High-performance airfoil for fan

A high-performance, airfoil-shaped technology, applied in the components of pumping devices for elastic fluids, non-variable-capacity pumps, machines/engines, etc., can solve problems such as poor matching, and achieve excellent matching and energy efficiency. High value, low noise effect

Active Publication Date: 2016-02-24
XIN CHANG COUNTRY SAN XIN AIR CONDITIONING FAN CO LTD
7 Cites 6 Cited by

AI-Extracted Technical Summary

Problems solved by technology

[0004] The present invention aims at the situation that the airfoil used by the existing low-speed fan blades does not match well with the actual working conditions, and provides a high-performance fan airf...
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Abstract

The invention relates to a high-performance airfoil for a fan, in particular to a high-performance airfoil for a fan, which is designed by applying an advanced pneumatic analysis technology in an aviation technology according to actual working conditions of low Reynolds number (generally lower than 106) of a small-size and low-rotating-speed fan; the invention discloses a maximum camber and a position thereof of the airfoil, a maximum thickness and a position thereof, an equation satisfied by upper and lower surfaces and an airfoil coordinate; f is the maximum camber; Xf is a transverse coordinate value of the maximum camber of the airfoil; t is the maximum thickness; Xt is a transverse coordinate vale of the maximum thickness of the airfoil; and C is a chord length. An original point of a coordinate system of the airfoil is defined as a front edge point of a middle arc line of the airfoil; an X axle is overlapped with a chord line; the direction is to point to the airfoil back edge from the airfoil front edge; and a Y axle is perpendicular to a direction of bending the X axle to the middle arc line of the airfoil. Under the same working conditions, compared with a traditional fan airfoil, the fan adopting the airfoil is better in matchability with actual working conditions, higher in air volume, lower in noise and higher in energy efficiency value.

Application Domain

Pump componentsPumps +2

Technology Topic

Air volumeEngineering +2

Image

  • High-performance airfoil for fan
  • High-performance airfoil for fan
  • High-performance airfoil for fan

Examples

  • Experimental program(1)

Example Embodiment

[0065] The accompanying drawings disclose an embodiment of the present invention in a non-limiting manner. The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0066] The design principle of the airfoil for a high-performance fan of the present invention is: firstly, in combination with the operating conditions of the low-speed fan, the aerodynamic analysis technology of the aviation industry is adopted to design a high-performance airfoil that matches the actual operating conditions of the fan. Special airfoil for fan. Since the main performance of the airfoil largely depends on the shape of its upper and lower surfaces or mid-curves, especially for low-speed airfoils, the rules of the upper and lower surfaces of the designed high-performance fan-specific airfoils are further studied. The characteristics, the distribution law of the upper and lower surfaces of the high-performance airfoil for fans, the equations and shapes that are satisfied, see figure 1.
[0067] According to the above design principles, the present invention specifically provides an airfoil for high-performance fans, named SXAIRFOIL-1. The specific description of the airfoil is as follows:
[0068] The ratio of the maximum camber f of the airfoil to the chord length C is f/C=8.58%, and the maximum camber position is X f /C=65%.
[0069] The ratio of the maximum thickness t of the airfoil to the chord length C is t/C=9.68%, and the maximum thickness position is X t /C=20%.
[0070] Leading edge radius: 4.6.
[0071] When the chord length is defined as 100, the equation of the upper surface of the airfoil is:
[0072] y=0.003+0.941x-3.335x 2 +5.708x 3 -4.590x 4 +1.275x 5
[0073] When the chord length is defined as 100, the equation of the lower surface of the airfoil is:
[0074] y=-0.001-0.729x+8.048x 2 -34.194x 3 +76.548x 4 -91.812x 5 +55.312x 6 -13.168x 7
[0075] Where X f Is the abscissa value at the maximum camber of the airfoil, X t It is the abscissa value at the maximum thickness of the airfoil. The origin of the coordinate system where the airfoil is defined is the leading edge point of the airfoil, the X axis coincides with the chord line, the direction is from the leading edge of the airfoil to the trailing edge of the airfoil, and the Y axis is vertical It is on the X axis and points in the direction of the arc curve in the airfoil.
[0076] When the chord length of the airfoil is 1, the coordinates corresponding to the upper and lower surfaces of the airfoil are as follows:
[0077] Top surface coordinates:
[0078] 10
[0079] 0.950.02933
[0080] 0.90.050875
[0081] 0.850.06798
[0082] 0.80.080985
[0083] 0.750.09012
[0084] 0.70.09574
[0085] 0.650.09993
[0086] 0.60.1032
[0087] 0.550.10557
[0088] 0.50.10703
[0089] 0.450.107585
[0090] 0.40.107235
[0091] 0.350.10598
[0092] 0.30.10382
[0093] 0.250.100705
[0094] 0.20.094635
[0095] 0.150.08443
[0096] 0.10.06971
[0097] 0.050.046475
[0098] 00
[0099] Bottom surface coordinates:
[0100] 00
[0101] 0.05-0.02381
[0102] 0.1-0.01907
[0103] 0.15-0.01061
[0104] 0.2-0.00215
[0105] 0.250.00631
[0106] 0.30.01477
[0107] 0.350.02323
[0108] 0.40.03169
[0109] 0.450.04015
[0110] 0.50.04861
[0111] 0.550.05707
[0112] 0.60.06552
[0113] 0.650.071575
[0114] 0.70.07342
[0115] 0.750.071085
[0116] 0.80.06453
[0117] 0.850.05361
[0118] 0.90.03807
[0119] 0.950.01751
[0120] 10.

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