CN1386985A - Diffuser with dual-column blades arranged radially and serially - Google Patents
Diffuser with dual-column blades arranged radially and serially Download PDFInfo
- Publication number
- CN1386985A CN1386985A CN02111960A CN02111960A CN1386985A CN 1386985 A CN1386985 A CN 1386985A CN 02111960 A CN02111960 A CN 02111960A CN 02111960 A CN02111960 A CN 02111960A CN 1386985 A CN1386985 A CN 1386985A
- Authority
- CN
- China
- Prior art keywords
- diffuser
- blade
- serially
- dual
- arranged radially
- 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
Images
Classifications
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A diffuser for centrifugal air compressor has front and back rings of blades, which are serially arranged in a ring and are alternatively arranged between two rings. The curved directions for the blades in different rings are different. Its advantages are high efficiency and wide range of flow variation in enlarged high-efficiency region and stable working region.
Description
The present invention relates to the vane diffuser of centrifugal compressor technology, promptly a kind of diffuser with dual-column blades arranged radially and serially.
The gas compressor performance comparison test that single-row vane diffuser and diffuser with dual-column blades arranged radially and serially are housed shows: because before diffuser with dual-column blades arranged radially and serially can pass through, the gap of the different matched positions of back two row leaf gratings, the variation combination of mutual alignment geometric parameters such as degree of overlapping reaches the suitable selection of two row cascade blade shapes with the chord length ratio, can form difform convergent passage, thereby can realize effectively streaming of two row Diffuser leaf gratings controlled (flow separation and the aerodynamic loading of control blade face distribute), improved the performance of centrifugal compressor significantly, the pressure ratio of speed conditions such as make smooth with the characteristic curve of changes in flow rate, enlarge surge margin, improved the pressure and the efficiency value of contrast corresponding points.The structure of diffuser with dual-column blades arranged radially and serially of the prior art all adopts crooked concave and convex direction of ahead blading mean camber line and the identical layout of the crooked concave and convex direction of rank rear blade mean camber line bar none.The limitation and the defective of this structure are: can make the centrifugal compressor performance than single-row vane diffuser situation be improved significantly the shape configuration of diffuser with dual-column blades arranged radially and serially, be only limited to the convergent passage that the outside of belly by the back side of ahead blading exit portion and rank rear blade inlet part forms and be narrow crack state (passage section of passage is very narrow) this particular case (Fig. 1).This just makes the structure of this diffuser with dual-column blades arranged radially and serially with practical value cut the narrow crack that is communicated with the blade back of the body, the outside of belly (kinetic energy with the back side high velocity air in the narrow crack of flowing through is penetrated the low velocity fluid that blows outside of belly boundary layer with opening at the front half part streamwise of single-row vane diffuser blade, strengthen the moving ability of separating of outside of belly boundary layer fluid anti-current) structure, form with stream the gross differences of all not having on the control mechanism in essence.Fig. 2 shows the schematic representation of opening the slot crack on the single-row vane diffuser blade.Because forward and backward row blade mutual alignment can only select narrow crack to dispose the limitation of this specified structure, this has just had a strong impact on diffuser with dual-column blades arranged radially and serially and has constituted the diversified performance that the control convergent passage is improved the centrifugal compressor performance potential of streaming by changing the geometric parameter of leaf grating own.(data of prior art aspect is seen model filial piety select " centrifugal compressor biserial leaf grating diffuser Design and test ", internal-combustion engine engineering, 1980 the 2nd phases, 63～73 pages.About blade lattice streaming control, can consult Te Leishenke " aerodynamics of compressor blade row ", China Machine Press, in January, 1984, Beijing)
