniformly arranged in an equal radius mode by taking the rotating shaft as the center, the positions of the inner layer of through holes and the outer layer of through holes correspond to each other, and the three-layer structure is fixed into a whole by the aid of the insulation bolts penetrating through the through holes. The insulating bolt consists of a bolt, an insulating gasket and an insulating sleeve, the insulating gasket is padded at the contact part of the bolt and the end face of the metal shell, and the insulating sleeve is sleeved at the position where the cylindrical surface of the bolt penetrates through the end cover and the metal shell. The motor shell is grounded through the current detection device and the switch, the motor shell is connected with the current detection device, the current detection device is connected with the normally closed switch, and the rear end of the normally closed switch is grounded.
Description
Technical Field
The invention relates to a motor, in particular to a short-circuit fault isolation structure of an aviation motor.
Background
At present, a multi-electric/full-electric airplane enters a full development stage, an aviation motor system gradually replaces an original hydraulic mechanism and the like on the multi-electric/full-electric airplane, and high-power propulsion energy is provided on an electric propulsion airplane. The aero-generator system needs to meet the electric energy requirements of high-capacity and high-reliability electric equipment of the airplane. Therefore, modern aero-electric machine systems, consisting of aero-electric motor systems and generator systems, are an important foundation supporting the development of aircraft electrification.
During operation of an aircraft motor, various short-circuit faults may occur, such as inter-turn short circuits, inter-phase short circuits, winding-to-casing short circuits, etc., which may cause sparks or arcs. The aviation motor can seriously affect the flight safety when short circuit occurs, and demagnetization and arc extinction treatment are usually required when short circuit faults occur. However, due to the particularity of the high-altitude working environment of the aviation motor, high-altitude arc extinction is difficult, and the controllability is not high; the electric excitation motor with the de-excitation function has the advantages of complex structure, low rotating speed, low power density and low efficiency. Although the permanent magnet motor has simple structure, high rotating speed, high power density and high efficiency, the permanent magnet rotor is difficult to de-energize, which affects the application of the permanent magnet motor in the aviation motor. Therefore, if arc extinction and demagnetization are not needed, the problem of short circuit of the aviation permanent magnet motor can be solved from other angles, and the method is a good method.
Patent CN201521058794.3 proposes a new insulation structure of an insulation end cover of a wind driven generator. The utility model discloses a what mainly protect is that a restriction axle current produces the insulating end cover technique that adopts, the design is for installing the position of installing the end cover on generator bearing room, and is insulating completely with the bearing room to the end cover, and restriction axle current produces. The insulation is realized by an insulation lantern ring, a bolt lantern ring and a large gasket.
Patent CN201410530835.8 proposes a motor stator, an insulating end cover of the motor stator and a motor. The insulation end cover comprises a cover body and a plurality of end cover teeth, the end cover teeth are arranged on the outer peripheral surface of the cover body and are spaced from each other along the circumferential direction of the cover body, end cover grooves corresponding to the stator grooves are formed between adjacent end cover teeth, paper clamping grooves are formed in the end cover teeth, insulation groove paper is arranged in the stator grooves, and two ends of the insulation groove paper are respectively matched in the paper clamping grooves. This design is also used to limit the generation of shaft currents and is structurally complex.
The prior patents are basically the same as the two listed patents in the aspect of designing the motor insulation end cover, and are aimed at shaft current limitation, but besides the shaft current needing to be limited, various short-circuit conditions which can occur to the motor winding need to be considered.
Disclosure of Invention
The invention aims to overcome the defect that the aviation permanent magnet motor is not easy to extinguish arc and demagnetize when short-circuit faults occur in the operation, and provides a short-circuit fault isolation structure of the aviation motor. The invention starts from the angle of cutting off a short-circuit current path, starts from the structural design of the motor, and even if a short-circuit fault occurs, the whole motor is insulated from the outside, so that large current cannot be generated, and serious consequences are avoided.
The short-circuit fault isolation structure of the aviation motor comprises an electric insulation end cover, an insulation bolt, an electric insulation bearing, a current detection device and a normally closed switch.
The electric insulation end covers are respectively arranged at the front end and the rear end of the motor shell and are fixed on the motor shell through insulation bolts. The electric insulation end cover adopts a three-layer sandwich structure, the inner layer and the outer layer are metal layers, namely an inner metal layer and an outer metal layer, and the middle layer is an insulation layer. In order to compact the three-layer structure, an inner layer of through holes and an outer layer of through holes are formed in each layer of end cover, the through holes are coaxially and uniformly arranged in an equal radius mode by taking the rotating shaft as the center, and the positions of the inner layer of through holes correspond to the positions of the outer layer of through holes. The inner layer through hole is arranged inside the outer layer through hole, and the radius of the ring where the inner layer through hole is arranged is smaller than that of the ring where the outer layer through hole is arranged. And compressing and fixing the inner metal layer, the insulating layer and the outer metal layer into a whole by using an insulating bolt to form the electric insulating end cover.
