CN102943774A - Design method of composite airfoil fan blade - Google Patents
Design method of composite airfoil fan blade Download PDFInfo
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- CN102943774A CN102943774A CN2012102751434A CN201210275143A CN102943774A CN 102943774 A CN102943774 A CN 102943774A CN 2012102751434 A CN2012102751434 A CN 2012102751434A CN 201210275143 A CN201210275143 A CN 201210275143A CN 102943774 A CN102943774 A CN 102943774A
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- 239000002131 composite material Substances 0.000 title claims abstract description 62
- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000007704 transition Effects 0.000 claims description 15
- 239000007787 solid Substances 0.000 claims description 6
- 230000001133 acceleration Effects 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 abstract description 6
- 238000005520 cutting process Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000009966 trimming Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 9
- 230000008859 change Effects 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000011031 large-scale manufacturing process Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 208000031872 Body Remains Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000004512 die casting Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
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Abstract
The invention provides a design method of a composite airfoil fan blade. The method comprises the steps that a standard aerial aerodynamic force airfoil is adopted as an airfoil blade main body of a composite airfoil; the front edge of the airfoil blade main body extends forward for airfoil superposition; or the back edge of the airfoil blade main body extends backward for the airfoil superposition; or the front edge of the airfoil blade main body extends forward and the back edge of the airfoil blade main body extends backward for the airfoil superposition simultaneously; the airfoil superposition is conducted on the suction surface of the airfoil blade main body; and the novel airfoil is composited. The composite airfoil can meet aerodynamic force requirements of different impellers by cutting and trimming a front edge extension airfoil and a back edge extension airfoil, changing a blade angle, changing a relative torsion angle, adjusting blade numbers, changing chord length according to a used calculation flow pattern and a use occasion. The method realizes mass production of blades, is high in generality, is particularly applied to the various fan and minitype wind power industries, and has a very good popularization value.
Description
Technical field
The present invention relates to blower fan wind power technology field, a kind of design method of composite vane type fan blade specifically, namely utilize aviation aerodynamic force standard aerofoil profile to be the airfoil fan main body, leading edge and trailing edge in the airfoil fan main body extend interpolation aerofoil profile generation composite vane type, or add the method that aerofoil profile generates composite vane type at the suction surface of airfoil fan main body.
Background technique
The performance of turbomachinery depends on structure and the shape of turbine-type impeller blade to a great extent; existing wing blades technology often adopts the method for mold pressing, die forging, precision milling, manual shaping to carry out machine shaping; difficulty of processing is large, and fabricating cost is high, is difficult to form large-scale production.In order to solve the making of turbine-type impeller blade, pertinent literature has been introduced extrudate and has been made fan impeller blade, but blade mostly is the axial-flow blower rectangular paddle, and namely blade radial units at different levels level cross section is identical.The patent documentation publication number is the axial type energy-saving fan blade that CN1908444 discloses extrusion and cutting process, blade profile is made of hollow wing blade main body and solid trailing edge, realizes needed flow pattern by different modes cutting, the change number of blade, blade chord length, blades installation angle and the rotating speed of blade trailing edge lagging edge.These documents have solved the calculating flow pattern of some axial-flow blowers, but still come with some shortcomings, because it is more that the turbomachinery impeller blade calculates flow pattern, be classified as substantially three classes on the structure: axial flow, centrifugal, mixed-flow, the blade in the document of front just obviously can not satisfy the engineering design requirement on using.In axial-flow blower when design, is in order to reduce noise, many occasions adopt blade sweepforward structure, because can't adopt the wing blade rectangular paddle that the front document mentions and realize this calculating flow pattern and structure with the wing blades of trailing edge, usually adopt the methods such as precision casting, injection moulding, die casting to realize, like this so that the manufacture cost of blower fan is high, the mould Meteorological is large, and versatility is poor between the different plane No.; And conventional centrifugal, mixed-flow impeller adopt single plate blade more, although simplified preparation process, also causes the consequence that general operational efficiency is low, condition range is narrow, noise is high simultaneously.Although some impeller has adopted wing blades, be limited to by hand more and piece together welding, the aerofoil profile low precision, fabricating cost is high, and is not suitable for large-scale production in enormous quantities.
Summary of the invention
Technical assignment of the present invention is to solve the deficiencies in the prior art, and a kind of design method of composite vane type fan blade is provided.