In order to overcome the narrow limitation of above-mentioned diffuser with dual-column blades arranged radially and serially structure, the present invention's design provides a kind of diffuser with dual-column blades arranged radially and serially new structure that makes the centrifugal compressor performance obtain bigger improvement.The diffuser with dual-column blades arranged radially and serially of the present invention's design is by radially arranged in series, circumferential staggered forward and backward two row radial blade Diffusers are formed.Wherein ahead blading is the accessory lobes grid; The rank rear blade is the main lobe grid.The matching principle of the major and minor leaf grating of diffuser with dual-column blades arranged radially and serially is with the accessory lobes grid streaming of different operating modes to be controlled, and makes the situation of streaming of main lobe grid keep good under design conditions and variable working condition as far as possible.Its technical characteristics is: the chord length of prostatitis accessory lobes grid blade is about 1/3～3/4 of rank rear main lobe grid blade chord length; The crooked concave and convex direction of the crooked concave and convex direction of prostatitis accessory lobes grid blade mean camber line and rank rear main lobe grid blade mean camber line is opposite each other, also be, the crooked concave and convex direction of rank rear blade mean camber line is all identical with the crooked concave and convex direction of the forward and backward row blade mean camber line of prior art diffuser with dual-column blades arranged radially and serially, also the crooked concave and convex direction with the blade mean camber line of single-row vane diffuser is identical, but opposite with the crooked concave and convex direction of ahead blading mean camber line; Near near the convergent passage that the outside of belly forms the outside of belly and the rank rear main lobe grid leaf head accessory lobes grid blade afterbody of prostatitis should be less than half pitch value of trailing edge place circumference in the circumferential spacing at prostatitis trailing edge place, and this condition can guarantee to form a convergence geometric properties and significantly stream the control runner near the outside of belly of rank rear blade inlet part.The fluid of the convergent passage of flowing through quickens therein, improved the flow velocity at the ahead blading afterbody back side and rank rear blade inlet part outside of belly place, increased the moving ability of separating of rank rear blade import outside of belly boundary layer fluid anti-current, the situation of streaming of rank rear main lobe grid is greatly improved.
Because the crooked concave and convex direction of ahead blading camber line is opposite with the crooked concave and convex direction of rank rear blade camber line, the present invention compares with the single-row or diffuser with dual-column blades arranged radially and serially of prior art, composes the following advantage of tool:
● allow how much angle α of ahead blading import
3ADesirable littler value, i.e. α
3A=10 °～15 °, thus " design discharge " corresponding with it and the value of " surge flow " are obviously reduced, and high efficiency operating mode and stall margin are expanded to the small flow direction.
● form near the outside of belly of rank rear blade inlet part easily that the multiple geometrical shape of row is available, the convergence geometric properties significantly streams the control runner, increased the ability of rank rear blade import outside of belly boundary layer fluid opposing flow separation.
● under the variable working condition situation, the ability of the anti-blade face of ahead blading flow separation own strengthens.When flow increases to certain value, separating just appears in flowing of ahead blading leading edge portion outside of belly place, but because air-flow is pressed the trend that log spiral moves in the runner, the fluid that has separated is extruded on the outside of belly that is attached to this ahead blading again in the downstream, has retrained, limited the expansion of fluid breakdown.For the very little operating mode of flow, because how much angle α of ahead blading import
3AValue obtains very little, and also corresponding the reducing of value of the air-flow high incidence at ahead blading import leading edge place postponed the generation of blade back separated flow, and makes the weakened of separated flow.
● the crooked concave and convex direction of ahead blading mean camber line makes air-flow turning in the accessory lobes grid of prostatitis (deceleration, diffusion) very fast, and ahead blading only need adopt short chord length just can allow the flow angle of rank rear blade inlet increase to and how much close degree in angle of rank rear blade import.
Ahead blading structure of the present invention in sum can adapt to bigger angle of attack excursion, the rank rear blade is played excellent good water conservancy diversion and boundary layer flow control action, guarantee in very big working conditions change scope, all to keep the good state that streams, thereby guaranteed whole diffuser with dual-column blades arranged radially and serially efficient height, the range of flow broadness of high efficient area and stable work area.
Below in conjunction with drawings and Examples technology contents of the present invention is specifically described.
