CN209228701U - A kind of high-pressure shaft flowing tune fan blade - Google Patents
A kind of high-pressure shaft flowing tune fan blade Download PDFInfo
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- CN209228701U CN209228701U CN201821679829.9U CN201821679829U CN209228701U CN 209228701 U CN209228701 U CN 209228701U CN 201821679829 U CN201821679829 U CN 201821679829U CN 209228701 U CN209228701 U CN 209228701U
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Abstract
It is flowed the utility model discloses a kind of high-pressure shaft and adjusts fan blade, which is the vanelets after modelling, amplifies to obtain practical blade profile according to practical blower machine number.Blade is divided into 12 sections by the blade profile from from wheel hub to wheel rim, chord length, laying angle and the meanline curvature radius with each section of variation of blade height ratio meet quadratic function relation.And blade by etc. circular rectors design, the blade design suitable for different wheel hub ratios.
Description
Technical field
The utility model belongs to axial flow blower field, is related to a kind of blade of high pressure liter aerofoil section, which belongs to wind
Blower is adjusted in machine important composition component, the ancillary equipment axis flowing for being particularly suitable for fired power generating unit.
Background technique
Axial flow blower is a kind of most commonly seen ventilating machinary of fan industry, is widely used in the industries such as industry, agricultural
Ventilation is supplied gas, and is adjusted blower to there is pressure the ancillary equipment axis flowing of fired power generating unit at present and is risen that insufficient stall is premature asks
Topic is unfavorable for energy-saving and emission-reduction if the transformation for carrying out complete machine will cause the waste of resource.
Blade has the raising of axial flow fan pressure as axial flow blower main component, blade profile of a high pressure itself
Important meaning, dynamic tune axial flow blower domestic at present is mainly introduced in developed countries, therefore develops the axis stream of a high pressure
Blade profile has important value.
The design parameter of axial-flow fan blade is numerous, and different design parameters has different influences to the pressure liter of blower,
Therefore Rational choice design parameter and its range are significant to the promotion of axial flow fan pressure.
Summary of the invention
The purpose of the present invention is to provide a kind of dynamic tune axial flow blower blade profiles of thermal power station, pass through the design geometric parameters to selection
Number (such as blade profile laying angle, leaf chord length etc.) carries out parametrization improvement, can efficiently solve axial flow fan pressure not
The problem of high and easy more early stall, while the blade design of different wheel hub ratios can be suitable for.
It adjusts axial flow blower machine number greatly since thermal power station is dynamic and model is different, while wheel hub ratio is also inconsistent, the utility model
Blade profile is modeled as the model leaf that hub radius is R1=150mm, is amplified further according to machine actual size.This
Utility model is the chord length b for having chosen model leaf section, laying angle β, meanline curvature radius ρ, aerofoil profile with respect to camberAnd
Relative thicknessAs design geometric parameter, the specific features of the blade are as follows:
By blade by 12 sections are divided into the short transverse from wheel hub to wheel rim, respectively section I, section II,
Section III, section IV, section V, section VI, section VII, section VIII, section Ⅸ, section Ⅹ, section Ⅺ and section Ⅻ.Each section
Chord length, laying angle and the meanline curvature radius in face have following quadratic function relation: b=- with the ratio ν of blade height
15.5ν2+32.3ν+45.8；The ν of β=- 14.42+106ν-19.8；The ν of ρ=2092-444.8ν+284.6；Wherein b indicates section string
Long, β indicates that section laying angle, ρ indicate that meanline curvature radius, υ indicate the ratio variation of blade height: ν=R1/r, R1 are wheel
I radius of radius, that is, section at hub, r are radius at section I~Ⅻ.The aerofoil profile in each section is with respect to camberOn existing camber basis
The upper variation in ± 3% range simultaneously；Meanwhile the relative thickness of aerofoil section I~ⅫBy 11.8%, 9.7%, 8.6%,
8.0%, 7.5%, 7.1%, 6.8%, 6.5%, 6.3%, 6.1%, 6.0%, 5.8% is given.
After the geometric parameter in each section determines, Howell aerofoil profile is selected to obtain each section according to Airfoil Design principle
Specific air foil shape, for the force-bearing situation for improving blade, the centroid for calculating section blade profile is used as the folded point pair cross-section of product to carry out radial direction
Product is folded.Centroid (the C of aerofoil sectionxFor centroid abscissa, Cy is centroid ordinate) it is calculated using following formula:
(xi,yi) be Curve of wing on each point abscissa and
Ordinate
Blade with the above characteristic by etc. circular rectors design, can be generated according to the different designs of blade height ratio ν different
The blade profile of wheel hub ratio.
