CN208982350U - Blade wheel structure for compressor - Google Patents
Blade wheel structure for compressor Download PDFInfo
- Publication number
- CN208982350U CN208982350U CN201820635416.4U CN201820635416U CN208982350U CN 208982350 U CN208982350 U CN 208982350U CN 201820635416 U CN201820635416 U CN 201820635416U CN 208982350 U CN208982350 U CN 208982350U
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- CN
- China
- Prior art keywords
- blade
- compressor
- wheel structure
- impeller
- diameter
- 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
The utility model relates to a kind of blade wheel structures for compressor, including shaft, impeller, wherein impeller includes multiple blade groups, multiple blade groups are circumferentially uniformly distributed, each blade group includes three blades, three blades are respectively the first blade, the second blade, third blade, and the first blade, the second blade, the leading-edge radius of third blade is different, thickness is different.The effect that the blade wheel structure can play water conservancy diversion, increase pressure, reduces blade side turbulent flow, improve the ride comfort of air-flow at blade exit, improves impeller performance.
Description
Technical field
The utility model relates to field of fluid machinery more particularly to a kind of for compressor or the blade wheel structure of air blower.
Background technique
Compressor or air blower are the fluid mechanical devices that fluid energy is converted mechanical energy into using gas as working media,
Blade wheel structure plays a crucial role efficiency, the performance of whole device.But to the raising of properties of product in existing product
There are also very big rooms for improvement.
Utility model content
The purpose of the utility model is to overcome the deficiencies in the prior art, provide a kind of impeller knot for compressor
Structure, the blade wheel structure for being used for compressor can play water conservancy diversion, increase pressure, reduce blade side turbulent flow, improve blade exit
The effect for locating the ride comfort of air-flow, improves impeller performance.
To achieve the goals above, the technical solution adopted in the utility model are as follows:
A kind of blade wheel structure for compressor, including shaft, impeller, shaft include first diameter section (, second diameter
Section, third diameter segment, their diameter is sequentially reduced, and impeller includes blade, shroud, hub disk, wheel hub, blade have leading edge, after
Edge；Second diameter section is optical axis section, and the unthreaded hole section location fit with wheel hub, third diameter segment is in external screw thread, with wheel hub
The cooperation of screw thread hole section, arc nut interior have internal thread hole, cooperate with the external screw thread of third diameter segment, impeller, arc spiral shell
Mother is installed in shaft, and rotation is driven by motor in shaft, it is characterised in that: impeller includes multiple blade groups, multiple blade group edges
Even circumferential distribution, each blade group include three blades, and three blades are respectively the first blade, the second blade, third
Blade, the first blade, the second blade, the leading-edge radius of third blade is different, thickness is different.
Further, in radial directions, the first blade, the second blade, third blade leading-edge radius be sequentially increased.
Further, the first blade, the second blade, third blade thickness H1, H2, H3 be sequentially reduced.
Further, each blade has multiple grooves in one side face, and multiple grooves are axially aligned.
Further, in radial directions, the initial position radius of groove is the 0.85-0.95 of blade outer edge radius, eventually
Stop bit is set to blade outer rim.
Further, the depth of groove is gradually increased from radially inner side to radial outside, i.e. depth of groove at blade outer rim
The original position depth of maximum, groove is minimum.
Further, the joint of the segmental arc of the flat segments and shroud of shroud is the first blade inlet edge location point.
The blade wheel structure for being used for compressor can play water conservancy diversion, increase pressure, reduce blade side turbulent flow, improve blade
The effect of the ride comfort of exit air-flow, improves impeller performance.
Detailed description of the invention
Fig. 1 is the utility model rotor structure figure；
Fig. 2 is the utility model blade construction figure；
Fig. 3 is the utility model blade construction figure, is the A-A view of Fig. 2.
In figure: shaft 1, first diameter section 11, second diameter section 12, third diameter segment 13, blade 2, leading edge 21, rear
22, the first blade 23, the second blade 24, third blade 25, groove 26, shroud 3, shroud import ring 31, hub disk 4, hub disk sealing
Ring 41, wheel hub 5, angled straight lines section 51, segmental arc 52, arc nut 6.
Specific embodiment
The utility model provides a kind of blade wheel structure for compressor, with reference to the accompanying drawing to the utility model make into
One step is described in detail.
Referring to attached drawing 1-3: the blade wheel structure for being used for compressor includes shaft 1, first diameter section 11, second diameter section
12, third diameter segment 13, blade 2, leading edge 21, rear 22, the first blade 23, the second blade 24, third blade 25, groove 26,
Shroud 3, shroud import ring 31, hub disk 4, hub disk sealing ring 41, wheel hub 5, angled straight lines section 51, segmental arc 52, arc nut 6.
Rotor includes shaft 1, impeller, and shaft 1 successively includes first diameter section 11, second diameter section 12, third diameter segment
13, their diameter is sequentially reduced；Second diameter section 12 is optical axis section, the unthreaded hole section location fit with wheel hub 5, third diameter segment
13 have external screw thread, cooperate with the internal screw thread hole section of wheel hub 5；It is curved portion outside arc nut 6, inside has internal thread hole,
Cooperate with the external screw thread of third diameter segment 13.Impeller, arc nut 6 are installed in shaft 1, and rotation is driven by motor in shaft 1.