Fig. 3 is the structural representation view of the diffuser with dual-column blades arranged radially and serially of the present invention's structure.Diffuser with dual-column blades arranged radially and serially by the ring base plate 1., the ring leaf grating 2. formed with the rank rear blade of the ring leaf grating formed of ahead blading 3. totally three parts constitute.2. the prostatitis leaf grating is cemented in base plate become one on 1. (integral precision casting or NC Milling form) with rank rear leaf grating blade 3..In base plate the same side 1., forward and backward two row leaf gratings 2. and 3. be each other arranged in series radially, along circumferential staggered (the prostatitis leaf grating 2. the blade trailing edge place diameter can greater than, be equal to or less than the 3. diameter of blade import leading edge of rank rear leaf grating).The mean camber line of rank rear blade crooked concave and convex direction 8. is identical with the crooked concave and convex direction of the blade mean camber line of the single-row or diffuser with dual-column blades arranged radially and serially of prior art, but ahead blading mean camber line crooked concave and convex direction 7. is opposite with it.Near the ahead blading afterbody the outside of belly 4. with the rank rear leaf head near the outside of belly 5. form a contraction shape passage 6., can implement effectively control to blade lattice streaming, improve the off design performance of centrifugal compressor.In Fig. 3 example, the trailing edge diameter of ahead blading is greater than the head leading edge diameter of rank rear blade.Fig. 4 shows the flow channel shape figure of the biserial vane diffuser of the present invention of a true design.In this embodiment, the trailing edge diameter of ahead blading is identical with the head leading edge diameter of rank rear blade; The ahead blading chord length is about half of rank rear blade chord length; At ahead blading trailing edge place, the circumferential distance between the rank rear blade outside of belly and the ahead blading outside of belly is about 1/4th of this place's circumference pitch value.
Claims (2)
1. diffuser with dual-column blades arranged radially and serially, it by the ring base plate 1., 3. 2. prostatitis ring leaf grating constitute with rank rear ring leaf grating, it is characterized in that: the prostatitis leaf grating 2. the blade mean camber line 7. crooked concave and convex direction and the rank rear leaf grating 3. blade mean camber line crooked concave and convex direction 8. is opposite each other, near the ahead blading afterbody outside of belly 4. with the rank rear leaf head near the outside of belly 5. constitute a contraction shape passage 6..
2. by the described diffuser with dual-column blades arranged radially and serially of claim 1, it is characterized in that: the prostatitis leaf grating 2. the chord length of blade be about the rank rear leaf grating 3. the blade chord length 1/3～3/4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021119600A CN1172093C (en) | 2002-06-06 | 2002-06-06 | Diffuser with dual-column blades arranged radially and serially |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021119600A CN1172093C (en) | 2002-06-06 | 2002-06-06 | Diffuser with dual-column blades arranged radially and serially |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1386985A true CN1386985A (en) | 2002-12-25 |
| CN1172093C CN1172093C (en) | 2004-10-20 |
Family
ID=4741830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021119600A Expired - Fee Related CN1172093C (en) | 2002-06-06 | 2002-06-06 | Diffuser with dual-column blades arranged radially and serially |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1172093C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195756A (en) * | 2012-01-10 | 2013-07-10 | 长沙理工大学 | Three-blade tandem type air compressor rotor |
| CN106089807A (en) * | 2016-06-28 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of diffuser based on fractal blade |
| CN106996383A (en) * | 2017-05-12 | 2017-08-01 | 浙江帝仕电子科技有限公司 | The brushless fan and its control mode of a kind of built-in drive |
