CN101949393A - Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor - Google Patents

Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor Download PDF

Info

Publication number
CN101949393A
CN101949393A CN 201010508522 CN201010508522A CN101949393A CN 101949393 A CN101949393 A CN 101949393A CN 201010508522 CN201010508522 CN 201010508522 CN 201010508522 A CN201010508522 A CN 201010508522A CN 101949393 A CN101949393 A CN 101949393A
Authority
CN
China
Prior art keywords
impeller
multistage centrifugal
guide ring
return channel
centrifugal blower
Prior art date
Application number
CN 201010508522
Other languages
Chinese (zh)
Inventor
于跃平
陈启明
胡四兵
钱勇
黄文俊
王鹏亮
董帆
Original Assignee
合肥通用机械研究院
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 合肥通用机械研究院 filed Critical 合肥通用机械研究院
Priority to CN 201010508522 priority Critical patent/CN101949393A/en
Publication of CN101949393A publication Critical patent/CN101949393A/en

Links

Abstract

The invention discloses a multistage centrifugal blower or an impeller inlet flowing guide structure of the multistage centrifugal compressor. The multistage centrifugal blower comprises a flowing returning device, an impeller, a shaft sleeve, a cover plate of the flowing returning device, an impeller wheel cover, a wheel disc, a vane inlet part of the impeller and a vane outlet part of the flowing returning device. The multistage centrifugal blower is characterized in that a flowing guide ring is arranged in an air current channel which is formed by the flowing returning device, the impeller and the shaft sleeve and enables the air current to flow from the last stage to the next stage. The invention can improve the air intake condition of the impeller of the traditional multistage centrifugal blower or the centrifugal compressor, inhibit gas separation at an air intake turning part of the wheel cover, reduce secondary flowing loss and improve pneumatic efficiency and operation stability of the multistage centrifugal blower and the centrifugal compressor.

