CN203321756U

CN203321756U - Medium-thickness airfoil blade for large turbines

Info

Publication number: CN203321756U
Application number: CN2013203066603U
Authority: CN
Inventors: 周文明; 代海涛
Original assignee: Guodian United Power Technology Co Ltd
Current assignee: Guodian United Power Technology Co Ltd
Priority date: 2013-05-30
Filing date: 2013-05-30
Publication date: 2013-12-04
Anticipated expiration: 2023-05-30

Abstract

The utility model relates to a medium-thickness airfoil blade for large turbines. The outline of the middle cross section of the blade includes a front edge, a tail edge, a suction surface line and a pressure surface line; the distance between the front edge and the tail edge is chord length; the maximum thickness of the cross section is 25-35% of the chord length; the distance between the maximum-thickness part and the front edge is 25-35% of the chord length; the maximum camber of the cross section is 2.0-3.0% of the chord length; the distance between the maximum-camber part and the front edge is 75-85% of the chord length; the radius of the front edge is 5.5-7.5% of the chord length; the end thickness of the tail edge is 0-3% of the chord length. The medium-thickness airfoil blade is better than the same-relative-thickness traditional DU and NACA airfoils in overall performance; wind utilization rate is increased; the structural weight is reduced; fatigue load is reduced, and important technical basis for the development of efficient low-cost wind turbines is provided.

Description

A kind of intermediate gauge airfoil fan of large fan

Technical field

The utility model relates to wind power generation field, particularly relates to a kind of intermediate gauge airfoil fan of large fan.

Background technique

Along with the energy and environmental problem become increasingly conspicuous, abundant, the pollution-free and reproducible wind energy of reserves is subject to people's attention gradually.The core component of wind-powered electricity generation unit-----blade has the aerofoil section of different-thickness and torsional angle distribution, and the aeroperformance of its aerofoil profile and the operational efficiency of complete machine and reliability are closely related.Early stage wind energy conversion system when blade design first-selection be the development comparative maturity, lifting resistance characteristic aviation aerofoil profile preferably, but the design that facts have proved this class aerofoil profile is not well positioned to meet fan design and usage requirement, as for the Stall Type wind energy conversion system, can produce too high peak energy and peak load in stall zone, not only damaged generator, and increased the weight of the load of blade, reduced the life-span of blade, simultaneously because wind energy conversion system is worked for a long time in the wild, be subject to sand and dust, the effect such as raindrop blade surface roughness increases, Airfoil Aerodynamic Performance worsens rapidly the energy loss caused can reach 20%-30%.

The research work of current domestic Special Airfoil of Wind Turbine is at the early-stage, Some Domestic blade factory can only survey and draw the fan blade of external production imitated, in default of geometry and the pneumatic performance data of aerofoil profile, directly affected the autonomous Design level of Chinese large-sized wind energy conversion system.Therefore how to found that a kind of wind energy utilization efficiency is high, the new intermediate gauge aerofoil profile fan blade of lightweight construction, the task of top priority of China's wind energy conversion system development.

The model utility content

The technical problems to be solved in the utility model is to provide a kind of intermediate gauge airfoil fan of large fan, its weight attenuating, blower fan combination property is improved, thereby overcome the deficiency that existing structure weight is heavy, wind energy utilization is low.

For solving the problems of the technologies described above, the utility model provides a kind of intermediate gauge airfoil fan of large fan, wherein the external frame of cross section is divided into leading edge, trailing edge, suction surface molded line and pressure side molded line, the distance of leading edge and trailing edge is chord length, the 25%-35% that the maximum ga(u)ge of described cross section is chord length, the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length; The 2.0%-3.0% that the maximum camber of described cross section is chord length, the distance of maximum camber place and leading edge is the 75%-85% of chord length; The 5.5%-7.5% that the radius of described leading edge is chord length, the 0%-3% that the end surface thickness of described trailing edge is chord length.。

As a kind of improvement of the present utility model, the utility model also can be realized by following proposal:

A kind of intermediate gauge airfoil fan of large fan, wherein, described maximum ga(u)ge is 30% of chord length, the distance of maximum ga(u)ge place and leading edge is 27.7% of chord length, maximum camber is 2.57% of chord length, the distance of maximum camber place and leading edge is 78.3% of chord length, and leading-edge radius is chord length 6.55%, and the trailing edge end surface thickness is chord length 1.3%.

A kind of intermediate gauge airfoil fan of large fan, wherein, described pressure side molded line and suction surface molded line are Bezier curve.

After adopting such design, the utility model at least has the following advantages:

1, this programme provides traditional DU, the NACA aerofoil profile that the vane airfoil profile that relative thickness is 30% (called after UP30) combination property is better than identical relative thickness, than traditional DU91-W-250 combination property, improves 2.3%.

2, new aerofoil profile has not only improved wind energy utilization efficiency, and has alleviated structure weight, has reduced fatigue load, has become the important technical basis of the low-cost wind energy conversion system of development Large Efficient.

The accompanying drawing explanation

Above-mentioned is only the general introduction of technical solutions of the utility model, and in order to better understand technological means of the present utility model, below in conjunction with accompanying drawing and embodiment, the utility model is described in further detail.

Fig. 1 is the leaf central part cross-sectional structure schematic diagram of the intermediate gauge airfoil fan of a kind of large fan of the utility model.

Fig. 2 is the partial enlarged drawing of trailing edge in Fig. 1.

The cross section external frame plotted curve of the intermediate gauge airfoil fan that Fig. 3 is a kind of large fan of the utility model.