The insulating bolt consists of a bolt, an insulating gasket and an insulating sleeve, the insulating gasket is padded at the contact part of the bolt and the end face of the metal shell, and the insulating sleeve is sleeved at the position where the cylindrical surface of the bolt penetrates through the end cover and the metal shell to ensure that the end cover shell is insulated from the motor shell.
The motor bearing adopts an electric insulation bearing, such as a ceramic ball bearing, and is matched with the insulation end cover, so that short-circuit current is prevented from flowing through the rotor.
Furthermore, in order to avoid possible short-circuit faults of the aviation motor during operation, the aviation motor shell is grounded through the current detection device and the switch, the motor shell is connected with the current detection device, the current detection device is connected with the normally closed switch, and the rear end of the normally closed switch is grounded. When the current flows to the ground through the grounding wire, the current flows through the current detection device firstly, when the winding is in short circuit with the casing, large current is generated, when the current detection device detects the large current exceeding the set standard, the normally closed switch on the grounding wire is disconnected, the grounding loop is cut off in time, and the potential of the motor shell rises at the moment, but the discharge to the ground can not occur, so that the protection effect is achieved. Thereby isolating the winding-to-case short circuit fault that may occur during operation of the aircraft motor.
Drawings
FIG. 1 is a schematic diagram of a short-circuit fault isolation structure of an aero-motor of the present invention;
FIG. 2 is a schematic view of the structure of an insulating end cap of the motor of the present invention;
FIG. 3 is a schematic view of the structure of an insulating end cap of the motor of the present invention;
FIGS. 4a and 4b are schematic views of the structure of the insulating bolt of the present invention;
FIG. 5 is a schematic view of the overall structure of the motor of the present invention;
fig. 6 is a schematic view of the overall structure of the motor of the present invention.
In the figure: 1 motor, 2 insulating end covers, 3 interior metal layers, 4 outer metal layers, 5 insulating layers, 6 insulating bolts, 7 electrically insulated bearings, 8 current detection devices, 9 switches, 10 casings, 11 bolts, 12 insulating gaskets and 13 insulating sleeves.
Detailed Description
As shown in fig. 1, the short-circuit fault isolation structure of the aero-motor of the embodiment of the present invention includes: the device comprises an electric insulation end cover 2, an insulation bolt 6, an electric insulation bearing 7, a current detection device 8 and a switch 9.
The invention relates to an aviation motor 1 with a short-circuit fault isolation structure, wherein electric insulation end covers 2 are respectively arranged at the front end and the rear end of a motor shell and are fixed on the motor shell 10 through insulation bolts 6. As shown in fig. 2 and 3, the insulating end cap 2 is of a three-layer sandwich structure, the inner layer and the outer layer are metal layers, the inner metal layer 3 and the outer metal layer 4 are respectively formed on the inner layer and the outer layer, the middle layer is an insulating layer 5, in order to compress the three-layer structure of the insulating end cap 2, an inner layer through hole and an outer layer through hole are formed in each electric insulating end cap, the through holes are coaxially and uniformly arranged in the same radius by taking the rotating shaft as the center, and the positions of the inner layer through hole and the. The inner layer through hole is arranged inside the outer layer through hole, and the radius of the ring where the inner layer through hole is arranged is smaller than that of the ring where the outer layer through hole is arranged. The insulating bolts 6 compress and fix the inner metal layer 3, the insulating layer 5 and the outer metal layer 4 as a whole to form the electrically insulating end cap 2.
As shown in fig. 4a and 4b, the insulating bolt 6 is composed of a bolt 11, an insulating washer 12 and an insulating sleeve 13. An insulating gasket 12 is padded at the contact part of the bolt 11 and the end face of the metal shell, and an insulating sleeve 13 is sleeved at the position where the cylindrical surface of the bolt 11 penetrates through the end cover and the metal shell to ensure that the end cover shell is insulated from the motor shell.
The motor bearing adopts an electric insulation bearing 7, such as a ceramic ball bearing, and is matched with the insulation end cover 2, so that short-circuit current is prevented from flowing through a rotor.
As shown in fig. 5 and 6, the motor, in combination with the electrically insulated bearing, the current detection device and the switch, forms a short-circuit fault isolation structure of the aircraft motor.
Further, in order to avoid short-circuit faults which may occur during the operation of the aviation motor, the motor shell is grounded through a current detection device 8 and a normally closed switch 9, the motor shell is connected with the current detection device 8, the current detection device 8 is connected with the normally closed switch 9, and the rear end of the normally closed switch 9 is grounded. When the current flows to the ground through the grounding wire, the current flows through the current detection device 8 firstly, when the motor winding short-circuits the shell, a large current is generated, when the current detection device 8 detects the large current exceeding the set standard, the normally closed switch 9 on the grounding wire is disconnected, the grounding loop is cut off in time, the potential of the motor shell rises at the moment, but the ground discharge can not occur, and the protection effect is achieved.