Description

The impeller inlet flow guide structure of multistage centrifugal blower or multistage centrifugal compressor
Technical field
The present invention relates to the impeller inlet guide ring in multistage centrifugal blower and the centrifugal compressor.
Background technique
Multistage centrifugal blower and multistage centrifugal compressor are widely used in the industrial departments such as metallurgy, petrochemical industry, power, sewage treatment.
Shown in Figure 1, multistage centrifugal blower and multistage centrifugal compressor are when work, and gas is sucked by induction chamber 1, and by being fixed on the 6 pairs of gas works done of impeller on the main shaft 2, gas pressure, speed, temperature improve; Flow into Diffuser 7 then, gas velocity reduces, pressure continues to improve; Bend 8 and return channel 9 play the guiding role, make gas flow into the next stage impeller, each grade is made up of an impeller and the retaining element that matches thereof such as Diffuser, bend and return channel etc., and such working procedure repeats, and the pressurized gas that final stage is come out are through spiral case 10 outputs.
Shown in Figure 2, in existing structural type, to outlet, airflow direction moves along a curved path by axially transferring to radially air-flow from the import of impeller 6 in each grade.Along with the distance of leaving impeller air-flow path centre of curvature increases, airspeed reduces, and pressure increases, therefore near enclosing cover for impeller 11 place's air-flows are by axial commentaries on classics radially the time, boundary layer separation district 14 takes place in convergence back diffusion at the enclosing cover for impeller turning earlier, and to 13 diffusions of impeller outlet place; And nearly hub disk 3 place's stream pressures produce the interference of the secondary flow vertical with impeller main air flow direction thus greater than nearly wheel cap side.These will cause the pneumatic efficiency of blower or compressor to reduce, and worsen gas flow.
Summary of the invention
The present invention is for avoiding above-mentioned existing in prior technology deficiency, the impeller inlet flow guide structure of a kind of multistage centrifugal blower or multistage centrifugal compressor is provided, to improve the impeller inlet air conditions of existing multistage centrifugal blower or centrifugal compressor, suppress wheel cap air inlet turning gas separation, reduce secondary flow and decrease, improve multistage centrifugal blower and centrifugal compressor pneumatic efficiency and running stability.
Technical solution problem of the present invention adopts following technological scheme:
The impeller inlet flow guide structure of multistage centrifugal blower of the present invention or multistage centrifugal compressor includes return channel, impeller, axle sleeve, return channel cover plate, enclosing cover for impeller, wheel disc, impeller blade import position and return channel blade exit position; Structural feature of the present invention is air-flow to be flowed to by upper level in the air-flow path of next stage be provided with guide ring what form with return channel, impeller and axle sleeve.
The structural feature of the impeller inlet flow guide structure of multistage centrifugal blower of the present invention or multistage centrifugal compressor also is:
Described guide ring in described air-flow path with the distance of enclosing cover for impeller than nearer with the distance of wheel disc, described guide ring and impeller blade import position and return channel blade exit position all maintain distance.
The guide ring revolution bus of described guide ring is a camber line.
Described guide ring by on the plane that is arranged in guide ring and the water conservancy diversion gusset that is disposed radially and the retaining ring that is positioned at the guide ring periphery be fixed in the inner groove of return channel cover plate.
The quantity of the quantity of described water conservancy diversion gusset and impeller blade and return channel blade is unequal, and arbitrarily between the two common divisor is not more than 2.
Described guide ring is connected with return channel dividing plate caudal lobe by sunk screw.
Compared with the prior art, beneficial effect of the present invention is embodied in:
Impeller inlet guide ring of the present invention changes the air flow state at impeller air inlet position: when the high-octane air-flow of part enters the wheel cap turning, the separation of air-flow diffusion is suppressed, reduce the adverse effect that secondary flow is brought in the impeller simultaneously, effectively improved the pneumatic efficiency and the running stability of multistage centrifugal blower or multistage centrifugal compressor.
Description of drawings
Fig. 1 is multistage centrifugal blower or a multistage centrifugal compressor cross-sectional view in the prior art;
Fig. 2 is the channel cross-section figure that multistage centrifugal blower or multistage centrifugal compressor impeller and return channel form in the prior art;
Fig. 3 is a structural representation of the present invention;
Fig. 4 is another mode of execution structural representation of the present invention;
Fig. 5 a is guide ring sectional structure schematic representation among the present invention;
Fig. 5 b is guide ring plan view among the present invention;
Fig. 5 c is guide ring side view among the present invention;
Fig. 6 a is sectional structure schematic representation in another mode of execution of the present invention;
Fig. 6 b is guide ring side-looking structural representation in another mode of execution of the present invention.
Number in the figure: 1 induction chamber, 2 main shafts, 3 hub disks, 4 return channel blade exit positions, 5 return channel cover plates, 6 impellers, 7 Diffusers, 8 bends, 9 return channels, 10 spiral cases, 11 enclosings cover for impeller, 12 axle sleeves, 13 impeller outlet places, the boundary layer separation district takes place in 14 enclosing cover for impeller turnings, 15 guide rings revolution bus, 16 water conservancy diversion gussets, 17 retaining rings, 18 impeller blade import positions, 19 guide rings, 20 return channel dividing plate caudal lobes, 21 sunk screws.
Embodiment
Embodiment 1:
Referring to Fig. 3, Fig. 5 a, Fig. 5 b and Fig. 5 c, in the present embodiment, at return channel 9, the air-flow that makes that forms between impeller 6 and the axle sleeve 12 is flowed in the air-flow path of next stage by upper level, guide ring 19 is set, guide ring 19 is by on the plane that is positioned at guide ring, and water conservancy diversion gusset 16 that is disposed radially and the retaining ring 17 that is arranged in the guide ring periphery are fixed in the inner groove of return channel cover plate 5, guide ring 19 in air-flow path with the distance of enclosing cover for impeller 11 than nearer with the distance of wheel disc 3, guide ring 19 all maintains distance with impeller blade import position 18 and return channel blade exit position 4, to avoid interference, guide ring revolution bus 15 is a camber line.
For the ease of being provided with, in the present embodiment, the quantity of water conservancy diversion gusset 16 can not equate with the quantity of impeller blade and return channel blade, and between the two common divisor is not more than 2 arbitrarily, such as: suppose that the water conservancy diversion reinforcing plate number is 11, the impeller blade number is 12, then the quantity of return channel blade can be 13 or 14, is unallowed but the quantity of return channel blade is taken as 15 or 16, here, 15, have common divisor 3 and 4 between 16 and 12 respectively, all greater than 2.
Embodiment 2:
Referring to Fig. 4, Fig. 6 a and Fig. 6 b, different is with embodiment 1, in the present embodiment, guide ring 19 is fixed on the return channel dividing plate caudal lobe (20) by sunk screw (21), in this structural type, do not need to be provided with water conservancy diversion gusset 16 and retaining ring 17 on the guide ring 19, other structural type is all identical with embodiment.