Technical assignment of the present invention is realized in the following manner: adopt aviation aerodynamic force standard aerofoil profile as the airfoil fan main body, then carry out aerofoil profile stack by leading edge, trailing edge to the airfoil fan main body or carry out the aerofoil profile stack at the suction surface of airfoil fan main body and make the composite vane type blade, this composite vane type blade is in the application of turbomachinery impeller, leaf grating leaf track media carries out twice or three acceleration, effectively reduce flow losses, play simultaneously the reduction noise contributions; Specifically comprise following design
1) the leading edge blade that extends forward of leading edge portion stack in the airfoil fan main body forms the composite vane type blade, and the leading edge vane thickness of stack prolongs by in face of the composite vane type blade pressure less than the airfoil fan body thickness, guarantees the pressure side smooth transition;
2) the trailing edge blade that extends back of rear edge part stack in the airfoil fan main body forms the composite vane type blade, and the trailing edge vane thickness of stack by prolonging behind the composite vane type blade pressure surface, guarantees the pressure side smooth transition less than the airfoil fan body thickness;
3) at the leading edge portion of airfoil fan main body and rear edge part superpose respectively leading edge blade and trailing edge blade, form the composite vane type blade, the leading edge blade of stack and the thickness of trailing edge blade are all less than the thickness of airfoil fan main body, by prolong in face of the composite vane type blade pressure and after prolong, guarantee whole pressure side smooth transition;
4) auxiliary surface that superposes of the suction surface on airfoil fan main body top forms auxiliary airfoil fan, by the stack auxiliary surface, the blade suction surface curve is modified;
5) auxiliary surface that superposes of the suction surface on leading edge blade that extends forward of the leading edge portion of airfoil fan main body stack, trailing edge blade that extends back of rear edge part stack and top forms auxiliary airfoil fan;
6) leading edge blade, trailing edge blade and the auxiliary surface section bar that is used for stack adopts the structural type of empty solid or hollow, when the composite vane type vane section bar adopted hollow structure, hole shape was D type beam, I-shape beam, slotted hole, circular hole, the combination of one or more shapes in tri-angle-holed;
7) leading edge blade, trailing edge blade and auxiliary surface adopt aluminium section bar integral drawing technique processing procedure as the combination of Split type structure and airfoil fan main body or connect by tenon structure or employing articulated joint.
Method of the present invention has following outstanding beneficial effect: by aviation aerodynamic force standard aerofoil profile is carried out the compound blade composite vane type that obtains, the turbomachinery impeller blade that utilizes composite vane type to make can better meet hydromechanical engineering calculation, so that the easier realization of mass, Extraordinary design.
1) outstanding effect is to become general blade in the application of different turbo wheel blades, both can be used as prismatic rectangular paddle, and the blade that also can be used as variable cross section, change aerofoil profile uses, and blade generalization degree is high.
2) the relative torsional angle of blade at the turbomachinery impeller can be 0, namely without the blade structure of torsional angle, also can adopt torsional angle frock clamping equipment that blade is carried out torsional angle, makes blade that certain relative torsional angle be arranged, so that impeller blade better meets the engineering calculation flow pattern.
3) material of vane section bar can be according to the difference of medium, environmental conditions and difference.Can be divided into metallic material, nonmetallic material, composite material.
Description of drawings
Accompanying drawing 1 is the structural representation of airfoil fan main body leading edge stack leading edge blade;
Accompanying drawing 2 is the structural representation of airfoil fan main body trailing edge stack trailing edge blade;
Accompanying drawing 3 is the structural representation of superpose respectively before and after the airfoil fan main body leading edge blade and trailing edge blade;
Accompanying drawing 4 is the structural representation of the auxiliary page of airfoil fan main body top suction surface stack;
Accompanying drawing 5 is superpose the respectively structural representation of leading edge blade, trailing edge blade and the auxiliary page of before and after the airfoil fan main body and top;
Mark in the accompanying drawing represents respectively: airfoil fan main body 1, leading edge blade 2, trailing edge blade 3, the auxiliary page 4.
Embodiment
With reference to Figure of description and specific embodiment the method that the present invention is based on the general composite vane type of aviation aerodynamic force standard aerofoil profile generation turbomachinery is done following explanation, but do not limit the present invention in any way.
