CN102163244A - Method for dolphin head-shaped processing of blade leading edge - Google Patents
Method for dolphin head-shaped processing of blade leading edge Download PDFInfo
- Publication number
- CN102163244A CN102163244A CN2010106236077A CN201010623607A CN102163244A CN 102163244 A CN102163244 A CN 102163244A CN 2010106236077 A CN2010106236077 A CN 2010106236077A CN 201010623607 A CN201010623607 A CN 201010623607A CN 102163244 A CN102163244 A CN 102163244A
- Authority
- CN
- China
- Prior art keywords
- blade profile
- leading edge
- globefish
- blade
- original
- 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.)
- Pending
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a method for the dolphin head-shaped processing of blade leading edge, belonging to the field of mechanical device and transportation technology. An original leading edge pressure lateral line in a curve area with an original blade profile leading edge for dolphin head shaping is removed, a convex curve with random curvature radius is smoothly connected with a leading edge top point and with a tangent point of the original blade profile leading edge and a blade profile pressure surface curve, and is also in smooth transitional connection with an original blade profile line at two tangent points; the blade profile, which jointly consists of the convex curve and the original blade profile line outside a dolphin head shaping area and the head of which is similar to dolphin head, is the dolphin head-shaped blade profile resulting from the processing according to the method. The blade profile leading edge processed according to the method of the invention can adapt to larger variation range of angle of attack of airflow; the invention provides a method for the dolphin head-shaped processing of blade profile leading edge, which reduces blade profile loss, improves aerodynamic performance and enhances overall efficiency on the premise that stability margin is not varied, or even increased, and which is particularly suitable for the design of turbine and aerofoil in aviation, aerospace, navigation and industrial energy power field.
Description
Technical field
The present invention relates to a kind of blade inlet edge globefish head dummy disposal route, belong to mechanical hook-up and transportation technology field.
Background technology
Blade profile has a significant impact wing or turbine aeroperformance, is the key that improves wing or turbine performance.Experience development decades, under the pattern of given mean camber line and stack thickness distribution, blade profile develops into arc any polynomial expression, the customization from early stage single circular arc, two circular arc, many circular arcs, be distributed to polynomial expression thickness distribution, thickness customization etc. from early stage NACA blade profile thickness, even directly optimize, instead design, we can say from the thinkable breach of macroscopic aspect and all expected that wing and turbine performance have obtained very big lifting.In the last few years, researchers begin to have in mind details, and find that details factors can produce big influence too, and the leading edge shape field that comes to this: the oval leading edge that has more universal significance is replacing conventional circular leading edge, not only reduce the blade profile total losses, also had good resistance to weathering.
More performance be always the various countries researcher diligent change in the hope of target.On the basis of the above, the researcher also expects to find new leading edge shape so that blade profile has wideer working range.Bionics provides a kind of new approaches for this reason.Dolphin body contour curve is tens million of years evolution results, is to be suitable for the best curve that dolphin moves about in water, and especially nose curve makes dolphin adapt to various maneuvers.If wing or turbine blade profile leading edge adopt analogous shape, will promote its performance.
Summary of the invention
The present invention seeks to improving wing or the turbine blade profile is streamed, and the blade inlet edge globefish head dummy disposal route of a kind of low loss, allowance is provided.
In order to achieve the above object, the inventive method adopts imitative dolphin head molded lines design, guaranteeing under the constant situation of original blade profile suction surface side leading edge elliptic arc, elliptic arc is on the pressure side made amendment, obtain with original blade profile suction surface side leading edge elliptic arc and original blade profile on the pressure side linear light slip over the imitative globefish head dummy pressure face side leading edge curve that crosses.Its specific implementation process is as follows:
Step 1 according to the actual requirements, adopts the method for conventional mean camber line and thickness distribution to determine original blade profile; Wherein, that the mean camber line given way has is single/pair/many circular arcs, polynomial expression or customization, thickness distribution has NACA series or customization, and leading edge be an ellipse (1≤major axis a/ minor axis b＜5);
So far finish the globefish head dummy of blade inlet edge is handled.
Step 1 of the present invention to the described method of step 3 is not only applicable to turbine blade, is equally applicable to the wing and the rotor of aircraft.
Beneficial effect
The present invention is from bionic angle, the fairshaped lower resistance of dolphin head, low loss characteristics are applied in the blade design, this globefish head dummy is handled the blade profile leading edge and done local adjustment to the pressure face direction on the basis of the circular leading edge of tradition, this adjustment makes profile loss littler, and can stand bigger air-flow angle of attack variation scope; Provide under a kind of even prerequisite of improving constant, reduced profile loss, improve aeroperformance, improve the blade inlet edge globefish head dummy disposal route of overall efficiency in stability margin.The present invention is specially adapted to the turbine and the wing design in Aeronautics and Astronautics, navigation and industrial energy power field.
