CN101173672A - Big and small impeller vane impeller with non-full height small blade and compressor machine - Google Patents
Big and small impeller vane impeller with non-full height small blade and compressor machine Download PDFInfo
- Publication number
- CN101173672A CN101173672A CNA2007101784016A CN200710178401A CN101173672A CN 101173672 A CN101173672 A CN 101173672A CN A2007101784016 A CNA2007101784016 A CN A2007101784016A CN 200710178401 A CN200710178401 A CN 200710178401A CN 101173672 A CN101173672 A CN 101173672A
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- China
- Prior art keywords
- big
- blade
- small
- impeller
- small leaf
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
Abstract
The invention discloses a compressor and an impeller with big and small blades in which the small blade is non-total-height. The invention is characterized in that: a blade is arranged between two adjacent big blades of the impeller with big and small blades; the height in radial direction of the small blade is equal to three percents to fifteen percents of the height in radial direction of the big blade; the string length in axial direction of the small blade is thirty percents to eighty-five percents of the string length in axial direction of the big blade; the initial arc of the small blade is the same as the arc in the central section of the big blade, and the tailing edge is aligned with the tailing edge of the big blade. The invention has the advantages that not only the structure and efficiency of the blade is not influenced, but also the secondary flow of the airflow near the wheel hub surface and at the root section of the blade is inhibited effectively.
Description
Technical field
The present invention relates to a kind of blade impellers mechanical device, relate in particular to a kind of impeller and gas compressor.
Background technique
Vane compressor generally is used for to gas boosting, is divided into axial flow, centrifugal and diagonal flow type gas compressor.Axial-flow compressor gas flow mode is an axial admission, axial exhaust; Centrifugal-flow compressor gas flow mode is an axial admission, radially exhaust; The diagonal flow type gas compressor is the compromise of axial flow and centrifugal compressor, and axial admission and axially has the several angle exhaust.Axial flow and diagonal flow type gas compressor comprise impeller, comprise rotor and stator, and impeller is provided with blade.
Gas compressor does work to air-flow by rotor blade, transforms the pressure energy and the kinetic energy of little air-flow, through stator blade unnecessary kinetic energy is converted into the pressure energy again, thereby finishes the supercharging to gas.Yet, gas always can not flow according to the direction of design, and flow direction and main flow and inconsistent at some local air flow produce partial lateral and flow, even occur flowing backwards and vortex, these and inconsistent the flowing of main flow direction are referred to as the interior secondary flow of gas compressor.In general, what secondary flow was brought all is counter productive, can hinder mobilely, weakens the boosting capability of gas compressor, reduces mechanical efficiency.
As shown in Figure 1, near the lateral flow 3 that occurs blade 1 root wheel hub surface 2 of rotor of the prior art is typical secondary flow.This is because the pressure of the pressure side of blade 1 greater than the pressure of suction surface, can form a vortex usually in the trigonum of the suction surface of blade 1 and wheel hub surface 2 formation, is called angular region vortex 4.Angular region vortex 4 can cause air-flow to stop up and flow losses, and may dwindle the gas compressor stable operation range.
As shown in Figure 2, in the intermediate portion of blade 2 height, because of air-flow velocity is bigger, the pressure difference balance between the centrifugal force of the generation of turning and pressure side, the suction surface, air-flow can flow through on request.
As shown in Figure 3, near wheel hub surface 2, the flowing velocity of air-flow slows down because of the obstruction of wheel hub surface 2, and pressure reduction will impel air-flow to flow to suction surface from pressure side.
In the prior art, for reducing lateral flow 3 and angular region vortex 4, general structure shape by the improvement blade reduces such as the corner that can make blade at root, or makes root of blade be in negative angle of attack, reduces the root load; Also can adopt full three-dimensional modeling design, allow blade, can partly control secondary flow at circumferential skewing.
There is following shortcoming at least in above-mentioned prior art: make the complex structure of blade, efficient low.
Summary of the invention
The purpose of this invention is to provide a kind of structure that neither influences blade and efficient, can effectively suppress air-flow near wheel hub surface and the big and small blade impeller and the gas compressor that have non-overall height small leaf of root of blade secondary flow again.
The objective of the invention is to be achieved through the following technical solutions:
The big and small blade impeller that has non-overall height small leaf of the present invention comprises a plurality of big blades, is provided with small leaf between adjacent two described big blades, and the radial height of described small leaf is smaller or equal to 20% of described big blades height.
Gas compressor of the present invention comprises the above-mentioned big and small blade impeller that has non-overall height small leaf.
As seen from the above technical solution provided by the invention, big and small blade impeller and the gas compressor that has non-overall height small leaf of the present invention, owing to be provided with small leaf between adjacent two big blades, the radial height of small leaf is smaller or equal to 20% of big blades height, neither influences the structure of blade and efficient, can effectively suppress air-flow near wheel hub surface and the secondary flow of root of blade again.
