CN106194818A - Centrifugal-flow compressor novel pressure side oil-gas seal structure - Google Patents
Centrifugal-flow compressor novel pressure side oil-gas seal structure Download PDFInfo
- Publication number
- CN106194818A CN106194818A CN201610768850.5A CN201610768850A CN106194818A CN 106194818 A CN106194818 A CN 106194818A CN 201610768850 A CN201610768850 A CN 201610768850A CN 106194818 A CN106194818 A CN 106194818A
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- Prior art keywords
- oil
- sealing
- centrifugal
- pressure side
- flow compressor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of centrifugal-flow compressor novel pressure side oil-gas seal structure, oil-sealing sleeve is loop configuration, oil-sealing sleeve inner headed face is fixed with impeller annular afterbody periphery interference fit, oil-sealing sleeve inner headed face afterbody is provided with seam one, axially being positioned with impeller annular afterbody by seam one, impeller is connected with spindle thread, by seam two radially location, disc gap is enclosed within main shaft, sealing gland circle and oil-sealing sleeve matched in clearance.The centrifugal-flow compressor novel pressure side oil-gas seal structure that the present invention provides, it is ensured that quality of fit, enhances the concentricity of impeller and main shaft, enhances rotor stability；Strengthen drawing oil effect, effectively prevent lubricating oil from penetrating into oil-sealing sleeve and sealing gland ring gap；Ensure the axiality with rotor-support-foundation system；Define oil sealing and sealing gland, prevent pressure-air at blade back from entering oil back chamber.
Description
Technical field
The present invention relates to a kind of centrifugal-flow compressor new type rotor structure, particularly relate to a kind of centrifugal-flow compressor Novel pressure
End oil-gas seal structure.
Background technology
The structure design of centrifugal-flow compressor oil gas envelope not only has influence on the oil gas envelope ability of compressor, is more related to rotor
Stability and the efficiency of compressor.At present, a kind of common structure is oil-sealing sleeve matched in clearance on main shaft, revolves with main shaft
Turn, with pressure side cover plate or sealing gland circle endoporus matched in clearance, be rotated up to oil sealing purpose by left-hand thread.Impeller back sealing gland tooth with
Sealing gland circle sealing gland backlash coordinates, and sealing gland circle afterbody (nearly disc end) is one annular groove.Operationally, disc is big for this structure
Amount is when getting rid of oil, and sealing gland circle monocycle groove can not draw oil to oil back chamber, and partly oil can ooze to oil-sealing sleeve left-hand thread, strengthens oil-sealing sleeve and bears
Lotus.Along with improving constantly of compressor operating mode, at blade back, gas pressure promotes, and single-layer back screw-type oil-sealing sleeve oil sealing ability is progressively
Decline, can not prevent that blade back gases at high pressure are counter to be filled to oil back chamber simultaneously.Design a kind of novel centrifugal-flow compressor oil gas sealed knot
Structure avoids disadvantage mentioned above to be the technological difficulties urgently broken through present stage.
Summary of the invention
The present invention be directed to the deficiency that prior art exists, propose the centrifugal-flow compressor leaf of a kind of non-stop layer through-hole structure
The Novel oil gas seal structure of wheel.
This centrifugal-flow compressor novel pressure side oil-gas seal structure, oil-sealing sleeve is loop configuration, oil-sealing sleeve inner headed face and leaf
Wheel annular afterbody periphery interference fit is fixed, and oil-sealing sleeve inner headed face afterbody is provided with seam one, by seam one and impeller annular
Afterbody axially positions, and impeller is connected with spindle thread, and by seam two radially location, disc gap is enclosed within main shaft, sealing gland
Circle and oil-sealing sleeve matched in clearance.
Described oil-sealing sleeve is provided with seal groove and seals tooth.
Described seal groove is trapezoidal left-hand thread seal groove, and described sealing tooth is taper sealing tooth.
Described sealing gland circle afterbody is double groove structures.
Described sealing gland circle coordinates with the sealing backlash of oil-sealing sleeve.
Described sealing gland circle seals the tooth place of cooperation with oil-sealing sleeve and is provided with oil sealing tooth.
Described oil sealing tooth is tapering oil sealing tooth.
The centrifugal-flow compressor novel pressure side oil-gas seal structure that the present invention provides, it is ensured that quality of fit, enhances impeller
With the concentricity of main shaft, enhance rotor stability；Strengthen drawing oil effect, effectively prevent lubricating oil from penetrating between oil-sealing sleeve and sealing gland circle
Gap；Ensure the axiality with rotor-support-foundation system；Define oil sealing and sealing gland, prevent pressure-air at blade back from entering oil back chamber.