Description of drawings
Fig. 1 is the blade profile synoptic diagram after globefish head dummy of the present invention is handled, and wherein (a) is whole structure figure, (b) is the partial enlarged drawing that blade inlet edge globefish head dummy is handled;
Fig. 2 is the numerical simulation result in the specific embodiment, and wherein (a) handles preceding numerical simulation result for the globefish head dummy, (b) is the numerical simulation result after the globefish head is handled.
Label declaration:
1-blade inlet edge suction side line; 2-leading edge vertex tangent; 3-blade inlet edge pressure side line; Pressure side line after the 4-first globefish head dummy is handled; 5-leading edge pressure face end points tangent line.Pressure side line after the 6-second globefish head dummy is handled.
Embodiment
For objects and advantages of the present invention are described better, content of the present invention is described further below in conjunction with drawings and Examples.
Present embodiment redesigns an axial flow compressor blade blade profile (NACA65 blade profile) according to the described method of summary of the invention, and verifies its action effect with numerical method.The relevant aerodynamic parameter of present embodiment is as follows: import stagnation pressure 103379Pa, outlet static pressure 101325Pa.
The detailed process that present embodiment carries out globefish head dummy improvement processing to the blade profile leading edge is as follows:
Step 1 according to the requirement of turbine design parameter, is determined original NACA65 vane foil and data thereof, shown in Fig. 1 (a);
The compressor impeller that adopts blade inlet edge globefish head dummy disposal route front and back in the present embodiment is carried out two-dimentional CFD numerical simulation, simulation result as shown in Figure 2, therefrom can obtain, blade inlet edge is after the globefish head dummy is handled, the separation of suction surface angular region has obtained inhibition, thereby loss reduces, and the leaf grating aeroperformance is improved.The gained result shows that the blade profile of handling through the globefish head dummy can play drag reduction and reduce the effect that flow-induced is vibrated, and can effectively realize Passive Control, reduces secondary flow loss.
When the radius-of-curvature of described convex curve radius-of-curvature and present embodiment was different, the form of convex curve can also become shown in the pressure face side line 6 after the second leading edge globefish head dummy among Fig. 1 (b) is handled.
The present invention carries out globefish head dummy design to blade profile, can very big limit land productivity with the little characteristics of its leading-edge radius, the globefish head dummy that obtains lower resistance, low loss, good stability is handled blade profile, with effective turbine aeroperformance that improves, the raising overall efficiency.
It should be noted last that above embodiment is only unrestricted in order to technical scheme of the present invention to be described, globefish head dummy of the present invention handle curve do not have only a kind of but can have multiple, so long as the curve in specialized range all belongs to category of the present invention.Although the present invention is had been described in detail with reference to embodiment, those of ordinary skill in the art is to be understood that, technical scheme of the present invention is made amendment or is equal to replacement, do not break away from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of the claim scope of the present invention.
Claims (2)
1. blade inlet edge globefish head dummy disposal route, it is characterized in that: its specific implementation process is as follows:
Step 1 according to the actual requirements, adopts the method for conventional mean camber line and thickness distribution to determine original blade profile;
Step 2, the original blade profile leading edge of determining step 1 is done the curve regions of a globefish correction of the flank shape; This curve regions is two the determined center section leading edge of tangent line molded lines on protophyll molded lines and the protophyll molded lines, wherein the point of contact of a tangent line is on the leading edge summit, be the intersection point of blade mean camber line and leading edge molded lines, the point of contact of another tangent line is exactly oval leading edge of original blade profile and blade profile pressure face contact of a curve point;
Step 3 is removed the original blade inlet edge pressure side line in the determined zone of step 2, with two point of contacts in the smooth Connection Step 2 of convex curve of any radius-of-curvature, and is connected with protophyll molded lines smooth transition at point of contact place; Constitute jointly by the protophyll molded lines beyond this convex curve and the globefish correction of the flank shape zone, its head and a globefish alike blade profile, be this method and handle the globefish head dummy blade profile that obtains;
So far finish the globefish head dummy of blade inlet edge is handled.