Detailed description of the invention
Fig. 1 is the utility model blade three-dimensional modeling and section aerofoil profile schematic diagram.
Fig. 2 is the utility model blade profile aerofoil profile parameter schematic diagram.
Fig. 3 is the Howell profile thickness distribution map that the utility model blade is chosen.
Fig. 4 is the coordinate points distribution map that the utility model blade seeks aerofoil section centroid.
Fig. 5 is the folded figure of the utility model blade profile product, folded by cross-section centroid diameter vector product.
Specific embodiment
The utility model technology is described in further detail with reference to the accompanying drawings and examples.
Embodiment 1
Impeller diameter in the implementation case is 2660mm, and wheel hub ratio is 0.6, then hub radius is 798mm, such as Fig. 1 institute
It is shown as blade three-dimensional modeling and section aerofoil profile schematic diagram, blade is divided into 12 sections from wheel hub to from wheel rim, then top section
Blade height ratio ν=0.6 (i.e. the height ratio in section Ⅻ be 0.6), the height ratio point in section I~Ⅻ can be calculated
Not are as follows: 1.0000,0.9636,0.9273,0.8909,0.8545,0.8182,0.7818,0.7455,0.7091,0.6727,
0.6364, 0.6000；Fig. 2 show the geometric parameter of section aerofoil profile, in conjunction with above-mentioned selected geometric parameter with blade height
The functional relation of ratio can each section of computation model blade supplemental characteristic it is as follows:
The chord length in section I is 62.60mm, and laying angle is 71.80 °, and meanline curvature radius is 48.80mm, maximum gauge
For 7.39mm；The chord length in section II is 62.53mm, and laying angle is 68.97 °, and meanline curvature radius is 50.05mm, maximum thick
Degree is 6.07mm；The chord length in section III is 62.42mm, and laying angle is 66.11 °, and meanline curvature radius is 51.85mm, maximum
With a thickness of 5.37mm；The chord length for cutting section IV is 62.27mm, and laying angle is 63.21 °, and meanline curvature radius is 54.21mm,
Maximum gauge is 4.98mm；V chord length is 62.08mm, and laying angle is 60.26 °, and meanline curvature radius is 57.12mm, most
Greatly with a thickness of 4.66mm；The chord length in section VI is 61.85mm, and laying angle is 57.29 °, and meanline curvature radius is 60.58mm,
Maximum gauge is 4.39mm；The chord length in section VII is 61.58mm, and laying angle is 54.27 °, and meanline curvature radius is
64.60mm, maximum gauge 4.19mm；The chord length in section VIII is 61.27mm, and laying angle is 51.22 °, meanline curvature radius
For 69.16mm, maximum gauge 3.98mm；The chord length in section Ⅸ is 60.91mm, and laying angle is 48.12 °, meanline curvature half
Diameter is 74.28mm, maximum gauge 3.84mm；The chord length in section Ⅹ is 60.51mm, and laying angle is 44.99 °, meanline curvature
Radius is 79.96mm, maximum gauge 3.69mm；The chord length in section Ⅺ is 60.08mm, and laying angle is 41.83 °, and middle camber line is bent
Rate radius is 86.18mm, maximum gauge 3.60mm；The chord length in section Ⅻ is 59.60mm, and laying angle is 38.62 °, middle camber line
Radius of curvature is 92.96mm, maximum gauge 2.98mm；
After the geometric parameter in model leaf section determines, it is converted into practical fan blade: the wherein peace in each section
Angle is put to remain unchanged, chord length, middle camber line and maximum gauge accordingly amplify K times (K be case study on implementation axial fan hub radius and model leaf
The ratio of piece hub radius, in this case study on implementation), then profile thickness according to Fig.3, is distributed feelings
Condition carries out profile thickness superposition on the middle camber line in each section of practical blade, obtains the coordinate value of Curve of wing each point, further according to
The distribution map of aerofoil profile coordinate points shown in Fig. 4 and centroid solution formula, are calculated the centroid in each section, and being that product is folded with centroid clicks through
Conduct vector product is folded, and the folded effect of product is as shown in Figure 5.In this case study on implementation, opposite camber keeps original constant, according to the actual situation
Make opposite camber on the basis of now in ± 3% range while changing.
