CN103161761A - Application of staggered spiral type design on volute - Google Patents
Application of staggered spiral type design on volute Download PDFInfo
- Publication number
- CN103161761A CN103161761A CN2011104253871A CN201110425387A CN103161761A CN 103161761 A CN103161761 A CN 103161761A CN 2011104253871 A CN2011104253871 A CN 2011104253871A CN 201110425387 A CN201110425387 A CN 201110425387A CN 103161761 A CN103161761 A CN 103161761A
- Authority
- CN
- China
- Prior art keywords
- spiral case
- volute
- spiral
- section
- design
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 claims abstract description 15
- 241000237858 Gastropoda Species 0.000 claims description 10
- 230000002452 interceptive effect Effects 0.000 abstract 1
- 230000000739 chaotic effect Effects 0.000 description 2
- 238000012938 design process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Images
Abstract
The invention belongs to design methods of a volute of a centrifugal compressor, and particularly relates to an application of staggered spiral type design on volute. Spiral lines is designed as connecting lines of centers of each cross section of the volute, and the spiral lines spreads circumferentially from the volute. The volute is divided into 8-12 cross section positions circumferentially, central line of each cross section shifts 2-5mm along a shaft line with respect to the central line of the previous cross section, and a transverse volute tongue structure is formed. The transverse volute tongue is formed by means of shifting central lines of cross sections, and thus the volute is avoided from interfering with a chimney fan, an initial small cross section of the volute is protected, air is guided to flow, and efficiency is improved. The initial small cross section of the volute is protected by removing the small cross sections of 0-10 degrees, and thus flow is improved, and volute size is reduced. The volute chimney fan of the centrifugal compressor is smoothly connected with the volute which is designed in a staggered spiral method, initial shape line of the chimney fan is in accordance with air flow direction at the outlet of the volute, and impact loss is reduced.
Description
Technical field
The invention belongs to the design method of scroll casing of centrifugal compressor, the specifically application of a kind of offset spiral design on spiral case.
Background technique
Centrifugal compressor for pursuing high efficiency pattern, is therefore often taked the structure optimization corrective measure to spiral case in design process, the energy-saving potential that may exist to excavating it improves the overall operation efficiency of unit by this.In the centrifugal compressor design, often there is certain particularity in the design of noticing spiral case, because wind outlet barrel is eaten up the spiral case small bore greatly, air-flow directly enters wind outlet barrel after Diffuser flows out in this section, therefore the main air flow of wind outlet barrel impacted, cause larger air-flow losses by mixture.How reducing air-flow losses by mixture puzzlement is the serious problems that those skilled in the art run into.
During spiral case, wind outlet barrel tends to cut the part small bore to centrifugal compressor in design, and forms connected domain by the tangent plane both, this just formed spiral case in circulate, cause the internal leakage loss.Adopt at present to change the spiral case sectional area, snail tongue structure and initial angle improve the spiral case pneumatic efficiency, have obtained lifting by a relatively large margin, but still have certain mobile chaotic district in the wind outlet barrel part.
Summary of the invention
In order to solve the mobile chaotic problem of wind outlet barrel in scroll casing of centrifugal compressor, the object of the present invention is to provide the application of a kind of offset spiral design on spiral case.
The objective of the invention is to be achieved through the following technical solutions:
The present invention adopts helix as the line of each kernel of section of spiral case, along the spiral case circumferentially deploying.
Wherein: spiral case each cross section is offset vertically, and the line of each kernel of section forms helix; The process that each cross section of described spiral case is offset vertically is: spiral case is divided into 8～12 sectional positions by circumferencial direction, then with the more last kernel of section line of each kernel of section line along journal offset 2～5mm, form the structure of a horizontal snail tongue; Described horizontal snail tongue is the method that spiral case is taked the skew of kernel of section line, after avoiding spiral case and wind outlet barrel to interfere, the initial small bore of spiral case is partly saved from damage, and is mobile in order to guide, and raises the efficiency; It is that 0 °～10 ° small bores are excised that the initial small bore of described spiral case is partly saved from damage, is conducive to improve flow, and reduces the spiral case volume; The scroll casing of centrifugal compressor wind outlet barrel is smoothly connected with the spiral case that adopts the design of offset spiral design method, and the initial molded line of wind outlet barrel and spiral case exit gas main flow direction are consistent, and reduce impact loss.
