CN205123501U - A cooling structure and aviation air cooling motor for aviation air cooling motor - Google Patents
A cooling structure and aviation air cooling motor for aviation air cooling motor Download PDFInfo
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- CN205123501U CN205123501U CN201520910704.2U CN201520910704U CN205123501U CN 205123501 U CN205123501 U CN 205123501U CN 201520910704 U CN201520910704 U CN 201520910704U CN 205123501 U CN205123501 U CN 205123501U
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- aviation
- cooling structure
- supercharging
- ventilated machine
- outer shroud
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Abstract
The utility model discloses a cooling structure and aviation air cooling motor for aviation air cooling motor. A cooling structure includes for aviation air cooling motor: ventilation pipe (1), ventilation pipe (1) cavity, axial flow fan (2), axial flow fan (2) set up in ventilation pipe (1), pressure boost end cover (3), pressure boost end cover (3) set up axial flow fan's air outlet end to with ventilation pipe (1) in order can the dismantlement mode being connected, wherein, be provided with pressure boost blade (31) on pressure boost end cover (3), pressure boost blade (31) are used for oneself the air current pressure boost of the air outlet end of axial flow fan (2). The utility model provides a cooling structure combines together axial flow fan and booster fan, for the prior art for aviation air cooling motor the utility model discloses a what produce is used for aviation air cooling motor's cooling structure cooling blast to possess the advantage that the flow is big, pressure is big simultaneously.
Description
Technical field
The utility model relates to aviation ventilated machine cooling technology field, particularly relates to a kind of cooling structure for aviation ventilated machine and aviation ventilated machine.
Background technology
At present, general tube-axial fan or the centrifugal fan of adopting of aviation ventilated machine cooling cools two kinds of modes, due to the design feature of two kinds of fans itself, the cooling blast flow that tube-axial fan produces is large, pressure is little, and the cooling blast pressure of centrifugal fan is large, flow is little.Along with the power of aviation ventilated machine constantly increases, these two kinds of cooling structures are difficult to meet motor cooling requirement.
Therefore, wish that a kind of technical scheme can overcome or reduce at least one shortcoming above-mentioned.
Utility model content
The purpose of this utility model is to provide a kind of cooling structure for aviation ventilated machine, to overcome or to reduce at least one shortcoming above-mentioned.
For achieving the above object, the utility model provides a kind of cooling structure for aviation ventilated machine.Described cooling structure comprises: ventilation duct, described ventilation duct hollow; Tube-axial fan, described tube-axial fan is arranged in described ventilation duct; Supercharging end cap, described supercharging end cap is arranged on described tube-axial fan air opening end, and is removably connected with ventilation duct; Wherein, described pressurized end covers and is provided with supercharging blade, and described supercharging blade is used for the air-flow supercharging of the air opening end from described tube-axial fan.
Preferably, described supercharging end cap is ring-type end cap, and it comprises inner ring and outer shroud, and described supercharging blade is distributed between described inner ring and described outer shroud.
Preferably, described inner ring is provided with bearing chamber, for installing with rotor bearing adaptation; Described outer shroud is provided with bolt hole, and described bolt hole is used for being connected with motor case.
Preferably, described outer shroud edge extends to described ventilation duct direction, forms an outer shroud edge surface, described outer shroud edge surface is provided with outer shroud edge surface bolt hole, and described outer shroud edge surface bolt hole is used for being connected with described ventilation duct.
Preferably, described supercharging blade is multiple, and described supercharging blade is provided with brush brush holder, and described brush brush holder is multiple, and each described brush brush holder is arranged on two adjacent supercharging blades.
Preferably, the blade edge of described tube-axial fan is 3 millimeters of 1 apart from the distance between described ventilation duct tube wall.
The utility model additionally provides a kind of aviation ventilated machine, and described aviation ventilated machine comprises motor and the cooling structure for aviation ventilated machine as above, and described motor and the described cooling structure for aviation ventilated machine are interconnected.
Tube-axial fan and force(d) (draft) fan combine by the cooling structure for aviation ventilated machine that the utility model provides, relative to prior art, the cooling structure cooling blast for aviation ventilated machine of generation of the present utility model possesses the advantage that flow is large, pressure is large simultaneously.
Accompanying drawing explanation
Fig. 1 is the structural representation of the cooling structure for aviation ventilated machine according to the utility model one embodiment.
Fig. 2 is the Facad structure schematic diagram of the cooling structure for aviation ventilated machine shown in Fig. 1.
Reference numeral:
| 1 | Ventilation duct | 32 | Inner ring |
| 2 | Tube-axial fan | 33 | Outer shroud |
| 3 | Supercharging end cap | 34 | Brush brush holder |
| 31 | Supercharging blade |
Embodiment
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection range can not be interpreted as.
Fig. 1 is the structural representation of the cooling structure for aviation ventilated machine according to the utility model one embodiment.Fig. 2 is the Facad structure schematic diagram of the cooling structure for aviation ventilated machine shown in Fig. 1.