Embodiment 2
It is 3350mm if you need to design impeller diameter, wheel hub is than the axial-flow fan blade for 0.63, then hub radius
Blade is divided into 12 sections, blade height ratio ν=0.63 (the i.e. section of top section by 1055mm from wheel hub to from wheel rim
Ⅻ height ratio be 0.63) can be calculated I~II of section height ratio be respectively as follows: 1.0000,0.9664,0.9327,
0.8991, 0.8655,0.8318,0.7982,0.7645,0.7309,0.6973,0.6636,0.6300；Using case study on implementation 1
In mode obtain after model leaf geometric parameter K times of amplification (in this case study on implementation), practical leaf later
The moulding of piece is identical as case study on implementation 1, is not repeated herein.
Claims (5)
1. fan blade is adjusted in a kind of high-pressure shaft flowing, it is characterised in that the big leaf model of machine number, which is turned to hub radius, is
Blade is divided into 12 sections, respectively section I, section II, section III, section by the blade profile of 150mm from wheel hub to from wheel rim
IV, section V, section VI, section VII, section VIII, section Ⅸ, section Ⅹ, section Ⅺ and section Ⅻ, the geometric parameters in each section
Number meets following quadratic function relation: b=-15.5 ν2+32.3ν+45.8；The ν of β=- 14.42+106ν-19.8；The ν of ρ=2092-
444.8ν+284.6；Wherein b indicates section chord length, and β indicates that section laying angle, ρ indicate that meanline curvature radius, ν indicate blade
The ratio of height changes: ν=R1/r, R1 are wheel hub radius, that is, I radius of section, and r is radius at section I~Ⅻ.
2. fan blade is adjusted in a kind of high-pressure shaft flowing according to claim 1, it is characterised in that: the aerofoil profile phase in each section
The variation in ± 3% range simultaneously on the basis of existing camber to camber.
3. fan blade is adjusted in a kind of high-pressure shaft flowing according to claim 1, it is characterised in that: aerofoil section I~Ⅻ
Relative thickness is respectively 11.8%, 9.7%, 8.6%, 8.0%, 7.5%, 7.1%, 6.8%, 6.5%, 6.3%, 6.1%,
6.0%, 5.8%.
4. fan blade is adjusted in a kind of high-pressure shaft flowing according to claim 1, it is characterised in that: each aerofoil profile is cut
Face remembers that the centroid point of aerofoil section is that space product folds point, as the variation space product of blade height folds point lineal layout.
5. fan blade is adjusted in a kind of high-pressure shaft flowing according to claim 1, it is characterised in that: the blade by etc. circular rectors
Design, the blade profile of different wheel hub ratios can be generated by changing blade height ratio.
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| CN201821679829.9U CN209228701U (en) | 2018-10-17 | 2018-10-17 | A kind of high-pressure shaft flowing tune fan blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111536075A (en) * | 2020-03-25 | 2020-08-14 | 浙江科贸智能机电股份有限公司 | Blade of ventilator and axial flow ventilator thereof |
| CN111677693A (en) * | 2020-05-21 | 2020-09-18 | 同济大学 | High-pressure cooling fan for large-flow low-noise fuel cell automobile |
| CN114829784A (en) * | 2019-12-18 | 2022-07-29 | 三电汽车空调***株式会社 | Centrifugal blower |
| WO2023040417A1 (en) * | 2021-09-18 | 2023-03-23 | 西安热工研究院有限公司 | New moving blade modeling method for energy-saving transformation of axial flow fan with adjustable moving blades of power station |
-
2018
- 2018-10-17 CN CN201821679829.9U patent/CN209228701U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114829784A (en) * | 2019-12-18 | 2022-07-29 | 三电汽车空调***株式会社 | Centrifugal blower |
| CN111536075A (en) * | 2020-03-25 | 2020-08-14 | 浙江科贸智能机电股份有限公司 | Blade of ventilator and axial flow ventilator thereof |
| CN111536075B (en) * | 2020-03-25 | 2024-05-28 | 浙江科贸智能机电股份有限公司 | Blade of ventilator and axial flow ventilator thereof |
| CN111677693A (en) * | 2020-05-21 | 2020-09-18 | 同济大学 | High-pressure cooling fan for large-flow low-noise fuel cell automobile |
| CN111677693B (en) * | 2020-05-21 | 2021-10-08 | 同济大学 | High-pressure cooling fan for large-flow low-noise fuel cell automobile |
| WO2023040417A1 (en) * | 2021-09-18 | 2023-03-23 | 西安热工研究院有限公司 | New moving blade modeling method for energy-saving transformation of axial flow fan with adjustable moving blades of power station |
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