Advantage of the present invention and good effect are:
1. the present invention adopts each cross section axial dipole field of spiral case, and each kernel of section line becomes helix shape, makes the small bore of spiral case and wind outlet barrel no longer crossing, has avoided the loss that circulates that exists in ordinary spiral case.Show by numerical simulation calculation, after each cross section axial dipole field of spiral case, the problem that does not exist spiral case small bore and wind outlet barrel to interfere has not had the loss of circulating, and spiral case small bore place has not had whirlpool clearly yet; Also no longer crossing at intake duct and wind outlet barrel, in wind outlet barrel, mobility status improves like this, and in spiral case, the bulk velocity distribution is more original designs a model evenly, compares master mould, and efficient improves 1.15%.
2. the present invention suitably is offset the spiral case cross section in the design process of spiral case, namely the molded line of spiral case is revised, and for technique with make all simple possible, is convenient to the popularization of offset spiral spiral case.
3. the present invention after the method that adopts the skew of kernel of section line avoids spiral case and wind outlet barrel to interfere, can do a horizontal snail tongue, and is mobile in order to guide, and improves the flow field, improves whole efficiency.
4. suitably to save from damage at the initial small bore of spiral case be that the initial small bore of spiral case is that low speed flows in the present invention, and 0 °～10 ° small bores are excised, and is conducive to improve and flows, and reduces the spiral case volume.
5. the present invention should be smoothly connected with the offset spiral spiral case at the spiral case wind outlet barrel, and the initial molded line of wind outlet barrel and spiral case exit gas main flow direction are consistent, and reduces impact loss.
6. the present invention is than common inner spiral casing, increase for the length of spiral case is limited, but the increase of this length is only that the final stage outlet volute stretches out, can't affect axial span and the bearing arrangement of rotor, also can not bring impact to critical speed of rotation and the stability of rotor.
Description of drawings
Fig. 1 is the whole level of centrifugal compressor of the present invention computation model structural drawing;
Fig. 2 is the schematic diagram of each cross section skew of scroll casing of centrifugal compressor of the present invention;
Fig. 3 is the air extraction structure schematic diagram after each cross section skew of scroll casing of centrifugal compressor of the present invention;
Fig. 4 is the complete computation illustraton of model of scroll casing of centrifugal compressor of the present invention;
Wherein: 1 is impeller, and 2 is Diffuser, and 3 is return channel, and 4 is spiral case, and 5 is horizontal snail tongue.
Embodiment
The invention will be further described below in conjunction with accompanying drawing.
As shown in Fig. 1～3, helix is as the line of each kernel of section of spiral case, along the spiral case circumferentially deploying; Spiral case is divided into 8～12 sectional positions by circumferencial direction, then with the more last kernel of section line of each kernel of section line along journal offset 2～5mm, the line of each kernel of section forms helix, and then forms the structure of a horizontal snail tongue.
Laterally the snail tongue is the method that spiral case is taked the skew of kernel of section line, after avoiding spiral case and wind outlet barrel to interfere, the initial small bore of spiral case is partly saved from damage, namely 0 °～10 ° small bores are excised, mobile in order to guide, raise the efficiency, be conducive to improve and flow, reduce the spiral case volume.
The scroll casing of centrifugal compressor wind outlet barrel is smoothly connected with the spiral case that adopts the design of offset spiral design method, and the initial molded line of wind outlet barrel and spiral case exit gas main flow direction are consistent, and reduce impact loss.Concrete grammar is:
Spiral case 4 is divided into 8～12 cross sections (the present embodiment is divided into 12 cross sections) along the circumferential direction, every 30 ° of cross sections, determine offset dimensions 2～5mm according to the shape in each cross section, then utilize existing 3D sculpting software (as Pro-E), by the function of mixed sweep, select a suitable track scanning to go out the spiral case entity, extend air duct, and make the snail tongue and to the modification of small bore, complete the spiral case moulding.
Investigate the offset spiral design to the impact in spiral case 4 flow fields, front and back, a complete computational fields will be arranged, therefore computation model of the present invention is comprised of impeller 1, Diffuser 2, bend, return channel 3 and spiral case more than 4 parts, these several parts are carried out respectively modeling and grid division, then carry out the grid docking, finally provide analog computation.According to structural feature, the present invention is divided into three parts with whole computational fields: entrance extension, impeller and diffuser portion, bend and return channel part, spiral case and wind outlet barrel part.Each part is given according to the model parameter of existing centrifugal compressor, just ignored the gap between impeller and Diffuser, impeller diameter is 1438mm, 19 blades are arranged, blade inlet edge is that the round end afterbody is blunt nosed, vaneless diffuser, return channel have 18 blades, and the blade front and rear edge is all round end.
The offset spiral design is applied on spiral case, with each cross section axial dipole field of spiral case, each kernel of section line becomes helix shape, make small bore and the wind outlet barrel of spiral case no longer crossing, and guarantee that wind outlet barrel should be smoothly connected with the offset spiral spiral case, avoided the loss that circulates that exists in ordinary spiral case in such structure, the initial molded line of wind outlet barrel also is consistent with spiral case exit gas main flow direction, reduces impact loss.