The cooling structure for aviation ventilated machine as shown in Figure 1 comprises: ventilation duct 1, tube-axial fan 2 and supercharging end cap 3.Wherein, ventilation duct 1 hollow; Tube-axial fan 2 is arranged in ventilation duct 1; Supercharging end cap 3 is arranged on the air opening end of tube-axial fan, and is removably connected with ventilation duct 1; Supercharging end cap 3 is provided with supercharging blade 31, supercharging blade 31 is for the air-flow supercharging by the air opening end from tube-axial fan 2.
See Fig. 2, in the present embodiment, supercharging end cap 3 is ring-type end cap, and it comprises inner ring 32 and outer shroud 33, and supercharging blade 31 is distributed between inner ring 32 and outer shroud 33.
In the present embodiment, inner ring 32 is provided with bearing chamber, for installing with rotor bearing adaptation; Outer shroud 33 is provided with bolt hole, and bolt hole is used for being connected with motor case.
See Fig. 1, in the present embodiment, outer shroud edge extends to ventilation duct direction, forms an outer shroud edge surface, outer shroud edge surface is provided with outer shroud edge surface bolt hole, and outer shroud edge surface bolt hole is used for being connected with ventilation duct 1.
See Fig. 2, in the present embodiment, supercharging blade 31 is multiple, supercharging blade 31 is provided with brush brush holder 34, and brush brush holder 34 is multiple, and each brush brush holder 34 is arranged on two adjacent supercharging blades 31.Be understandable that, the quantity of brush brush holder can sets itself as required.Such as, 4,6 or other quantity.
In the present embodiment, the distance between the blade edge Distance Ventilation tube wall of tube-axial fan is 3 millimeters of 1.
The utility model additionally provides a kind of aviation ventilated machine, and described aviation ventilated machine comprises motor and the cooling structure for aviation ventilated machine as above, and described motor and the described cooling structure for aviation ventilated machine are interconnected.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (7)
1. for a cooling structure for aviation ventilated machine, it is characterized in that, the described cooling structure for aviation ventilated machine comprises:
Ventilation duct (1), described ventilation duct (1) hollow;
Tube-axial fan (2), described tube-axial fan (2) is arranged in described ventilation duct (1);
Supercharging end cap (3), described supercharging end cap (3) is arranged on the air opening end of described tube-axial fan, and is removably connected with ventilation duct (1); Wherein,
Described supercharging end cap (3) is provided with supercharging blade (31), and described supercharging blade (31) is for will from the air-flow supercharging of the air opening end of described tube-axial fan (2).
2. as claimed in claim 1 for the cooling structure of aviation ventilated machine, it is characterized in that, described supercharging end cap (3) is ring-type end cap, it comprises inner ring (32) and outer shroud (33), and described supercharging blade (31) is distributed between described inner ring (32) and described outer shroud (33).
3. as claimed in claim 2 for the cooling structure of aviation ventilated machine, it is characterized in that, (32) are provided with bearing chamber to described inner ring, for installing with rotor bearing adaptation; (33) are provided with bolt hole to described outer shroud, and described bolt hole is used for being connected with motor case.
4. as claimed in claim 3 for the cooling structure of aviation ventilated machine, it is characterized in that, described outer shroud edge extends to described ventilation duct direction, form an outer shroud edge surface, described outer shroud edge surface is provided with outer shroud edge surface bolt hole, described outer shroud edge surface bolt hole is used for being connected with described ventilation duct (1).
5. as claimed in claim 4 for the cooling structure of aviation ventilated machine, it is characterized in that, described supercharging blade (31) is for multiple, described supercharging blade (31) is provided with brush brush holder (34), described brush brush holder (34) is for multiple, and each described brush brush holder (34) is arranged on two adjacent supercharging blades (31).
6., as claimed in claim 5 for the cooling structure of aviation ventilated machine, it is characterized in that, the blade edge of described tube-axial fan is 1 millimeter to 3 millimeters apart from the distance between described ventilation duct tube wall.
7. an aviation ventilated machine, it is characterized in that, described aviation ventilated machine comprises motor and as the cooling structure for aviation ventilated machine in claim 1 to 6 as described in any one, and described motor and the described cooling structure for aviation ventilated machine are interconnected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520910704.2U CN205123501U (en) | 2015-11-16 | 2015-11-16 | A cooling structure and aviation air cooling motor for aviation air cooling motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520910704.2U CN205123501U (en) | 2015-11-16 | 2015-11-16 | A cooling structure and aviation air cooling motor for aviation air cooling motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205123501U true CN205123501U (en) | 2016-03-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520910704.2U Active CN205123501U (en) | 2015-11-16 | 2015-11-16 | A cooling structure and aviation air cooling motor for aviation air cooling motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205123501U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374302A (en) * | 2018-12-07 | 2019-02-22 | 北京理工大学 | A kind of small rotor engine rig test air cooling system |
-
2015
- 2015-11-16 CN CN201520910704.2U patent/CN205123501U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374302A (en) * | 2018-12-07 | 2019-02-22 | 北京理工大学 | A kind of small rotor engine rig test air cooling system |
| CN109374302B (en) * | 2018-12-07 | 2020-02-07 | 北京理工大学 | Air cooling system for small rotor engine bench test |
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| GR01 | Patent grant |