Claims (6)

1. the impeller inlet flow guide structure of multistage centrifugal blower or multistage centrifugal compressor includes return channel (9), impeller (6), axle sleeve (12), return channel cover plate (5), enclosing cover for impeller (11), wheel disc (3), impeller blade import position (18) and return channel blade exit position (4); It is characterized in that air-flow being flowed to by upper level in the air-flow path of next stage be provided with guide ring (19) what form with return channel (9), impeller (6) and axle sleeve (12).
2. the impeller inlet flow guide structure of multistage centrifugal blower according to claim 1 or multistage centrifugal compressor, it is characterized in that described guide ring (19) in described air-flow path with the distance of enclosing cover for impeller (11) than nearer with the distance of wheel disc (3), described guide ring (19) all maintains distance with impeller blade import position (18) and return channel blade exit position (4).
3. the impeller inlet flow guide structure of multistage centrifugal blower according to claim 1 or multistage centrifugal compressor is characterized in that the guide ring revolution bus (15) of described guide ring (19) is camber line.
4. the impeller inlet flow guide structure of multistage centrifugal blower according to claim 1 or multistage centrifugal compressor, the described guide ring of its feature (19) by on the plane that is arranged in guide ring and the water conservancy diversion gusset (16) that is disposed radially and the retaining ring (17) that is positioned at the guide ring periphery be fixed in the inner groove of return channel cover plate (5).
5. the impeller inlet flow guide structure of multistage centrifugal blower according to claim 4 or multistage centrifugal compressor, the quantity that it is characterized in that the quantity of described water conservancy diversion gusset (16) and impeller blade and return channel blade is unequal, and between the two common divisor is not more than 2 arbitrarily.
6. the impeller inlet flow guide structure of multistage centrifugal blower according to claim 1 or multistage centrifugal compressor is characterized in that described guide ring (19) is connected with return channel dividing plate caudal lobe (20) by sunk screw (21).
CN 201010508522 2010-10-15 2010-10-15 Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor CN101949393A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201010508522 CN101949393A (en) 2010-10-15 2010-10-15 Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201010508522 CN101949393A (en) 2010-10-15 2010-10-15 Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor

Publications (1)

Publication Number Publication Date
CN101949393A true CN101949393A (en) 2011-01-19

Family

ID=43452995

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201010508522 CN101949393A (en) 2010-10-15 2010-10-15 Multistage centrifugal blower or impeller inlet flowing guide structure of multistage centrifugal compressor

Country Status (1)

Country Link
CN (1) CN101949393A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102192191A (en) * 2011-03-30 2011-09-21 宋波 Orthogonal guide rectifier
CN102400960A (en) * 2011-12-20 2012-04-04 中国船舶重工集团公司第七�三研究所 Centrifugal oxygen-enriched air compressor and application thereof
CN102852862A (en) * 2012-10-09 2013-01-02 宁波风机有限公司 Air inlet flow guide device for small centrifugal fan
CN103398024A (en) * 2013-08-15 2013-11-20 西安胜唐鼓风机有限公司 Inlet guide device of sintering machine
CN103671193A (en) * 2013-11-30 2014-03-26 西安交通大学 Centrifugal compressor with oscillatory flow returning device blades
CN104995411A (en) * 2012-12-14 2015-10-21 苏尔寿管理有限公司 Pump device comprising a flow guiding element
CN105240320A (en) * 2015-10-15 2016-01-13 珠海格力电器股份有限公司 Air supplementation structure of centrifugal compressor and compressor
WO2020211706A1 (en) * 2019-04-16 2020-10-22 Atlas Copco (Wuxi) Compressor Co., Ltd. Guide device for directing gas through

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB745059A (en) * 1952-03-21 1956-02-22 Alfred Buchi Multi-stage centrifugal pump or blower
DE1046248B (en) * 1952-03-21 1958-12-11 Alfred Buechi Dr Ing Multi-stage centrifugal conveyor machine
CH466492A (en) * 1966-12-05 1968-12-15 Utah Construction & Mining Co Centrifugal compressor
CN1875191A (en) * 2003-11-07 2006-12-06 诺沃皮尼奥内控股有限公司 Multistage centrifugal compressor
CN201358959Y (en) * 2009-01-21 2009-12-09 长沙埃尔压缩机有限责任公司 Multistage centrifugal blower
CN201827150U (en) * 2010-10-15 2011-05-11 合肥通用机械研究院 Flow guiding structure at impeller inlet of multistage centrifugal blower or multistage centrifugal compressor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB745059A (en) * 1952-03-21 1956-02-22 Alfred Buchi Multi-stage centrifugal pump or blower
DE1046248B (en) * 1952-03-21 1958-12-11 Alfred Buechi Dr Ing Multi-stage centrifugal conveyor machine
CH466492A (en) * 1966-12-05 1968-12-15 Utah Construction & Mining Co Centrifugal compressor
CN1875191A (en) * 2003-11-07 2006-12-06 诺沃皮尼奥内控股有限公司 Multistage centrifugal compressor
US20070122273A1 (en) * 2003-11-07 2007-05-31 Franco Sarri Multistage centrifugal compressor
CN201358959Y (en) * 2009-01-21 2009-12-09 长沙埃尔压缩机有限责任公司 Multistage centrifugal blower
CN201827150U (en) * 2010-10-15 2011-05-11 合肥通用机械研究院 Flow guiding structure at impeller inlet of multistage centrifugal blower or multistage centrifugal compressor