| CN107304775A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN109026830A (en) * | 2018-08-16 | 2018-12-18 | 泛仕达机电股份有限公司 | A kind of centrifugal impeller |
| CN113090582A (en) * | 2021-03-30 | 2021-07-09 | 南京工业大学 | Tandem blade for generating unsteady jet flow based on front edge modification and rear edge modification |
| CN114688084A (en) * | 2022-05-23 | 2022-07-01 | 山东建筑大学 | Reverse lower-airfoil blade leading edge slotting configuration for reducing aerodynamic noise of centrifugal compressor |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100457548C (en) * | 2007-11-09 | 2009-02-04 | 北京航空航天大学 | Non-axial-symmetry combination processing machine box |
| CN101463831B (en) * | 2007-12-19 | 2011-07-27 | 富准精密工业(深圳)有限公司 | Cooling fan and its fan blades |
| US11401947B2 (en) * | 2020-10-30 | 2022-08-02 | Praxair Technology, Inc. | Hydrogen centrifugal compressor |
-
2002
- 2002-06-06 CN CNB021119600A patent/CN1172093C/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103195756A (en) * | 2012-01-10 | 2013-07-10 | 长沙理工大学 | Three-blade tandem type air compressor rotor |
| CN107304775A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN106089807A (en) * | 2016-06-28 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of diffuser based on fractal blade |
| CN106996383A (en) * | 2017-05-12 | 2017-08-01 | 浙江帝仕电子科技有限公司 | The brushless fan and its control mode of a kind of built-in drive |
| CN109026830A (en) * | 2018-08-16 | 2018-12-18 | 泛仕达机电股份有限公司 | A kind of centrifugal impeller |
| CN113090582A (en) * | 2021-03-30 | 2021-07-09 | 南京工业大学 | Tandem blade for generating unsteady jet flow based on front edge modification and rear edge modification |
| CN113090582B (en) * | 2021-03-30 | 2022-04-01 | 南京工业大学 | Tandem blade for generating unsteady jet flow based on front edge modification and rear edge modification |
| CN114688084A (en) * | 2022-05-23 | 2022-07-01 | 山东建筑大学 | Reverse lower-airfoil blade leading edge slotting configuration for reducing aerodynamic noise of centrifugal compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1172093C (en) | 2004-10-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7674092B2 (en) | Blade or vane for a turbomachine | |
| CN1272524C (en) | Turbomachine blade unit | |
| US4653976A (en) | Method of compressing a fluid flow in a multi stage centrifugal impeller | |
| CA2658914C (en) | Impulse turbine for use in bi-directional flows | |
| JP5550657B2 (en) | Bank platform turbine blade | |
| US7476086B2 (en) | Tip cambered swept blade | |
| US20110318172A1 (en) | Tandem blade design | |
| JPS5990797A (en) | Centrifugal compressor and compression method | |
| CN1172093C (en) | Diffuser with dual-column blades arranged radially and serially | |
| US20120009065A1 (en) | Rotor blade | |
| PL198629B1 (en) | Compressor's vane in particular for a gas turbine engine | |
| CN205559366U (en) | Centrifugal compressor's diffuser | |
| US2974927A (en) | Supersonic fluid machine | |
| CN100374733C (en) | Radial single raw blade diffuser | |
| CN112682108B (en) | Turbine blade end wall structure with D-shaped micro-group air film cooling holes, method thereof and gas turbine | |
| CN109026830B (en) | Centrifugal impeller | |
| CN110566285B (en) | Compact centripetal turbine guider | |
| CN114483204B (en) | Stationary blade suitable for radial-axial vertical non-vertical air inlet | |
| TWI638101B (en) | Bird wing-shaped high pressure axial fan blade and rotating axial flow fan thereof | |
| CN208605394U (en) | With the centrifugal impeller for increasing function decreasing loss | |
| CN207333296U (en) | Gas-turbine unit | |
| CN1650097A (en) | Improved vane design for use in variable geometry_turbocharger | |
| CN201547018U (en) | Rotating blade row layout of axial compressor | |
| CN201330620Y (en) | Novel high pressure clapboard static cascade applicable to steam turbine varying duty running | |
| CN201116510Y (en) | Wind mill impeller equipped with jet flap type vane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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 | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20041020 Termination date: 20110606 |