The present invention adopts aviation aerodynamic force standard aerofoil profile as the airfoil fan main body, then carry out aerofoil profile stack by leading edge, trailing edge to the airfoil fan main body or carry out the aerofoil profile stack at the suction surface of airfoil fan main body and make the composite vane type blade, this composite vane type blade is in the application of turbomachinery impeller, leaf grating leaf track media carries out twice or three acceleration, effectively reduce flow losses, play simultaneously the reduction noise contributions; The specific design method is as follows:
1) the leading edge blade that extends forward of leading edge portion stack in the airfoil fan main body forms the composite vane type blade, and the leading edge vane thickness of stack prolongs by in face of the composite vane type blade pressure less than the airfoil fan body thickness, guarantees the pressure side smooth transition;
2) the trailing edge blade that extends back of rear edge part stack in the airfoil fan main body forms the composite vane type blade, and the trailing edge vane thickness of stack by prolonging behind the composite vane type blade pressure surface, guarantees the pressure side smooth transition less than the airfoil fan body thickness;
3) at the leading edge portion of airfoil fan main body and rear edge part superpose respectively leading edge blade and trailing edge blade, form the composite vane type blade, the leading edge blade of stack and the thickness of trailing edge blade are all less than the thickness of airfoil fan main body, by prolong in face of the composite vane type blade pressure and after prolong, guarantee whole pressure side smooth transition;
4) auxiliary surface that superposes of the suction surface on airfoil fan main body top forms auxiliary airfoil fan, by the stack auxiliary surface, the blade suction surface curve is modified;
5) auxiliary surface that superposes of the suction surface on leading edge blade that extends forward of the leading edge portion of airfoil fan main body stack, trailing edge blade that extends back of rear edge part stack and top forms auxiliary airfoil fan;
6) leading edge blade, trailing edge blade and the auxiliary surface section bar that is used for stack adopts the structural type of empty solid or hollow, when the composite vane type vane section bar adopted hollow structure, hole shape was D type beam, I-shape beam, slotted hole, circular hole, the combination of one or more shapes in tri-angle-holed;
7) leading edge blade, trailing edge blade and auxiliary surface adopt aluminium section bar integral drawing technique processing procedure as the combination of Split type structure and airfoil fan main body or connect by tenon structure or employing articulated joint.
Embodiment 1: the generation of composite vane type
Composite vane type generating mode of the present invention is divided into following six classes:
1. leading edge superimposion aerofoil profile: as the airfoil fan main body, and the leading edge of airfoil fan main body extended the stack aerofoil profile with the standard aerofoil profile, stack aerofoil profile and airfoil fan main body pressure side molded line are matched, i.e. the wing
The pressure side molded line radius of curvature of type blade body pressure side molded line radius of curvature and stack aerofoil profile is tangent at the binding site place, the maximum ga(u)ge of stack aerofoil profile is less than the maximum ga(u)ge of airfoil fan main body, on the suction surface with airfoil fan main body molded line and stack aerofoil profile molded line smooth transition.
2. trailing edge superimposion aerofoil profile: with the standard aerofoil profile as the airfoil fan main body, and the trailing edge of airfoil fan main body extended the stack aerofoil profile, stack aerofoil profile and airfoil fan main body pressure side molded line are matched, the pressure side molded line radius of curvature that is airfoil fan main body pressure side molded line radius of curvature and stack aerofoil profile is tangent at the binding site place, the maximum ga(u)ge of stack aerofoil profile is less than the maximum ga(u)ge of airfoil fan main body, on the suction surface with airfoil fan main body molded line and stack aerofoil profile molded line smooth transition.
3. trailing edge stack bent plate composite vane type: with the standard aerofoil profile as the airfoil fan main body, and the trailing edge of airfoil fan main body extended stack bent plate aerofoil profile, bent plate aerofoil profile and the airfoil fan main body pressure side molded line of stack are matched, the pressure side molded line radius of curvature that is airfoil fan main body pressure side molded line radius of curvature and stack bent plate aerofoil profile is tangent at the binding site place, on the suction surface with airfoil fan main body molded line and stack bent plate aerofoil profile molded line smooth transition.
4. leading edge, trailing edge superimposion aerofoil profile: with the standard aerofoil profile as the airfoil fan main body, and leading edge, the trailing edge of airfoil fan main body extended the stack aerofoil profile, stack aerofoil profile and airfoil fan main body pressure side molded line are matched, the pressure side molded line radius of curvature that is airfoil fan main body pressure side molded line radius of curvature and stack aerofoil profile is tangent at the binding site place, the maximum ga(u)ge of stack aerofoil profile is less than the maximum ga(u)ge of airfoil fan main body, on the suction surface with airfoil fan main body molded line and stack aerofoil profile molded line smooth transition.