Fig. 4 is the intermediate gauge airfoil fan of a kind of large fan of the utility model and the lift coefficient comparison diagram of DU97-W-300.

Fig. 5 is the intermediate gauge airfoil fan of a kind of large fan of the utility model and the ratio of lift coefficient to drag coefficient comparison diagram of DU97-W-300.

Embodiment

With reference to Fig. 1, Fig. 2, the utility model provides the vane airfoil profile that relative thickness is 30% (called after UP30), the intermediate gauge airfoil fan of large fan that the utility model provides, wherein the external frame of cross section mainly consists of leading edge 1, trailing edge 2, suction surface molded line 3 and pressure side molded line 4, wherein leading edge 1 is circular arc, leading edge 1 is connected with suction surface molded line 3, pressure side molded line 4 respectively, the curvature at tie point place is continuous, and suction surface molded line 3 ends 11 are connected to form trailing edge 2 with pressure side molded line 4 ends 13.

At first, the title of each several part in Fig. 1 is defined as follows:

1, mean camber line 10: do the incircle of a series of suction surface molded line 3 and pressure side molded line 4 in aerofoil profile, the line of these incenters is called the mean camber line 10 of aerofoil profile.

2, chord length: the line of mean camber line 10 rear and front end points is called wing chord, and the length of wing chord is called for short chord length.

3, camber C: the maximum normal distance between mean camber line 10 and wing chord is called the maximum camber of aerofoil profile, is called for short camber, and it is called relative maximum camber with the ratio of chord length.

4, leading-edge radius: the apothem of the leading edge 1 by aerofoil profile is called leading-edge radius, and it is called relative leading-edge radius with the ratio of chord length.

5, maximum ga(u)ge D: in the aerofoil profile incircle, maximum inscribe diameter of a circle is called the maximum ga(u)ge of aerofoil profile, and it is called relative maximum ga(u)ge with the ratio of chord length.

6, maximum ga(u)ge position: along wing chord by leading edge point to the maximum ga(u)ge place the distance be called the maximum ga(u)ge position, it is called relative maximum ga(u)ge position with the ratio of chord length.

7, maximum camber position: by leading edge point to maximum camber place chordwise the distance be called the maximum camber position, it is called relative maximum camber position with the ratio of chord length.

8, the trailing edge end face 12: the line segment that the end 11 of suction surface molded line 3 and the end of pressure side molded line 4 13 lines form is trailing edge end face 12, and its thickness becomes relative trailing edge end surface thickness with the ratio of chord length.

Shown in Fig. 3, pressure side molded line 4 of the present utility model and suction surface molded line 3 adopts be the Bezier(shellfish hereby) curve, the geometric data of the aerofoil profile (UP30) that the relative thickness of this programme design is 30% is as follows:

The scope of UP30 each several part parameter value:

Through experimental verification repeatedly, most preferred embodiment data of the present utility model are as follows:

The Design of Aerodynamic Configuration that according to geometry and the pneumatic performance data of above-mentioned aerofoil profile, can carry out the large scale wind power machine blade.

The aerodynamic data comparison diagram of UP30 and DU97-W-300 aerofoil profile is shown in reference to Fig. 4, Fig. 5, in figure, y coordinate is respectively lift coefficient and ratio of lift coefficient to drag coefficient, the angle of the line that abscissa is aerofoil profile leading edge and trailing edge and the direction of the wind comes from (unit for °), the aeroperformance of UP30 obviously is better than traditional DU aerofoil profile of stack pile as seen from the figure.The main layout of the utility model large scale wind power machine intermediate gauge airfoil fan is at close blade medium position, this position is the position that blade is mainly exerted oneself, the aerofoil profile of this position of large scale wind power machine blade needs high coefficient of lift combined, high lift-drag ratio, mild stalling characteristics, low roughness receptance, high reynolds number stability, this programme is by the performance of the mode comprehensive assessment aerofoil profile to above-mentioned index parameter weighting, obtained traditional DU, NACA aerofoil profile that combination property is better than identical relative thickness, the reynolds number range of the aerofoil profile operation that the utility model provides is at 3*10 ⁶To 6*10 ⁶.

The above; it is only preferred embodiment of the present utility model; not the utility model is done to any pro forma restriction, those skilled in the art utilize the technology contents of above-mentioned announcement to make a little simple modification, equivalent variations or modification, all drop in protection domain of the present utility model.

Claims

1. the intermediate gauge airfoil fan of a large fan, wherein the external frame of cross section is divided into leading edge, trailing edge, suction surface molded line and pressure side molded line, and the distance of leading edge and trailing edge is chord length, it is characterized in that:

The 25%-35% that the maximum ga(u)ge of described cross section is chord length, the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length;

The 2.0%-3.0% that the maximum camber of described cross section is chord length, the distance of maximum camber place and leading edge is the 75%-85% of chord length;

The 5.5%-7.5% that the radius of described leading edge is chord length, the 0%-3% that the end surface thickness of described trailing edge is chord length.

2. the intermediate gauge airfoil fan of a kind of large fan according to claim 1, it is characterized in that: described maximum ga(u)ge is chord length 30%, the distance of maximum ga(u)ge place and leading edge is 27.7% of chord length, maximum camber is 2.57% of chord length, the distance of maximum camber place and leading edge is 78.3% of chord length, leading-edge radius is 6.55% of chord length, and the trailing edge end surface thickness is chord length 1.3%.

3. the intermediate gauge airfoil fan of a kind of large fan according to claim 1 and 2, it is characterized in that: described pressure side molded line and suction surface molded line are Bezier curve.