Description of drawings
Fig. 1 is the structural representation of big and small blade impeller of the prior art;
Fig. 2 is the intermediate portion velocity vector schematic representation of big and small blade impeller blade height in the prior art;
Fig. 3 is near the velocity vector schematic representation the big and small blade impeller wheel surface in the prior art;
Fig. 4 is the structural representation that has the big and small blade impeller of non-overall height small leaf of the present invention;
Fig. 5 is the inhibitory action schematic representation of non-overall height small leaf among the present invention near the secondary flow big and small blade impeller wheel surface.
Embodiment
The big and small blade impeller that has non-overall height small leaf of the present invention, its preferable embodiment as shown in Figure 4, comprise a plurality of big blades 5, be provided with small leaf 6 between adjacent two described big blades 5, the radial height of small leaf 6 can be smaller or equal to 20% of the height of big blade 5, can be 3%, 10%, 15%, 20% etc.
The axial chord length of small leaf 6 can be the 30%-85% of the axial chord length of big blade 5, can be 30%, 45%, 55%, 70%, 85% etc.Be that small leaf is not full-scale in the axial direction, but from axial a certain position, the trailing edge of small leaf 6 can be concordant with the trailing edge of big blade 5, also can be a little leading or lag behind the trailing edge of big blade 5.
The initial camber line of small leaf 6 can be identical with the middle part camber line of big blade 5.
Gas compressor of the present invention comprises the above-mentioned big and small blade impeller that has non-overall height small leaf, and above-mentioned big and small blade impeller can be used on the rotor of gas compressor, also can be used on the stator of gas compressor.
The present invention is being installed a small leaf additional between per two blades on the wheel hub surface of big and small blade impeller, the radial height of this small leaf is very little, thereby do not play pressurization substantially, its effect is to block near the horizontal secondary flow of wheel hub surface, reduce angular region vortex etc., thereby improve the working efficiency of impeller.
Referring to Fig. 1 and Fig. 3, as can be seen, near the lateral flow the wheel hub surface is generally more serious at the leaf grating rear portion.
So small leaf of the present invention is not full-scale in the axial direction, but, stop to big blade trailing edge from axial a certain position.The axial length of small leaf cutter is less than the axial length of big blade.
The specific constructive form of small leaf will determine that the mean camber line shape of small leaf can given original state be identical with corresponding big blade mean camber line by Pneumatic Calculation, and through behind the calculation optimization, its mean camber line can be any curve.
As shown in Figure 5, the existence of small leaf has been played the obvious suppression effect near the secondary flow the wheel hub surface as can be seen.Use structural type of the present invention, can weaken near the lateral flow of wheel hub surface greatly, stop up and flow losses thereby weaken the angular region.
Certainly, the frictional loss of small leaf itself and the extra secondary flow loss that itself causes have, but medium and small blades height of the present invention and axial length are all less, and the loss of himself is less.Totally bring benefit can for gas compressor through the small leaf behind the aerodynamic optimization, make gas compressor have higher efficient and wideer stable operation range.
The above; only for the preferable embodiment of the present invention, but protection scope of the present invention is not limited thereto, and anyly is familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.
Claims (8)
1. a big and small blade impeller that has non-overall height small leaf comprises a plurality of big blades, it is characterized in that, is provided with small leaf between adjacent two described big blades, and the radial height of described small leaf is smaller or equal to 20% of the radial height of described big blade.
2. the big and small blade impeller that has non-overall height small leaf according to claim 1 is characterized in that the radial height of described small leaf equals the 3%-15% of the radial height of big blade.
3. the big and small blade impeller that has non-overall height small leaf according to claim 1 and 2 is characterized in that the axial chord length of described small leaf is the 30%-85% of the axial chord length of described big blade.
4. the big and small blade impeller that has non-overall height small leaf according to claim 3 is characterized in that the axial chord length of described small leaf is the 45%-70% of the axial chord length of described big blade.
5. according to claim 3 or the 4 described big and small blade impellers that have non-overall height small leaf, it is characterized in that the initial camber line of described small leaf is identical with the middle part camber line of described big blade.
6. the big and small blade impeller that has non-overall height small leaf according to claim 1 and 2 is characterized in that the trailing edge of described small leaf is concordant with described big vane trailing edge.
7. according to claim 1 or the 2 described big and small blade impellers that have non-overall height small leaf, it is characterized in that the trailing edge of described small leaf is leading or lag behind described big vane trailing edge.