5. leading edge stack aerofoil profile, trailing edge stack bent plate composite vane type: with the standard aerofoil profile as the airfoil fan main body, and to the leading edge of airfoil fan main body, trailing edge extends the stack aerofoil profile, leading edge extension stack standard aerofoil profile, trailing edge extension stack bent plate aerofoil profile, stack aerofoil profile and airfoil fan main body pressure side molded line are matched, the pressure side molded line radius of curvature that is airfoil fan main body pressure side molded line radius of curvature and stack aerofoil profile is tangent at the binding site place, the maximum ga(u)ge of stack aerofoil profile is less than the maximum ga(u)ge of airfoil fan main body, on the suction surface with airfoil fan main body molded line and stack aerofoil profile molded line smooth transition.
6. suction surface superimposion aerofoil profile: with the standard aerofoil profile as the airfoil fan main body, in the suction surface of the theme aerofoil profile aerofoil profile that superposes, the pressure side molded line of composite vane type is that the pressure side molded line of airfoil fan main body remains unchanged, on the suction surface with airfoil fan main body molded line and stack aerofoil profile molded line smooth transition.Embodiment 2: select the type of composite vane type, and definite section form
(1) according to the definite aerofoil profile molded line that adopts composite vane type of engineering calculation flow pattern.
(2) the composite vane type sectional dimension is little, can select the composite vane type solid construction when perhaps considering the conditions such as blade is wear-resisting, intensity, rigidity,
When (3) the composite vane type sectional dimension is larger, satisfying under the conditions such as blade strength, rigidity, can select multi-form hollow section structure.
When (4) the composite vane type sectional dimension was larger, the also blade profile structure of attachable type: can be articulation structure, also can be tenon structure,
Embodiment 3: the vane section bar material
Medium (occasion) difference applicable according to impeller blade selected different materials.Blade material can be metallic material, nonmetallic material, composite material.
Embodiment 4: the vane section bar moulding
By push, extrude, the method for drawing produces the composite vane type vane section bar
Embodiment 5: make blade with vane section bar
Choose vane section bar according to the engineering calculation flow pattern, and press the intercepting of blade Len req as the blade woolen cloth.
According to leading edge, the trailing edge thin wing of the leaf milling blade of blade, and repair.
Adjust the relative torsional angle of blade, make it to satisfy engineering calculation.
Being connected between blade and card or the wheel hub, can be different according to turbo wheel Placement multi-form, unlike material, can adopt Placement: riveted joint, welding, rivet welding, bolt connect, bonding.
Embodiment 6: utilize composite vane type to generate the material method of leaf type:
According to the performance requirement of different purposes turbomachinery impellers with calculate the molded line structure that flow pattern is selected composite vane type, and determine the cross section structure of composite vane type according to use occasion, then by push, extrude, the method for drawing produces the composite vane type vane section bar.
The vane section bar cross section structure is divided into: solid composite aerofoil profile, full Hollow Compound aerofoil profile, the composite vane type with center hole, the Hollow Compound aerofoil profile with stiffening rib, the composite vane type of Split type structure.
The blade profile structure is that the Split type structure formula can adopt tenon structure, articulation structure.
Add man-hour at vane section bar, the vane section bar cross section structure will be followed following technical requirements:
1) the aviation aerodynamic force standard aerofoil profile that the occasion of using according to impeller is selected to adapt with it when needing to consider that the ratio of lift coefficient to drag coefficient coefficient is high, also will be considered structural strength, rigidity and Placement as airfoil fan main body and stack aerofoil profile.
2) the pressure center excursion of composite vane type blade should drop on the place ahead of center of gravity, guarantees the stability of blade when working conditions change.
3) the blade profile structure will be selected different structures according to the difference of applicable situation, when selecting hollow-core construction, different hollow-core constructions is set according to the characteristics of material, intensity, rigidity, so that stock utilization is the highest, structure is the lightest, technology capability is best.