2. a kind of blade inlet edge globefish head dummy disposal route according to claim 1, it is characterized in that: step 1 to the described method of step 3 is applicable to turbine blade, also is applicable to the wing and the rotor of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106236077A CN102163244A (en) | 2010-12-30 | 2010-12-30 | Method for dolphin head-shaped processing of blade leading edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106236077A CN102163244A (en) | 2010-12-30 | 2010-12-30 | Method for dolphin head-shaped processing of blade leading edge |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102163244A true CN102163244A (en) | 2011-08-24 |
Family
ID=44464470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010106236077A Pending CN102163244A (en) | 2010-12-30 | 2010-12-30 | Method for dolphin head-shaped processing of blade leading edge |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102163244A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103982462A (en) * | 2014-05-15 | 2014-08-13 | 北京理工大学 | Wavelike jet method for blade trailing edges |
| CN107480392A (en) * | 2017-08-25 | 2017-12-15 | 北京航空航天大学 | A kind of blade shape construction method based on oval heterogeneous deformation |
| CN108121864A (en) * | 2017-12-15 | 2018-06-05 | 北京理工大学 | A kind of horizontal secondary method of flow control of end wall based on vortex generator |
| CN110059414A (en) * | 2019-04-22 | 2019-07-26 | 北京理工大学 | A kind of two-dimentional blade shape construction method of direct control channel |
| CN110594072A (en) * | 2019-05-27 | 2019-12-20 | 合肥工业大学 | Bionic wing-shaped blade |
| CN113051688A (en) * | 2021-04-09 | 2021-06-29 | 中山大学 | Blade profile shape geometry calculation method, device and equipment |
-
2010
- 2010-12-30 CN CN2010106236077A patent/CN102163244A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103252536B (en) * | 2013-05-20 | 2015-01-28 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103982462A (en) * | 2014-05-15 | 2014-08-13 | 北京理工大学 | Wavelike jet method for blade trailing edges |
| CN103982462B (en) * | 2014-05-15 | 2016-03-30 | 北京理工大学 | A kind of waveform jetting method of blade trailing edge |
| CN107480392A (en) * | 2017-08-25 | 2017-12-15 | 北京航空航天大学 | A kind of blade shape construction method based on oval heterogeneous deformation |
| CN107480392B (en) * | 2017-08-25 | 2020-06-09 | 北京航空航天大学 | Blade modeling method based on elliptical non-uniform deformation |
| CN108121864A (en) * | 2017-12-15 | 2018-06-05 | 北京理工大学 | A kind of horizontal secondary method of flow control of end wall based on vortex generator |
| CN108121864B (en) * | 2017-12-15 | 2021-05-25 | 北京理工大学 | End wall transverse secondary flow control method based on vortex generator |
| CN110059414A (en) * | 2019-04-22 | 2019-07-26 | 北京理工大学 | A kind of two-dimentional blade shape construction method of direct control channel |
| CN110059414B (en) * | 2019-04-22 | 2020-09-29 | 北京理工大学 | Two-dimensional blade modeling method for directly controlling channel |
| CN110594072A (en) * | 2019-05-27 | 2019-12-20 | 合肥工业大学 | Bionic wing-shaped blade |
| CN113051688A (en) * | 2021-04-09 | 2021-06-29 | 中山大学 | Blade profile shape geometry calculation method, device and equipment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102163244A (en) | Method for dolphin head-shaped processing of blade leading edge | |
| CN101405504B (en) | Wind turbine rotor blade | |
| CN106446324B (en) | Design method of final-stage twisted blade of large industrial steam turbine | |
| CN102032215B (en) | Method for designing blade type with waveform surface | |
| CN102032213A (en) | Biomimetic processing method for leading edge of blade at end area | |
| CN101923584A (en) | Method for designing special wind turbine airfoil profile and special wind turbine airfoil profile | |
| CN103994195B (en) | Based on the torque converter blades formative method of scholar Koffsky molded line | |
| CN103790639A (en) | Method for edge strip shape modifying of front edge of end area blade of turbine | |
| CN111120401A (en) | Multi-wing centrifugal ventilator blade design method based on NACA wing profile | |
| CN107145677A (en) | A kind of improved geometric parameter Airfoil Design method | |
| CN109229364B (en) | Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region | |
| CN111435399A (en) | Molding method of fan assembly | |
| CN205779470U (en) | A kind of blunt trailing edge wind mill airfoil circulation control device | |
| CN108980103B (en) | Design method of forward multi-wing centrifugal ventilator impeller with inlet winglet | |
| CN113090580B (en) | Centrifugal impeller blade with S-shaped front edge and modeling method thereof | |
| CN204357771U (en) | A kind of metal stiffened edge, fan blade and turbogenerator | |
| CN209441633U (en) | A kind of low reynolds number rotor-blade airfoil | |
| CN105401982A (en) | Tail-stage movable blade body structure for half-rotating-speed nuclear turbine | |
| CN102032214B (en) | Blade leading edge modification method for suppressing separation | |
| CN108304606B (en) | Impeller with chamfer structure | |
| CN109779971B (en) | High-load compressor blade profile radial stacking modeling optimization method based on curvature control | |
| CN204099272U (en) | A kind of low specific-speed centrifugal pump impeller | |
| CN105787217B (en) | A kind of optimum design method of aircraft ripple aerofoil profile | |
| CN100400375C (en) | Aerofoil with blunt tail edge | |
| CN112861321B (en) | Method for molding end wall of axial flow compressor with tandem stator blade profile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20110824 |