Impeller includes multiple blade groups, and multiple blade groups are circumferentially uniformly distributed, and each blade group includes three blades 2,
Blade 2 has leading edge 21, rear 22, which is respectively the first blade 23, the second blade 24, third blade 25；In diameter
To on direction, the first blade 23, the second blade 24, third blade 25 the radius of leading edge 21 be sequentially increased, the first blade 23,
Two blades 24, third blade 25 thickness H1, H2, H3 be sequentially reduced, H2=(0.7-0.8) H1, preferably 0.75H1, H3=(0.45-
0.55) H1, preferably 0.5H1；First blade 23, the second blade 24, the outer diameter of third blade 25 are identical；Three blades 2 are all torsion
Curved three dimendional blade.Its effect that can be played water conservancy diversion, reduce blade two sides turbulent flow improves impeller performance.
Each blade 2 has multiple grooves 26 in its pressure face, and multiple grooves 26 are axially aligned；In radial directions,
The initial position radius of groove 26 be 2 outer rim of blade, 22 radius 0.85-0.95, preferably 0.9, final position be 2 outer rim of blade
22；The depth of the groove 26 of pressure face is gradually increased from radially inner side to radial outside, i.e., 26 depth of groove at blade outer rim 22
26 depth of original position groove of maximum, groove 26 is minimum.It, which can be played, increases pressure, improves air-flow at blade exit
Ride comfort.
The shroud import ring 31 of shroud 3 is flat segments, the junction of flat segments and the segmental arc of shroud 3 in the axial direction
For 2 leading edge of blade, 21 location point.The outside of hub disk 4 is equipped with hub disk sealing ring 41, hub disk sealing ring 41 and compressor or air blower
Shell backboard sealing structure cooperation.The outside of wheel hub 5 contacted with blade 2 includes angled straight lines section 51, segmental arc 52, and
One blade, 23 leading edge 21 is in angled straight lines section 51, and the second blade 24,25 leading edge of third blade are in segmental arc 52.
The blade wheel structure for being used for compressor can play water conservancy diversion, increase pressure, reduce blade side turbulent flow, improve blade
The effect of the ride comfort of exit air-flow, improves impeller performance.
Above embodiment is the explanation to the utility model, is not the restriction to the utility model, and any pair of sheet is practical
Structure after novel simple transformation belongs to the protection scope of the utility model.
Claims (5)
1. being used for the blade wheel structure of compressor, including shaft (1), impeller, shaft include first diameter section (11), second diameter section
(12), third diameter segment (13), their diameter are sequentially reduced, and impeller includes blade (2), shroud (3), hub disk (4), wheel hub
(5), the blade has leading edge (21), rear (22)；Second diameter section (12) is optical axis section, the unthreaded hole Duan Ding with wheel hub (5)
Position cooperation, third diameter segment (13) have external screw thread, cooperate with the internal screw thread hole section of wheel hub (5), have inside arc nut (6)
Internal thread hole cooperates with the external screw thread of third diameter segment (13), and impeller, arc nut are installed in shaft, and shaft is by motor
Driving rotation, it is characterised in that: impeller includes multiple blade groups, and multiple blade groups are circumferentially uniformly distributed, each blade group packet
Including three blades (2), three blades (2) are respectively the first blade (23), the second blade (24), third blade (25), and
One blade (23), the second blade (24), the leading-edge radius of third blade (25) is different, thickness is different.
2. being used for the blade wheel structure of compressor as described in claim 1, it is characterised in that: in radial directions, the first blade
(23), the second blade (24), third blade (25) leading-edge radius be sequentially increased.
3. being used for the blade wheel structure of compressor as claimed in claim 2, it is characterised in that: the first blade (23), the second blade
(24), thickness H1, H2, H3 of third blade (25) are sequentially reduced.
4. being used for the blade wheel structure of compressor as described in claim 1, it is characterised in that: each blade (2) is in one side mask
Have multiple grooves (26), multiple grooves (26) are axially aligned.
5. being used for the blade wheel structure of compressor as claimed in claim 4, it is characterised in that: in radial directions, groove (26)
Initial position radius is the 0.85-0.95 of blade outer edge radius, and final position is blade outer rim.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820635416.4U CN208982350U (en) | 2018-05-01 | 2018-05-01 | Blade wheel structure for compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820635416.4U CN208982350U (en) | 2018-05-01 | 2018-05-01 | Blade wheel structure for compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208982350U true CN208982350U (en) | 2019-06-14 |
Family
ID=66778563
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820635416.4U Expired - Fee Related CN208982350U (en) | 2018-05-01 | 2018-05-01 | Blade wheel structure for compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208982350U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111828375A (en) * | 2020-06-30 | 2020-10-27 | 中国航发南方工业有限公司 | Split-flow centrifugal impeller and aircraft engine with same |
-
2018
- 2018-05-01 CN CN201820635416.4U patent/CN208982350U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111828375A (en) * | 2020-06-30 | 2020-10-27 | 中国航发南方工业有限公司 | Split-flow centrifugal impeller and aircraft engine with same |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190614 Termination date: 20210501 |