CN104763473B - an airfoil - Google Patents

Abstract

The invention relates to an airfoil, which is provided with specific relations of chord length, mounting angle and bending angle and can effectively improve the balance relation of various indexes such as overall efficiency, economic efficiency, mechanical integrity, working life and the like.

Description

an airfoil

technical field

The invention relates to an airfoil, in particular to an airfoil for a turbine rotor, a compressor blade or a pump impeller.

Background technique

For the design of airfoils used as turbine rotors, compressor blades or pump impellers, there are various design requirements so that the turbine rotors, compressor blades or pump impellers can meet the indicators of overall machine efficiency, economic efficiency, mechanical integrity, etc. included design goals. During the working process of turbine rotors, compressor blades or pump impellers, centrifugal force, gas pressure or vibration will generate stress. The existence of stress will affect the working life of turbine rotors, compressor blades or pump impellers, and even cause shutdown in severe cases. Therefore, it is very critical for the design of the airfoil.

There are various improved airfoils, see for example US6190128B1 which discloses a cooled moving blade for a gas turbine having a contoured base portion formed by an elliptical curved surface, and a straight The surface portion, wherein the rectilinear surface portion is provided at the hub portion of the blade which is thermally stressed, can provide stress relief, but the mechanical integrity needs to be improved. EP 0887513 B1 discloses the installation angle and the spine angle of the airfoil of the first-stage turbine blade. However, at constant flow, there is a strong need for compressor designs that can achieve increased efficiency.

Therefore, it is urgent to propose an airfoil that can effectively improve the balanced relationship of various indicators such as overall machine efficiency, economic efficiency, mechanical integrity, and working life.

Contents of the invention

The purpose of the present invention is to provide an airfoil that can effectively improve the balanced relationship of various indicators such as overall machine efficiency, economic efficiency, mechanical integrity, and working life in order to solve the above technical problems.

The technical scheme that the present invention adopts for solving the technical problem is:

From the reference point at the bottom of the airfoil to the point at the far end, it is graduated according to the height. The section of each division of the airfoil is an airfoil, and the chord length, installation Corners and bends, as shown in the table below:

graduation height (mm) Chord length L(mm) Installation angle α(°) Bend angle β(°) A0 0.000 200.000 25.002 20.065 A1 54.026 200.747 31.426 17.375 A2 102.131 201.479 36.152 14.286 A3 162.458 202.748 40.965 12.154 A4 214.464 204.173 43.263 10.028 A5 265.796 205.791 46.121 8.984 A6 319.467 205.159 48.005 7.527

Among them, the connection line between the front and rear edges of the airfoil is called the airfoil chord line, the length of the chord line is called the chord length, the angle between the chord line and the line perpendicular to the longitudinal axis is the installation angle, and the middle arc at the trailing edge The angle between the tangent of the line and the chord is a curved angle, and the data in the table retains three valid figures.

Preferably, the radius of the leading edge is 1-3mm, and the maximum thickness is 15-20mm, wherein, the radius of the inscribed circle at the leading edge of the airfoil is called the leading edge radius, and the diameter of the inscribed circle of the airfoil circumference is called the thickness .

Beneficial effects of the present invention: Compared with the prior art, the airfoil of the improved airfoil of the present invention can effectively improve the balanced relationship of various indicators such as overall machine efficiency, economic efficiency, mechanical integrity, and working life.

Description of drawings

Figure 1 is a height scale of the airfoil of the present invention.

Figure 2 is a schematic illustration of an airfoil with defined characteristic dimensions of the present invention.

The names of the components in the figure are as follows:

Center arc 1, leading edge 2, trailing edge 3, chord length L, leading edge radius r, thickness h, installation angle α, bending angle β

detailed description

The composition structure and working principle of the present invention will be described in detail below in conjunction with the accompanying drawings.

Figure 1 enumerates the arbitrary graduations of the airfoil continuing from the reference point A0 at the bottom end to the point A6 at the far end, and the section of each graduation of the airfoil is an airfoil.

Fig. 2 is used to exemplarily define the terms chord length L, installation angle, bending angle β, leading edge radius r, and thickness h used in defining the airfoil.

As shown in Figure 2, the middle arc 1 is the line connecting the center of the inscribed circle around the airfoil called the middle arc. Leading edge 2 refers to the frontmost point of the arc in the airfoil called the leading edge of the airfoil. Trailing edge 3 refers to the last point of the arc in the airfoil called the trailing edge. The connection between the front and rear edges of the airfoil is called the airfoil chord, and the length of the chord is called the chord length L. The radius of the inscribed circle at the leading edge of the airfoil is called the leading edge radius r. The diameter of the inscribed circle of the airfoil circumference is called the thickness h. The angle between the chord line and the line L2 perpendicular to the longitudinal axis L1 is the installation angle α. The included angle between the tangent line of the middle arc ₁ at the rear edge and the chord line is the bending angle β.

According to the height scale, the airfoil has the chord length L, installation angle α and bending angle β as listed in Table 1, wherein the data in Table 1 retains three decimal places. The radius of the leading edge is 1-3mm, and the maximum value of the thickness h is 15-20mm.

graduation height (mm) Chord length L(mm) Installation angle α(°) Bend angle β(°) A0 0.000 200.000 25.002 20.065 A1 54.026 200.747 31.426 17.375 A2 102.131 201.479 36.152 14.286 A3 162.458 202.748 40.965 12.154 A4 214.464 204.173 43.263 10.028 A5 265.796 205.791 46.121 8.984 A6 319.467 205.159 48.005 7.527

Although the content disclosed and described herein is regarded as the most practical typical embodiment, it is not a limitation to the protection scope of the present invention. Those skilled in the art should understand that on the basis of the technical solution of the present invention, those skilled in the art Various modifications or deformations that can be made by personnel without creative efforts are still within the protection scope of the present invention.

Claims (3)

1. An airfoil, characterized in that: from the reference point (A0) at the bottom of the airfoil to the point (A6) at the far end, it is indexed according to height, and the section of each index of the airfoil is a Airfoil, the chord length (L), installation angle (α) and bend angle (β) of said airfoil at multiple divisions, as shown in the table below: graduation height (mm) Chord length L(mm) Installation angle α(°) Bend angle β(°) A0 0.000 200.000 25.002 20.065 A1 54.026 200.747 31.426 17.375 A2 102.131 201.479 36.152 14.286 A3 162.458 202.748 40.965 12.154 A4 214.464 204.173 43.263 10.028 A5 265.796 205.791 46.121 8.984 A6 319.467 205.159 48.005 7.527 Among them, the connection between the front and rear edges of the airfoil is called the airfoil chord, the length of the chord is called the chord length (L), and the angle between the chord and the line (L2) perpendicular to the longitudinal axis (L1) is the installation angle (α), the angle between the tangent line of the central arc (1) at the rear edge and the chord line is the bending angle (β), and the data in the table retains three valid figures. 2. An airfoil according to claim 1, characterized in that: the radius of the leading edge is 1-3mm, the maximum value of the thickness (h) is 15-20mm, wherein the inscribed circle at the leading edge of the airfoil The radius is called the leading edge radius, and the diameter of the inscribed circle of the airfoil circumference is called the thickness (h). 3. An airfoil according to claim 1 or 2, characterized in that the airfoil is used for a turbine rotor, a compressor blade or a pump impeller.