CN205089679U - Turbine fan blade rotor that turbine air compressor machine was used - Google Patents
Turbine fan blade rotor that turbine air compressor machine was used Download PDFInfo
- Publication number
- CN205089679U CN205089679U CN201520823737.3U CN201520823737U CN205089679U CN 205089679 U CN205089679 U CN 205089679U CN 201520823737 U CN201520823737 U CN 201520823737U CN 205089679 U CN205089679 U CN 205089679U
- Authority
- CN
- China
- Prior art keywords
- fan blade
- blade rotor
- rotor body
- turbine
- air compressor
- 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
Links
Abstract
The utility model discloses a turbine fan blade rotor that turbine air compressor machine was used, including fan blade rotor body, fan blade rotor body's top is provided with the centrifuge scraper, the axle center position department at fan blade rotor body's top is provided with the link, the centrifuge scraper annular sets up the outside of link, the centrifuge scraper with form a 1mm -2mm's clearance between the surface of link, be provided with the axial compressor blade on fan blade rotor body's the outer lane, fan blade rotor body's bottom is provided with vortex blade, the axle center position department of fan blade rotor body's bottom is provided with first link, vortex blade annular sets up the outside of first link, the device adopts centrifuge scraper, axial compressor blade and vortex blade, can greatly increased energy consumption utilization ratio, and improve air compression and compare.
Description
Technical field
The utility model relates to a kind of turbine fan blade rotor of turbine air compressor.
Background technique
Air compressor is a kind of conventional equipment, the compression of air can be completed by air compressor, reach equipment use needs, air compressor of the prior art is mostly individual blade rotor structure, its compression ratio is lower, energy utilization rate is lower, and the compression ratio that therefore can export under the energy consumption that communicates is lower, cannot meet actual use needs.
Summary of the invention
The technical problems to be solved in the utility model is to provide a kind of turbine fan blade rotor of turbine air compressor, and this device adopts centrifugal blade, axial blade and swirl vane, greatly can increase energy utilization rate, improves air compressing ratio.
For solving the problem, the utility model adopts following technological scheme:
A kind of turbine fan blade rotor of turbine air compressor, comprise fan blade rotor body, the top of described fan blade rotor body is provided with centrifugal blade, the shaft core position place at the top of described fan blade rotor body is provided with connecting end, described centrifugal blade annular is arranged on the outside of described connecting end, the gap of a 1mm-2mm is formed between the outer surface of described centrifugal blade and described connecting end, the outer ring of described fan blade rotor body is provided with axial blade, the bottom of described fan blade rotor body is provided with swirl vane, the shaft core position place of the bottom of described fan blade rotor body is provided with the first connecting end, described swirl vane annular is arranged on the outside of described first connecting end.
As preferred technological scheme, described centrifugal blade and described fan blade rotor body are integral type structure.
As preferred technological scheme, described axial blade and described fan blade rotor body are integral type structure.
As preferred technological scheme, described swirl vane and described fan blade rotor body are integral type structure.
The beneficial effects of the utility model are: this device adopts centrifugal blade, axial blade and swirl vane, greatly can increase energy utilization rate, improve air compressing ratio, and the structure of this device is comparatively simple, and cost is comparatively cheap, is applicable to promoting the use of.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technological scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is forward stereogram of the present utility model;
Fig. 2 is reversed isometric view of the present utility model;
Fig. 3 is plan view of the present utility model;
Fig. 4 is worm's eye view of the present utility model.
Embodiment
Below in conjunction with accompanying drawing, preferred embodiment of the present utility model is described in detail, to make advantage of the present utility model and feature can be easier to be readily appreciated by one skilled in the art, thus more explicit defining is made to protection domain of the present utility model.
Consult Fig. 1, Fig. 2, the turbine fan blade rotor of a kind of turbine air compressor shown in Fig. 3 and Fig. 4, comprise fan blade rotor body 1, the top of described fan blade rotor body 1 is provided with centrifugal blade 2, the shaft core position place at the top of described fan blade rotor body 1 is provided with connecting end 111, described centrifugal blade 2 annular is arranged on the outside of described connecting end 111, the gap of a 1mm is formed between described centrifugal blade 2 and the outer surface of described connecting end 111, the outer ring of described fan blade rotor body 1 is provided with axial blade 3, the bottom of described fan blade rotor body 1 is provided with swirl vane 4, the shaft core position place of the bottom of described fan blade rotor body 1 is provided with the first connecting end 121, described swirl vane 4 annular is arranged on the outside of described first connecting end 121.
A preferred embodiment in the utility model, the vane thickness of described centrifugal blade is 1mm, and described centrifugal blade and described fan blade rotor body are integral type structure.