Accompanying drawing explanation
Fig. 1 is the cross-sectional view of the present invention.
Reference is as follows: 1-oil-sealing sleeve, 2-impeller, 3-seam one, 4-main shaft, 5-disc, and 6-sealing gland circle, 11-is close
Envelope tooth, 12-seal groove, the double groove structure of 61-, 62-oil sealing tooth.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
The a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under not making creative work premise, broadly falls into the scope of protection of the invention.
Fig. 1 is the cross-sectional view of centrifugal-flow compressor of the present invention novel pressure side oil-gas seal structure.
This centrifugal-flow compressor novel pressure side oil-gas seal structure, oil-sealing sleeve 1 is loop configuration, oil-sealing sleeve 1 inner headed face with
Impeller 2 annular afterbody periphery interference fit is fixed, and oil-sealing sleeve 1 inner headed face afterbody is provided with seam 1, by seam 1 and leaf
Wheel 2 annular afterbody axially positions, and impeller 2 is threadeded with main shaft 4, and by seam two radially location, disc 5 gap is enclosed within master
On axle 4, sealing gland circle 6 and oil-sealing sleeve 1 matched in clearance.Oil-sealing sleeve 1 is provided with seal groove 12 and seals tooth 11.Seal groove 12 is trapezoidal
Left-hand thread seal groove, sealing tooth 11 is taper sealing tooth.Sealing gland circle 6 afterbody is double groove structures 61.Sealing gland circle 6 and oil-sealing sleeve 1
Sealing tooth 11 matched in clearance.Sealing gland circle 6 seals tooth 11 place of cooperation and is provided with oil sealing tooth 62 with oil-sealing sleeve 1.Oil sealing tooth 62 is tapering
Oil sealing tooth.
A kind of centrifugal-flow compressor novel pressure side oil-gas seal structure, including: impeller 2 (for centrifugal-flow compressor impeller) and master
Axle 4, also includes oil-sealing sleeve 1, sealing gland circle 6, disc 5；Oil-sealing sleeve 1 with trapezoidal left-hand thread seal groove and taper sealing tooth, and
Fix with impeller 2 interference fit, positioned by seam 1；Impeller 2 uses with main shaft 4 threadeds, the most fixed by seam two
Position.Disc 5 gap is placed on main shaft 4, rotates with main shaft 4.Sealing gland circle 6 afterbody is with dicyclo groove structure 61, with oil-sealing sleeve 1
Also oil sealing tooth 62 is had at tapering tooth cooperation.
Use the present invention of technique scheme, impeller 2 be directly threaded connection with main shaft 4 (when rotor operates, screw thread
Connect by screw-down torque), it is ensured that quality of fit, enhance the concentricity of impeller 2 and main shaft 4, enhance rotor stability.Gas
Seal 6 afterbody is double groove structures 61, strengthens drawing oil effect, effectively prevents lubricating oil from penetrating into oil-sealing sleeve 1 and sealing gland circle 6 gap.Oil
Big envelope 1 loop configuration, inner headed face and impeller 2 annular afterbody periphery interference fit, it is ensured that with the axiality of rotor-support-foundation system；Inner circle
Face afterbody has seam 1, axially positions with the annular afterbody at impeller 2 back side.Oil-sealing sleeve 1 is close with left-hand thread seal groove and tapering
Envelope tooth, left-hand thread is first oil seal system, when rotated, is isolated by lubricating oil.The gentle seal of taper sealing tooth 6 of oil-sealing sleeve 1
Tapering oil sealing tooth be combined as second oil sealing, oil-sealing sleeve 1 rotate in, the lubricating oil come at left-hand thread can be got rid of back, play
Oil sealing effect.The most also form sealing gland simultaneously, prevent pressure-air at blade back from entering oil back chamber.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit；Although
With reference to previous embodiment, the present invention is described in detail, it will be understood by those within the art that: it still may be used
So that the technical scheme described in foregoing embodiments to be modified, or wherein portion of techniques feature is carried out equivalent；
And these amendment or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (7)
1. a centrifugal-flow compressor novel pressure side oil-gas seal structure, it is characterised in that: oil-sealing sleeve is loop configuration, in oil-sealing sleeve
Disc is fixed with impeller annular afterbody periphery interference fit, and oil-sealing sleeve inner headed face afterbody is provided with seam one, by seam one with
Impeller annular afterbody axially positions, and impeller is connected with spindle thread, and by seam two radially location, disc gap is enclosed within main shaft
On, sealing gland circle and oil-sealing sleeve matched in clearance.
