CN103967827A - Double-stage or multi-stage fan axial force balance device - Google Patents
Double-stage or multi-stage fan axial force balance device Download PDFInfo
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- CN103967827A CN103967827A CN201310396725.2A CN201310396725A CN103967827A CN 103967827 A CN103967827 A CN 103967827A CN 201310396725 A CN201310396725 A CN 201310396725A CN 103967827 A CN103967827 A CN 103967827A
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Abstract
The invention relates to the field of fans, particularly relates to a bearing force balance structure, and discloses a double-stage or multi-stage fan axial force balance device which comprises a preceding-stage seal, a backward-stage seal, a preceding-stage impeller, a backward-stage impeller and a housing case. The preceding-stage seal is arrange between a wind outlet surface of the preceding-stage impeller and the housing case, the backward-stage seal is arranged between a windward surface of the backward-stage impeller and the housing case, airflow which is blown out of the preceding-stage impeller flows to the backward-stage impeller via a guide vane in a guided manner, the preceding-stage seal and the backward-stage seal form a dynamic and static seal pair, and the distance from the axis of the preceding-stage seal to the axis of the preceding-stage impeller is farther than the distance from the axis of the backward-stage seal to the axis of the backward-stage impeller. The double-stage or multi-stage fan axial force balance device has the advantages that a cavity between the preceding-stage impeller and the backward-stage impeller is hermetically divided by a sealing device, so that pressures which act on the side surfaces of the backward-stage impeller are larger than pressures which act on the side surfaces of the preceding-stage impeller, resultant force which is opposite to axial thrust can be generated, a part of the axial thrust can be offset, purposes can be achieved, axial force can be reduced, strength required by bearings can be lowered, and the service lives of the bearings can be prolonged.
Description
Technical field
The present invention relates to blower fan field, relate in particular to a kind of trunnion shaft load structure.
Background technique
, in twin-stage or multistage blower fan, between two adjacent impellers, not necessarily have seal arrangement now, even if having, its effect is only also the air-flow between 2 cavitys of isolation.In fact, due to the supercharging of blower fan to air-flow, self can be subject to an axial reaction force, therefore need to use thrust-bearing.Because multistage blower fan end thrust is large, high to bearing requirement, cause bearing short working life, cost is high, blower fan structure complexity.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of twin-stage or multistage blower fan axial thrust balancing devices, cavity before and after cutting apart with seal arrangement sealing between level impeller, make to act on pressure in the pressure ratio prime of rear class impeller side larger, just can produce one with end thrust reverse make a concerted effort, offset a part of end thrust, reduce the required intensity of bearing, improved bearing life.
The present invention is achieved in that a kind of twin-stage or multistage blower fan axial thrust balancing devices, comprise prime sealing, final-stage seal, prime impeller, rear class impeller and casing, described prime sealing is arranged between the outlet air surface and casing of prime impeller, described final-stage seal is arranged between the windward side and casing of rear class impeller, the air-flow that described prime impeller blows out is by the stator rear class impeller that leads, prime sealing is static and dynamic sealing pair with final-stage seal, and the distance of described prime sealing and prime impeller axis is greater than the distance of final-stage seal and rear class impeller axis.
Described static and dynamic sealing pair is carbocyclic ring, dry gas seals, honeycomb seal, labyrinth seal or brush seal.
Described prime impeller and rear class impeller are on same axis.
Twin-stage of the present invention or multistage blower fan axial thrust balancing devices are cut apart the cavity between the level impeller of front and back with seal arrangement sealing, due to the supercharging of prime impeller, axial force is to point to prime impeller from rear class impeller, it is larger that the present invention makes to act on pressure in the pressure ratio prime of rear class impeller side, just can produce one with reverse the making a concerted effort of end thrust, offset a part of end thrust, just can realize object, reduce axial force, reduce the required intensity of bearing, improved bearing life.
Brief description of the drawings
Fig. 1 is the structural representation of twin-stage of the present invention or multistage blower fan axial thrust balancing devices.
In figure: 1 prime sealing, 2 final-stage seals, 3 prime impellers, 4 rear class impellers, 5 casings, 6 stators.
Embodiment
Below in conjunction with specific embodiment, further set forth the present invention.Should be understood that these embodiments are only not used in and limit the scope of the invention for the present invention is described.In addition should be understood that those skilled in the art can make various changes or modifications the present invention after having read the content of the present invention's statement, these equivalent form of values fall within the application's appended claims limited range equally.
Embodiment 1
As shown in Figure 1, a kind of twin-stage or multistage blower fan axial thrust balancing devices, comprise prime sealing 1, final-stage seal 2, prime impeller 3, rear class impeller 4 and casing 5, described prime impeller 3 and rear class impeller 4 are on same axis, described prime sealing 1 is arranged between the outlet air surface and casing 5 of prime impeller 3, described final-stage seal 2 is arranged between the windward side and casing 5 of rear class impeller 4, the air-flow that described prime impeller 3 blows out is by the stator 6 rear class impeller 4 that leads, prime sealing 1 is static and dynamic sealing pair with final-stage seal 2, the distance of described prime sealing 1 and prime impeller 3 axis is greater than the distance of final-stage seal 2 and rear class impeller 4 axis.
In the present embodiment, described static and dynamic sealing pair is carbocyclic ring, dry gas seals, honeycomb seal, labyrinth seal or brush seal.
The present invention is arranged in bipolar or multistage blower fan.Each group movable vane and quiet stator are called one-level, and one group of static and dynamic sealing pair is set between adjacent two-stage.