Show by the analog computation of existing CFD analysis software, after each cross section axial dipole field of spiral case, the problem that does not exist spiral case small bore and wind outlet barrel to interfere has not had the loss of circulating, and spiral case small bore place has not had whirlpool clearly yet; Also no longer crossing at intake duct and wind outlet barrel, in wind outlet barrel, mobility status improves like this, and eliminated the irregular mobility status at original 360 ° of outlets and wind outlet barrel place fully, it is better that spiral case after optimization and wind outlet barrel mate, pressure distribution is also more even, compare master mould, efficient improves 1.15%.
As everyone knows, spiral case is that impeller or the collection of Diffuser effluent air are transported to exhaust duct, and flowing of its inside is very complicated.Air-flow constantly has gas to flow into spiral case by impeller (or Diffuser) along the colleague that spiral case flows, and namely gas simultaneously flows, and one side is mixed.Therefore the design of spiral case molded line not only directly affects the flow losses in spiral case, and the impeller of front or the performance of Diffuser are had anti-impact.The present invention adopts the design method of offset spiral, the spiral case molded line is improved, and to comprising that several parts of impeller, Diffuser, bend, return channel and spiral case form the territory of flowing and consider, by the analog computation of existing CFD analysis software, improve pneumatic efficiency 1.15%, show that the whole efficiency of compressor bank has had further raising.
Above-described embodiment is the better mode of execution of the present invention; but embodiments of the present invention are not restricted to the described embodiments; other any do not deviate from change, the modification done under Spirit Essence of the present invention and principle, substitutes, combination, simplify; all should be the substitute mode of equivalence, within being included in protection scope of the present invention.
Claims (6)
1. the application of offset spiral design on spiral case, it is characterized in that: helix is as the line of each kernel of section of spiral case, along the spiral case circumferentially deploying.
2. by the application of the described offset spiral of claim 1 design on spiral case, it is characterized in that: spiral case each cross section is offset vertically, and the line of each kernel of section forms helix.
3. by the application of the described offset spiral design of claim 2 on spiral case, it is characterized in that: the process that described spiral case each cross section is offset vertically is: spiral case is divided into 8～12 sectional positions by circumferencial direction, then with the more last kernel of section line of each kernel of section line along journal offset 2～5mm, form the structure of a horizontal snail tongue.
4. by the application of the described offset spiral design of claim 3 on spiral case, it is characterized in that: described horizontal snail tongue is the method that spiral case is taked the skew of kernel of section line, after avoiding spiral case and wind outlet barrel to interfere, the initial small bore of spiral case is partly saved from damage, mobile in order to guide, raise the efficiency.
5. by the application of the described offset spiral design of claim 4 on spiral case, it is characterized in that: it is that 0 °～10 ° small bores are excised that the initial small bore of described spiral case is partly saved from damage, is conducive to improve flow, and reduces the spiral case volume.
6. by the application of the described offset spiral design of claim 1 on spiral case, it is characterized in that: the scroll casing of centrifugal compressor wind outlet barrel is smoothly connected with the spiral case that adopts the design of offset spiral design method, the initial molded line of wind outlet barrel and spiral case exit gas main flow direction are consistent, and reduce impact loss.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110425387.1A CN103161761B (en) | 2011-12-16 | A kind of offset spiral method for designing of spiral case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110425387.1A CN103161761B (en) | 2011-12-16 | A kind of offset spiral method for designing of spiral case |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103161761A true CN103161761A (en) | 2013-06-19 |
| CN103161761B CN103161761B (en) | 2016-12-14 |
Family
ID=
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832455A (en) * | 2015-04-10 | 2015-08-12 | 江苏大学 | Centrifugal pump impeller with round blade outlet sides |
| CN105090122A (en) * | 2015-06-30 | 2015-11-25 | 黑龙江凯普瑞机械设备有限公司 | Centrifugal fan and vaneless diffuser thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6579060B1 (en) * | 1999-09-28 | 2003-06-17 | Royal Appliance Mfg. Co. | Impeller and housing assembly with reduced noise and improved airflow |