Claims (1)
1. the design method of a composite vane type fan blade, it is characterized in that, adopt aviation aerodynamic force standard aerofoil profile as the airfoil fan main body, then carry out aerofoil profile stack by leading edge, trailing edge to the airfoil fan main body or carry out the aerofoil profile stack at the suction surface of airfoil fan main body and make the composite vane type blade, this composite vane type blade is in the application of turbomachinery impeller, leaf grating leaf track media carries out twice or three acceleration, effectively reduces flow losses, plays simultaneously the reduction noise contributions; Specifically comprise following design:
1) the leading edge blade that extends forward of leading edge portion stack in the airfoil fan main body forms the composite vane type blade, and the leading edge vane thickness of stack prolongs by in face of the composite vane type blade pressure less than the airfoil fan body thickness, guarantees the pressure side smooth transition;
2) the trailing edge blade that extends back of rear edge part stack in the airfoil fan main body forms the composite vane type blade, and the trailing edge vane thickness of stack by prolonging behind the composite vane type blade pressure surface, guarantees the pressure side smooth transition less than the airfoil fan body thickness;
3) at the leading edge portion of airfoil fan main body and rear edge part superpose respectively leading edge blade and trailing edge blade, form the composite vane type blade, the leading edge blade of stack and the thickness of trailing edge blade are all less than the thickness of airfoil fan main body, by prolong in face of the composite vane type blade pressure and after prolong, guarantee whole pressure side smooth transition;
4) auxiliary surface that superposes of the suction surface on airfoil fan main body top forms auxiliary airfoil fan, by the stack auxiliary surface, the blade suction surface curve is modified;
5) auxiliary surface that superposes of the suction surface on leading edge blade that extends forward of the leading edge portion of airfoil fan main body stack, trailing edge blade that extends back of rear edge part stack and top forms auxiliary airfoil fan;
6) leading edge blade, trailing edge blade and the auxiliary surface section bar that is used for stack adopts the structural type of empty solid or hollow, when the composite vane type vane section bar adopted hollow structure, hole shape was D type beam, I-shape beam, slotted hole, circular hole, the combination of one or more shapes in tri-angle-holed;
7) leading edge blade, trailing edge blade and auxiliary surface adopt aluminium section bar integral drawing technique processing procedure as the combination of Split type structure and airfoil fan main body or connect by tenon structure or employing articulated joint.
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| CN201210275143.4A CN102943774B (en) | 2012-08-06 | 2012-08-06 | A kind of design method of composite airfoil fan blade |
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| CN201210275143.4A CN102943774B (en) | 2012-08-06 | 2012-08-06 | A kind of design method of composite airfoil fan blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104613006A (en) * | 2014-12-10 | 2015-05-13 | 张凤荣 | Wing sectional material combination type turbine centrifugal impeller |
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| CN2405053Y (en) * | 1998-11-10 | 2000-11-08 | 王茹 | Vane of axial-flow electric fan |
| CN101975146A (en) * | 2010-11-12 | 2011-02-16 | 湖南工程学院 | Hybrid wing blade of wind-driven generator |
| JP2011032991A (en) * | 2009-08-05 | 2011-02-17 | Showa Furyoku Kikai Kk | Mixed flow fan including airfoil blade |
| CN202326408U (en) * | 2011-11-29 | 2012-07-11 | 冀东日彰节能风机制造有限公司 | Efficient centrifugal ventilator blade structure |
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2012
- 2012-08-06 CN CN201210275143.4A patent/CN102943774B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2299010A (en) * | 1939-08-15 | 1942-10-13 | Aircooled Motors Corp | Fan construction for air-cooled engines |
| GB689073A (en) * | 1949-02-15 | 1953-03-18 | Kloeckner Humboldt Deutz Ag | Improvements in rotary blowers |
| PL121750B1 (en) * | 1978-07-10 | 1982-05-31 | Luft U Kaeltetechnik Veb K | Radial flow impeller |
| CN2311647Y (en) * | 1997-11-03 | 1999-03-24 | 朱亚芳 | Blade of fan |
| CN2405053Y (en) * | 1998-11-10 | 2000-11-08 | 王茹 | Vane of axial-flow electric fan |
| JP2011032991A (en) * | 2009-08-05 | 2011-02-17 | Showa Furyoku Kikai Kk | Mixed flow fan including airfoil blade |
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| CN104613006A (en) * | 2014-12-10 | 2015-05-13 | 张凤荣 | Wing sectional material combination type turbine centrifugal impeller |
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Effective date of registration: 20231212 Address after: 212200 Lianhe village, Xinba Town, Yangzhong City, Zhenjiang City, Jiangsu Province Patentee after: ZHENJIANG HUAYANG ROLLING STOC Address before: Room 402, Unit 1, Building 5, Zhongjian Huafu Community, Sanba East Road, Decheng District, Dezhou City, Shandong Province, 253074 Patentee before: Wang Shuqin |