8. a gas compressor is characterized in that, comprises the described big and small blade impeller that has non-overall height small leaf of claim 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101784016A CN100494694C (en) | 2007-11-29 | 2007-11-29 | Big and small impeller vane impeller with non-full height small blade and compressor machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101784016A CN100494694C (en) | 2007-11-29 | 2007-11-29 | Big and small impeller vane impeller with non-full height small blade and compressor machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101173672A true CN101173672A (en) | 2008-05-07 |
| CN100494694C CN100494694C (en) | 2009-06-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007101784016A Expired - Fee Related CN100494694C (en) | 2007-11-29 | 2007-11-29 | Big and small impeller vane impeller with non-full height small blade and compressor machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100494694C (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022378A (en) * | 2010-12-23 | 2011-04-20 | 北京航空航天大学 | Small or small vane impeller with blunt trailing edge structure used in vane compressor |
| CN103261699A (en) * | 2010-12-27 | 2013-08-21 | 三菱重工业株式会社 | Impeller for centrifugal compressor |
| CN105673562A (en) * | 2016-01-13 | 2016-06-15 | 西北工业大学 | Small separation blade for stability enhancement of rotor of axial flow compressor |
| US20160186773A1 (en) * | 2014-12-29 | 2016-06-30 | General Electric Company | Axial compressor rotor incorporating splitter blades |
| CN105736460A (en) * | 2014-12-29 | 2016-07-06 | 通用电气公司 | Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN109416050A (en) * | 2016-07-15 | 2019-03-01 | 通用电气公司 | Axial Flow Compressor with current divider blade |
| CN111156201A (en) * | 2019-12-30 | 2020-05-15 | 江汉大学 | Axial flow fan and guide vane thereof |
| CN113653672A (en) * | 2021-08-31 | 2021-11-16 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
-
2007
- 2007-11-29 CN CNB2007101784016A patent/CN100494694C/en not_active Expired - Fee Related
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022378B (en) * | 2010-12-23 | 2012-09-05 | 北京航空航天大学 | Small or small vane impeller with blunt trailing edge structure used in vane compressor |
| CN102022378A (en) * | 2010-12-23 | 2011-04-20 | 北京航空航天大学 | Small or small vane impeller with blunt trailing edge structure used in vane compressor |
| CN103261699B (en) * | 2010-12-27 | 2016-08-03 | 三菱重工业株式会社 | The impeller of centrifugal compressor |
| CN103261699A (en) * | 2010-12-27 | 2013-08-21 | 三菱重工业株式会社 | Impeller for centrifugal compressor |
| US9494160B2 (en) | 2010-12-27 | 2016-11-15 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor impeller |
| CN105736460A (en) * | 2014-12-29 | 2016-07-06 | 通用电气公司 | Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades |
| CN105736461B (en) * | 2014-12-29 | 2019-10-18 | 通用电气公司 | It is incorporated to the Axial Flow Compressor rotor of splitterr vanes |
| CN105736461A (en) * | 2014-12-29 | 2016-07-06 | 通用电气公司 | Axial compressor rotor incorporating splitter blades |
| US20160186773A1 (en) * | 2014-12-29 | 2016-06-30 | General Electric Company | Axial compressor rotor incorporating splitter blades |
| US9874221B2 (en) * | 2014-12-29 | 2018-01-23 | General Electric Company | Axial compressor rotor incorporating splitter blades |
| US9938984B2 (en) | 2014-12-29 | 2018-04-10 | General Electric Company | Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades |
| CN105736460B (en) * | 2014-12-29 | 2020-08-07 | 通用电气公司 | Axial compressor rotor incorporating non-axisymmetric hub flowpath and splitter blades |
| CN105673562A (en) * | 2016-01-13 | 2016-06-15 | 西北工业大学 | Small separation blade for stability enhancement of rotor of axial flow compressor |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN109416050A (en) * | 2016-07-15 | 2019-03-01 | 通用电气公司 | Axial Flow Compressor with current divider blade |
| CN111156201A (en) * | 2019-12-30 | 2020-05-15 | 江汉大学 | Axial flow fan and guide vane thereof |
| CN113653672A (en) * | 2021-08-31 | 2021-11-16 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
| CN113653672B (en) * | 2021-08-31 | 2023-11-10 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100494694C (en) | 2009-06-03 |
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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 | ||
| ASS | Succession or assignment of patent right |
Owner name: CHANGZHOU LANXIANG MACHINERY WORKS |
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| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 100083 NO.37, XUEYUAN ROAD, HAIDIAN DISTRICT, BEIJING CITY TO: 100191 NO.37, XUEYUAN ROAD, HAIDIAN DISTRICT, BEIJING CITY |
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| TR01 | Transfer of patent right |
Effective date of registration: 20100806 Address after: 100191 Haidian District, Xueyuan Road, No. 37, Co-patentee after: Changzhou Lanxiang Machinery Works Patentee after: Beihang University Address before: 100083 Haidian District, Xueyuan Road, No. 37, Patentee before: Beihang University |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090603 Termination date: 20101129 |
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| CF01 | Termination of patent right due to non-payment of annual fee |