Centrifugal-flow compressor the most according to claim 1 novel pressure side oil-gas seal structure, it is characterised in that: described oil sealing
Put and be provided with seal groove and seal tooth.
Centrifugal-flow compressor the most according to claim 2 novel pressure side oil-gas seal structure, it is characterised in that: described sealing
Groove is trapezoidal left-hand thread seal groove, and described sealing tooth is taper sealing tooth.
Centrifugal-flow compressor the most according to claim 1 novel pressure side oil-gas seal structure, it is characterised in that: described sealing gland
Circle afterbody is double groove structures.
Centrifugal-flow compressor the most according to claim 2 novel pressure side oil-gas seal structure, it is characterised in that: described sealing gland
Circle coordinates with the sealing backlash of oil-sealing sleeve.
Centrifugal-flow compressor the most according to claim 4 novel pressure side oil-gas seal structure, it is characterised in that: described sealing gland
Enclose and be provided with oil sealing tooth with the oil-sealing sleeve sealing tooth place of cooperation.
Centrifugal-flow compressor the most according to claim 6 novel pressure side oil-gas seal structure, it is characterised in that: described oil sealing
Tooth is tapering oil sealing tooth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610768850.5A CN106194818A (en) | 2016-08-31 | 2016-08-31 | Centrifugal-flow compressor novel pressure side oil-gas seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610768850.5A CN106194818A (en) | 2016-08-31 | 2016-08-31 | Centrifugal-flow compressor novel pressure side oil-gas seal structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106194818A true CN106194818A (en) | 2016-12-07 |
Family
ID=58088607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610768850.5A Pending CN106194818A (en) | 2016-08-31 | 2016-08-31 | Centrifugal-flow compressor novel pressure side oil-gas seal structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106194818A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107588039A (en) * | 2017-10-26 | 2018-01-16 | 凤城市时代龙增压器制造有限公司 | A kind of sealing structure for generator terminal of being calmed the anger for ball bearing turbine supercharger |
| CN108930665A (en) * | 2018-07-17 | 2018-12-04 | 赵浩浩 | It is a kind of for compressor or the blade wheel structure of air blower |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0920592B1 (en) * | 1996-08-23 | 2003-12-10 | Eddy Pump Corporation | Pump with a shaft sealing system |
| CN2769561Y (en) * | 2004-12-29 | 2006-04-05 | 中国船舶重工集团公司第七一一研究所 | Single-stage high-speed centrifugal compressor |
| CN101975185A (en) * | 2010-10-21 | 2011-02-16 | 湖南天雁机械有限责任公司 | Compressor seal structure of small turbocharger |
| CN203685664U (en) * | 2014-01-22 | 2014-07-02 | 重庆江增机械有限公司 | Turbocharger compressor combination sealing structure |
| CN104405683A (en) * | 2014-12-12 | 2015-03-11 | 中国北车集团大连机车研究所有限公司 | Centrifugal-flow compressor rotor structure |
| CN104500440A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Low-cycle-fatigue-resistant turbocharger air compressor impeller |
-
2016
- 2016-08-31 CN CN201610768850.5A patent/CN106194818A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0920592B1 (en) * | 1996-08-23 | 2003-12-10 | Eddy Pump Corporation | Pump with a shaft sealing system |
| CN2769561Y (en) * | 2004-12-29 | 2006-04-05 | 中国船舶重工集团公司第七一一研究所 | Single-stage high-speed centrifugal compressor |
| CN101975185A (en) * | 2010-10-21 | 2011-02-16 | 湖南天雁机械有限责任公司 | Compressor seal structure of small turbocharger |
| CN203685664U (en) * | 2014-01-22 | 2014-07-02 | 重庆江增机械有限公司 | Turbocharger compressor combination sealing structure |
| CN104405683A (en) * | 2014-12-12 | 2015-03-11 | 中国北车集团大连机车研究所有限公司 | Centrifugal-flow compressor rotor structure |
| CN104500440A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Low-cycle-fatigue-resistant turbocharger air compressor impeller |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107588039A (en) * | 2017-10-26 | 2018-01-16 | 凤城市时代龙增压器制造有限公司 | A kind of sealing structure for generator terminal of being calmed the anger for ball bearing turbine supercharger |
| CN107588039B (en) * | 2017-10-26 | 2024-03-05 | 凤城市时代龙增压器制造有限公司 | Sealing structure for compressor end of ball bearing turbocharger |
| CN108930665A (en) * | 2018-07-17 | 2018-12-04 | 赵浩浩 | It is a kind of for compressor or the blade wheel structure of air blower |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161207 |