Claims (2)
1. The utility model provides an aeronautical motor's short-circuit fault isolation structure which characterized in that: the short-circuit fault isolation structure of the aviation motor comprises an electric insulation end cover, an insulation bolt, an electric insulation bearing, a current detection device and a normally closed switch; the electric insulation end covers are respectively arranged at the front end and the rear end of the motor shell and are fixed on the motor shell through insulation bolts; the insulating bolt consists of a bolt, an insulating gasket and an insulating sleeve, the insulating gasket is padded at the position where the bolt is contacted with the end face of the motor shell, and the insulating sleeve is sleeved at the position where the cylindrical surface of the bolt penetrates through the electric insulating end cover and the motor shell to ensure that the electric insulating end cover is insulated from the motor shell; the motor shell is grounded through the current detection device and the switch, the motor shell is connected with the current detection device, the current detection device is connected with the normally closed switch, and the rear end of the normally closed switch is grounded; when current flows to the ground through the grounding wire, the current flows through the current detection device firstly, when the motor winding short-circuits the motor shell, large current is generated, when the current detection device detects the large current exceeding a set standard, the normally closed switch on the grounding wire is disconnected, the grounding loop is cut off in time, and at the moment, the potential of the motor shell rises, but the ground discharge cannot occur, so that the protection effect is achieved; thereby isolating winding-to-motor case short circuit faults that may occur during operation of the aero motor.
2. The short-circuit fault isolation structure of an aero-motor as claimed in claim 1, wherein: the electric insulation end cover adopts a three-layer sandwich structure, the inner layer and the outer layer are metal layers, namely an inner metal layer and an outer metal layer respectively, and the middle layer is an insulation layer; each electric insulation end cover is provided with an inner layer of through holes and an outer layer of through holes, the through holes are coaxially and uniformly arranged in an equal radius mode by taking the rotating shaft as a center, and the positions of the inner layer of through holes correspond to the positions of the outer layer of through holes; the radius of a ring where the inner through hole is located is smaller than that of a ring where the outer through hole is located; the inner metal layer, the insulating layer and the outer metal layer are compressed and fixed into a whole through the insulating bolts to form the electric insulating end cover.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910652290.0A CN110401173B (en) | 2019-07-19 | 2019-07-19 | Short-circuit fault isolation structure of aviation motor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910652290.0A CN110401173B (en) | 2019-07-19 | 2019-07-19 | Short-circuit fault isolation structure of aviation motor |
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| CN110401173A CN110401173A (en) | 2019-11-01 |
| CN110401173B true CN110401173B (en) | 2021-03-26 |
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| CN113419148A (en) * | 2021-06-30 | 2021-09-21 | 深圳市准点仪器有限公司 | Testing method for motor winding insulation |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207926296U (en) * | 2018-02-13 | 2018-09-28 | 中山大洋电机股份有限公司 | A kind of motor stator and its motor of application |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| IT1182611B (en) * | 1985-10-14 | 1987-10-05 | Omp Off Meccano Plast | PROTECTION DEVICE FOR AN ELECTRIC ENGINE, IN PARTICULAR FOR THE COMPRESSOR ENGINE OF A REFRIGERATOR |
| JP5184897B2 (en) * | 2008-01-11 | 2013-04-17 | 株式会社東芝 | Submersible drive motor |
| CN201663432U (en) * | 2009-12-11 | 2010-12-01 | 森萨塔科技麻省公司 | Motor protector |
| CN201918701U (en) * | 2010-12-31 | 2011-08-03 | 浙江安美德汽车配件有限公司 | Short-circuit prevention coil rack structure of automobile engine |
| US20120243129A1 (en) * | 2011-03-24 | 2012-09-27 | General Electric Company | Shorting protection for systems having electric machines |
| CN202586584U (en) * | 2012-05-14 | 2012-12-05 | 成都佳电电机有限公司 | Insulating end cover of aerogenerator |
| CN203562867U (en) * | 2013-11-04 | 2014-04-23 | 合肥荣事达三洋电器股份有限公司 | Insulating motor cover |
| CN104362791A (en) * | 2014-10-10 | 2015-02-18 | 杭州九维自动化设备有限公司 | Motor stator, motor stator insulation end cover and motor |
| CN104578638A (en) * | 2015-02-05 | 2015-04-29 | 杭州天航国发科技有限公司 | Center point lightning-protection type vertical axis outer rotor permanent magnet coreless coil generator |
| CN105262285B (en) * | 2015-12-01 | 2018-02-23 | 中固维科（成都）动力技术有限公司 | A kind of aviation machine manufacture craft |
| CN205212604U (en) * | 2015-12-18 | 2016-05-04 | 永济市众鑫电机配件制造有限公司 | Novel insulation system of insulating end cover of aerogenerator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN207926296U (en) * | 2018-02-13 | 2018-09-28 | 中山大洋电机股份有限公司 | A kind of motor stator and its motor of application |
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