Air-flow is by prime impeller 3, rear class impeller 4, be pressurized the rear generation end thrust F contrary with airflow direction, S1 is the area on prime impeller 3 air-out sides, and P1 is the pressure acting on S1, acts on the pressure F1=P1 × S1 on prime impeller 3 air-out sides; S2 is the area of rear class impeller 4 air intake sides, P2 is the pressure acting on S2, act on the pressure F2=P2 × S2 on rear class impeller 4 air intake sides, the impact of boosting due to stator 6, so P1<P2, by prime sealing 1 is set, final-stage seal 2 makes S1<S2, F1<F2.The resultant direction of F1, F2 is contrary with end thrust F, thereby reaches balancing axial thrust, reduce the number of the object of bearing, extends bearing working life.
Claims (3)
1. a twin-stage or multistage blower fan axial thrust balancing devices, comprise prime sealing (1), final-stage seal (2), prime impeller (3), rear class impeller (4) and casing (5), described prime sealing (1) is arranged between the outlet air surface and casing (5) of prime impeller (3), described final-stage seal (2) is arranged between the windward side and casing (5) of rear class impeller (4), the air-flow that described prime impeller (3) blows out is by stator (6) guiding rear class impeller (4), prime sealing (1) is static and dynamic sealing pair with final-stage seal (2), it is characterized in that: the distance of described prime sealing (1) and prime impeller (3) axis is greater than the distance of final-stage seal (2) and rear class impeller (4) axis.
2. twin-stage as claimed in claim 1 or multistage blower fan axial thrust balancing devices, is characterized in that: described static and dynamic sealing is secondary is carbocyclic ring, dry gas seals, honeycomb seal, labyrinth seal or brush seal.
3. twin-stage as claimed in claim 1 or multistage blower fan axial thrust balancing devices, is characterized in that: described prime impeller (3) and rear class impeller (4) are on same axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310396725.2A CN103967827B (en) | 2013-09-04 | 2013-09-04 | Twin-stage or multistage blower fan axial thrust balancing devices |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310396725.2A CN103967827B (en) | 2013-09-04 | 2013-09-04 | Twin-stage or multistage blower fan axial thrust balancing devices |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103967827A true CN103967827A (en) | 2014-08-06 |
| CN103967827B CN103967827B (en) | 2016-01-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310396725.2A Expired - Fee Related CN103967827B (en) | 2013-09-04 | 2013-09-04 | Twin-stage or multistage blower fan axial thrust balancing devices |
Country Status (1)
| Country | Link |
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| CN (1) | CN103967827B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112431781A (en) * | 2020-11-24 | 2021-03-02 | 稳力(广东)科技有限公司 | Axial resultant force adjusting method of coaxial two-stage centrifugal or mixed-flow air compressor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5531564A (en) * | 1994-02-11 | 1996-07-02 | A. Ahlstrom Corporation | Centrifugal pump |
| CN201265547Y (en) * | 2008-09-23 | 2009-07-01 | 长沙佳能通用泵业有限公司 | Balancing type single-suction horizontal multiple-stage centrifugal pump |
| CN201306289Y (en) * | 2008-11-07 | 2009-09-09 | 李永胜 | High-lift multistage centrifugal pump |
| CN102242736A (en) * | 2010-05-11 | 2011-11-16 | 诺沃皮尼奥内有限公司 | Balance drum configuration for compressor rotors |
| CN202047989U (en) * | 2010-12-29 | 2011-11-23 | 荆锁祥 | Sectional oppositely-mounted double-volute abrasion-resistant multistage pump for mine |
| WO2012061011A2 (en) * | 2010-10-25 | 2012-05-10 | Dresser-Rand Company | System and apparatus for reducing thrust forces acting on a compressor rotor |
| CN203548307U (en) * | 2013-09-04 | 2014-04-16 | 上海鼓风机厂有限公司 | Axial force balancing device of dual-stage or multistage fan |
-
2013
- 2013-09-04 CN CN201310396725.2A patent/CN103967827B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5531564A (en) * | 1994-02-11 | 1996-07-02 | A. Ahlstrom Corporation | Centrifugal pump |
| CN201265547Y (en) * | 2008-09-23 | 2009-07-01 | 长沙佳能通用泵业有限公司 | Balancing type single-suction horizontal multiple-stage centrifugal pump |
| CN201306289Y (en) * | 2008-11-07 | 2009-09-09 | 李永胜 | High-lift multistage centrifugal pump |
| CN102242736A (en) * | 2010-05-11 | 2011-11-16 | 诺沃皮尼奥内有限公司 | Balance drum configuration for compressor rotors |
| WO2012061011A2 (en) * | 2010-10-25 | 2012-05-10 | Dresser-Rand Company | System and apparatus for reducing thrust forces acting on a compressor rotor |
| CN202047989U (en) * | 2010-12-29 | 2011-11-23 | 荆锁祥 | Sectional oppositely-mounted double-volute abrasion-resistant multistage pump for mine |
| CN203548307U (en) * | 2013-09-04 | 2014-04-16 | 上海鼓风机厂有限公司 | Axial force balancing device of dual-stage or multistage fan |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112431781A (en) * | 2020-11-24 | 2021-03-02 | 稳力(广东)科技有限公司 | Axial resultant force adjusting method of coaxial two-stage centrifugal or mixed-flow air compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103967827B (en) | 2016-01-20 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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: 20160120 Termination date: 20190904 |