A preferred embodiment in the utility model, the vane thickness of described axial blade is 0.85mm, and described axial blade and described fan blade rotor body are integral type structure.
A preferred embodiment in the utility model, the vane thickness of described swirl vane is 0.85mm, and described swirl vane and described fan blade rotor body are integral type structure.
The beneficial effects of the utility model are: this device adopts centrifugal blade, axial blade and swirl vane, greatly can increase energy utilization rate, improve air compressing ratio, and the structure of this device is comparatively simple, and cost is comparatively cheap, is applicable to promoting the use of.
The above, be only embodiment of the present utility model, but protection domain of the present utility model is not limited thereto, and any change of expecting without creative work or replacement, all should be encompassed within protection domain of the present utility model.Therefore, the protection domain that protection domain of the present utility model should limit with claims is as the criterion.
Claims (4)
1. the turbine fan blade rotor of a turbine air compressor, it is characterized in that: comprise fan blade rotor body, the top of described fan blade rotor body is provided with centrifugal blade, the shaft core position place at the top of described fan blade rotor body is provided with connecting end, described centrifugal blade annular is arranged on the outside of described connecting end, the gap of a 1mm-2mm is formed between the outer surface of described centrifugal blade and described connecting end, the outer ring of described fan blade rotor body is provided with axial blade, the bottom of described fan blade rotor body is provided with swirl vane, the shaft core position place of the bottom of described fan blade rotor body is provided with the first connecting end, described swirl vane annular is arranged on the outside of described first connecting end.
2. the turbine fan blade rotor of turbine air compressor according to claim 1, is characterized in that: described centrifugal blade and described fan blade rotor body are integral type structure.
3. the turbine fan blade rotor of turbine air compressor according to claim 1, is characterized in that: described axial blade and described fan blade rotor body are integral type structure.
4. the turbine fan blade rotor of turbine air compressor according to claim 1, is characterized in that: described swirl vane and described fan blade rotor body are integral type structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520823737.3U CN205089679U (en) | 2015-10-23 | 2015-10-23 | Turbine fan blade rotor that turbine air compressor machine was used |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520823737.3U CN205089679U (en) | 2015-10-23 | 2015-10-23 | Turbine fan blade rotor that turbine air compressor machine was used |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205089679U true CN205089679U (en) | 2016-03-16 |
Family
ID=55480371
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520823737.3U Expired - Fee Related CN205089679U (en) | 2015-10-23 | 2015-10-23 | Turbine fan blade rotor that turbine air compressor machine was used |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205089679U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018103342A1 (en) * | 2016-12-05 | 2018-06-14 | 珠海格力电器股份有限公司 | Fan blade with circumferential air output and fan having same |
| CN108999792A (en) * | 2018-07-13 | 2018-12-14 | 吴艮华 | A kind of impeller air pump |
-
2015
- 2015-10-23 CN CN201520823737.3U patent/CN205089679U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018103342A1 (en) * | 2016-12-05 | 2018-06-14 | 珠海格力电器股份有限公司 | Fan blade with circumferential air output and fan having same |
| CN108999792A (en) * | 2018-07-13 | 2018-12-14 | 吴艮华 | A kind of impeller air pump |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205089679U (en) | Turbine fan blade rotor that turbine air compressor machine was used | |
| CN204724969U (en) | The Linear cut wheel stand of tape guide ring | |
| CN205013367U (en) | Impeller of centrifugal pump | |
| CN203114726U (en) | Grooving structure used for impeller | |
| CN103307253A (en) | Improved gear | |
| CN203438413U (en) | Mixer rotor | |
| CN105711833B (en) | Helicopter main blade | |
| CN206092674U (en) | Shaft | |
| CN204646780U (en) | A kind of front fan of motor | |
| CN202914387U (en) | Centrifugal impeller | |
| CN202914383U (en) | Centrifuge impeller | |
| CN203258015U (en) | Intermediate shaft gear forging blank | |
| CN203906362U (en) | Compound type shaft sleeve at top of electric pump | |
| CN104728159A (en) | Auxiliary vortex wheel of centrifugal compressor | |
| CN203796611U (en) | Impeller | |
| CN204591775U (en) | A kind of blade wheel structure | |
| CN204628071U (en) | A kind of blower fan structure-improved | |
| CN203978915U (en) | A kind of peripheral pump impeller | |
| CN203926110U (en) | A kind of coupling guard | |
| CN203730394U (en) | Impeller of vortex pump | |
| CN203942347U (en) | A kind of rotor | |
| CN203747604U (en) | Three-section rotary shaft structure of high-speed permanent magnet synchronous motor | |
| CN203292569U (en) | Ductile end mill | |
| CN202949334U (en) | Low-power three-phase asynchronous motor rotor | |
| CN104074555B (en) | Power blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160316 Termination date: 20161023 |