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102192191A (en) * 2011-03-30 2011-09-21 宋波 Orthogonal guide rectifier
CN102192191B (en) * 2011-03-30 2013-07-31 宋波 Orthogonal guide rectifier
CN102400960A (en) * 2011-12-20 2012-04-04 中国船舶重工集团公司第七�三研究所 Centrifugal oxygen-enriched air compressor and application thereof
CN102852862A (en) * 2012-10-09 2013-01-02 宁波风机有限公司 Air inlet flow guide device for small centrifugal fan
CN102852862B (en) * 2012-10-09 2015-11-11 宁波风机有限公司 A kind of air inlet flow guide device for small centrifugal fan
CN104995411A (en) * 2012-12-14 2015-10-21 苏尔寿管理有限公司 Pump device comprising a flow guiding element
US10634165B2 (en) 2012-12-14 2020-04-28 Sulzer Management Ag Pumping apparatus having a flow guiding element
CN103398024B (en) * 2013-08-15 2016-03-23 西安胜唐鼓风机有限公司 A kind of import flow guide device of sintering machine
CN103398024A (en) * 2013-08-15 2013-11-20 西安胜唐鼓风机有限公司 Inlet guide device of sintering machine
CN103671193A (en) * 2013-11-30 2014-03-26 西安交通大学 Centrifugal compressor with oscillatory flow returning device blades
CN103671193B (en) * 2013-11-30 2016-01-20 西安交通大学 The centrifugal compressor that a kind of return channel blade can vibrate
CN105240320A (en) * 2015-10-15 2016-01-13 珠海格力电器股份有限公司 Air supplementation structure of centrifugal compressor and compressor
CN105240320B (en) * 2015-10-15 2019-01-22 珠海格力电器股份有限公司 A kind of centrifugal compressor gas supplementary structure and compressor
US10544799B2 (en) 2015-10-15 2020-01-28 Gree Electric Appliances, Inc. Of Zhuhai Centrifugal compressor gas-supplementing structure and compressor
WO2020211706A1 (en) * 2019-04-16 2020-10-22 Atlas Copco (Wuxi) Compressor Co., Ltd. Guide device for directing gas through

Similar Documents

Publication Publication Date Title
CN104995375B (en) Sealing assembly between hot gas route and disc cavity in turbine engine
USRE32462E (en) Centrifugal fluid machine
US8616843B2 (en) Turbo machinery
CN1072318C (en) Air moving device
EP0439267B1 (en) Compressor impeller with displaced splitter blades
US8016557B2 (en) Airfoil diffuser for a centrifugal compressor
US8313290B2 (en) Centrifugal compressor having vaneless diffuser and vaneless diffuser thereof
US10066638B2 (en) Centrifugal compressor and turbocharger
US2658455A (en) Impeller with center intake
CA2618177C (en) Leaned centrifugal compressor airfoil diffuser
EP2975269B1 (en) Centrifugal compressor
CN104421199B (en) The asymmetrical bilateral turbo-charger impeller of function and diffuser
CN104428539A (en) Centrifugal compressor
US4354802A (en) Vaned diffuser
EP2917587B1 (en) Centrifugal compressor with twisted return channel vane
US10400788B2 (en) Intermediate intake-type diaphragm and centrifugal rotating machine
CN105723097B (en) Radial outward flow turbine
US9371836B2 (en) Mixed flow fan assembly
US8534998B2 (en) Centrifugal fan
US9874224B2 (en) Centrifugal compressor and turbocharger
US3171353A (en) Centrifugal fluid pump
RU2581686C2 (en) Radial diffuser blade for centrifugal compressors
CN101868629B (en) Compressor
US20160069302A1 (en) Compressor of exhaust turbocharger
CN104196761A (en) Double-air-inlet centrifugal fan

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20110119

C02 Deemed withdrawal of patent application after publication (patent law 2001)