| US20070134085A1 (en) * | 2001-12-10 | 2007-06-14 | Resmed Limited | Double-ended blower and volutes therefor |
| CN1985093A (en) * | 2004-01-30 | 2007-06-20 | 百思科技公司 | Housing for a centrifugal fan, pump or turbine |
| CN101296722A (en) * | 2005-10-28 | 2008-10-29 | 雷斯梅德有限公司 | Single or multiple stage blower and nested volute(s) and/or impeller(s) therefor |
| US7455499B2 (en) * | 2005-07-07 | 2008-11-25 | The Scott Fetzer Company | Centrifugal fan |
| CN201891495U (en) * | 2010-11-26 | 2011-07-06 | 宁波科达制动器制造有限公司 | Turbocharger |
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6579060B1 (en) * | 1999-09-28 | 2003-06-17 | Royal Appliance Mfg. Co. | Impeller and housing assembly with reduced noise and improved airflow |
| US20070134085A1 (en) * | 2001-12-10 | 2007-06-14 | Resmed Limited | Double-ended blower and volutes therefor |
| CN1985093A (en) * | 2004-01-30 | 2007-06-20 | 百思科技公司 | Housing for a centrifugal fan, pump or turbine |
| US7455499B2 (en) * | 2005-07-07 | 2008-11-25 | The Scott Fetzer Company | Centrifugal fan |
| CN101296722A (en) * | 2005-10-28 | 2008-10-29 | 雷斯梅德有限公司 | Single or multiple stage blower and nested volute(s) and/or impeller(s) therefor |
| CN201891495U (en) * | 2010-11-26 | 2011-07-06 | 宁波科达制动器制造有限公司 | Turbocharger |
Non-Patent Citations (1)
| Title |
|---|
| 刘丰庆: "离心压缩机中间抽气结构优化设计", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832455A (en) * | 2015-04-10 | 2015-08-12 | 江苏大学 | Centrifugal pump impeller with round blade outlet sides |
| CN105090122A (en) * | 2015-06-30 | 2015-11-25 | 黑龙江凯普瑞机械设备有限公司 | Centrifugal fan and vaneless diffuser thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Zhu et al. | Optimization design of a reversible pump–turbine runner with high efficiency and stability | |
| Ye et al. | Numerical investigation of blade tip grooving effect on performance and dynamics of an axial flow fan | |
| CN203500056U (en) | Closed-type high-flow and high-energy head model level | |
| CN102608914B (en) | Optimization design method of radial-flow-type hydraulic turbine | |
| CN102852857B (en) | High-load super transonic axial gas compressor aerodynamic design method | |
| CN203335470U (en) | High-efficiency centrifugal fan without volute | |
| CN101403321A (en) | Axial flow turbine and stage structure thereof | |
| CN104675755A (en) | Circumferential staggered self-circulating casing treating method for axial-flow compressor | |
| CN104675748B (en) | A kind of low noise with conduit is without spiral case centrifugal fan | |
| CN102817873B (en) | Ladder-shaped gap structure for gas compressor of aircraft engine | |
| CN105782117A (en) | Stability extending device of centrifugal compressor | |
| CN103807201A (en) | Combined suction layout method for controlling compressor stator corner separation | |
| CN104806571B (en) | A kind of efficient centrifugal air blast based on computational fluid dynamics simulation | |
| CN105179322B (en) | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove | |
| CN105756719A (en) | Gas compressor stator blade root slotting method based on optimization algorithm | |
| CN104392018A (en) | Realization method of circular-arc inclined slit machine case based on tip flow field and geometric formulation | |
| CN103244209B (en) | A kind of diffuser end wall of turbine single-side exhaust system | |
| CN108487942A (en) | Control the casing and blade combined shaping method of turbine blade-tip gap flowing | |
| CN104653515A (en) | Double-suction type centrifugal ventilation fan | |
| CN113090580B (en) | Centrifugal impeller blade with S-shaped front edge and modeling method thereof | |
| CN101749279A (en) | Centrifugal compressor asymmetric self-circulation treatment casing based on varied notching width | |
| CN101158991A (en) | Pneumatic power design method for big and small blade compressor | |
| CN204692190U (en) | A kind of vane diffuser with deviated splitter vane | |
| CN202833325U (en) | Radial diffuser and centrifugal compressor with the same | |
| Tun et al. | Multi-point optimization of recirculation flow type casing treatment in centrifugal compressors |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110869 No. 16 A Development Road, Shenyang Economic and Technological Development Zone, Liaoning Province Patentee after: Shenyang Blower Works Group Corp. Address before: 110869 No. 16 A Development Road, Shenyang Economic and Technological Development Zone, Liaoning Province Patentee before: SHENYANG BLOWER WORKS Group Corp. |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20130619 Assignee: SHENYANG BLOWER GROUP GEAR COMPRESSOR CO.,LTD. Assignor: Shenyang Blower Works Group Corp. Contract record no.: X2023210000171 Denomination of invention: A Design Method for Spiral Case with Misalignment Granted publication date: 20161214 License type: Common License Record date: 20231103 |