CN-117167213-B - Method and apparatus for determining blade shaft position based on airfoil geometry characteristics

CN117167213BCN 117167213 BCN117167213 BCN 117167213BCN-117167213-B

Abstract

The application discloses a method and a device for determining the axial position of a blade based on geometrical profile characteristics of an airfoil, wherein the method comprises the steps of selecting a target section according to the maximum chord length section of the blade, determining the positions of the maximum thickness points of suction surfaces and the positions of the maximum thickness points of pressure surfaces of a plurality of sections of a first section according to the chord length distribution curve, the relative thickness distribution curve and the geometrical profile data of a standard airfoil of the blade and the relative thickness of the standard airfoil of the blade, wherein the first section takes the target section and the blade tip of the blade as boundaries, calculating according to the positions of the maximum thickness points of the suction surfaces and the maximum thickness points of the pressure surfaces of the plurality of sections of the first section, chord lengths and distance information of the plurality of sections and the blade root diameter of the blade to obtain the axial position of the blade of the plurality of sections of the first section, wherein the distance information represents the distance from the section to the blade root of the blade, and the axial position of the blade of the plurality of sections of the second section is calculated according to the chord length distribution curve of the blade and the blade root diameter of the blade.

Inventors

LIAO CAICAI
LIU XIN
QIN ZHIWEN
HU HEWEN
YU LU
LI XINKAI
Zhou Dieming
SUN MANJIE

Assignees

中国华能集团清洁能源技术研究院有限公司
华能海上风电科学技术研究有限公司

Dates

Publication Date: 20260505
Application Date: 20231013

Claims (6)

1. A method of determining a vane shaft position based on airfoil geometry characteristics, comprising: selecting a target section according to the maximum chord length section of the blade; Determining positions of suction surface maximum thickness points and positions of pressure surface maximum thickness points of a plurality of sections of a first section according to the chord length distribution curve, the relative thickness distribution curve, the geometric shape data of a standard airfoil and the relative thickness of the standard airfoil of the blade, wherein the first section takes the target section and the blade tip of the blade as boundaries; Calculating the positions of blade shafts of the sections of the first section according to the positions of the maximum thickness points of the suction surfaces and the maximum thickness points of the pressure surfaces of the sections of the first section, chord lengths and distance information of the sections and the diameters of blade roots of the blades, wherein the distance information represents the distances from the sections to the blade roots of the blades; Calculating blade shaft positions of a plurality of sections of the second section according to the chord length distribution curve of the blade and the root diameter of the blade aiming at the second section of the blade; the calculating, according to the positions of the maximum thickness points of the suction surface and the maximum thickness points of the pressure surface of the multiple sections of the first section, the chord lengths and the distance information of the multiple sections, and the root diameter of the blade, the positions of the blade axes of the multiple sections of the first section, includes: calculating the thickness position information of the pressure surfaces of the sections of the first section according to the maximum thickness point position, chord length and distance information of the pressure surfaces of the sections of the first section and the root diameter of the blade; Calculating suction surface thickness position information of the sections of the first section according to the position, chord length and distance information of the maximum thickness points of the suction surfaces of the sections of the first section and the root diameter of the blade; Calculating the blade axis positions of the multiple sections of the first section according to the pressure surface thickness position information and the suction surface thickness position information of the multiple sections of the first section, wherein the calculating comprises the steps of calculating average thickness information according to the pressure surface thickness position information and the suction surface thickness position information of the multiple sections of the first section, calculating according to a formula (Dr-K_ave (Ri-R1))/(2 x Ci) for the ith section to obtain the blade axis position of the ith section, wherein Dr is the blade root diameter of the blade, K_ave is the average thickness information, ri is the distance from the ith section to the blade root, R1 is the distance from the target section to the blade root, and Ci is the chord of the ith section; wherein, for the second section of the blade, according to the chord length distribution curve of the blade and the root diameter of the blade, calculating the blade axis positions of a plurality of sections of the second section, including: Selecting a plurality of cross-sections at a second section of the blade; Determining the chord lengths of a plurality of sections in the second section according to the chord length distribution curve of the blade, wherein the second section takes the target section and the blade root of the blade as boundaries; And obtaining the positions of blade shafts of the sections in the second section according to the chord lengths of the sections in the second section and the root diameters of the blades, wherein the calculated positions of the blade shafts of the sections are Dr/(2 x Ci) for each section i of the second section.
2. The method of claim 1, wherein determining suction side maximum thickness point locations and pressure side maximum thickness point locations for a plurality of sections of the first section based on the chord length distribution curve, the relative thickness distribution curve, the geometric profile data of the standard airfoil, and the standard airfoil relative thickness of the blade comprises: selecting a plurality of cross-sections at a first section of the blade; determining the relative thicknesses of the sections of the first section according to the chord length distribution curve and the relative thickness distribution curve of the blade; determining maximum thickness point position information of the standard airfoil according to geometric shape data of the standard airfoil, wherein the maximum thickness point position information comprises a pressure surface maximum thickness point position and a suction surface maximum thickness point position; and interpolating to obtain the positions of the maximum thickness points of the suction surfaces and the positions of the maximum thickness points of the pressure surfaces of the sections according to the relative thicknesses of the sections, the relative thicknesses of the standard airfoil sections and the position information of the maximum thickness points of the standard airfoil sections.
3. The method of claim 1, wherein selecting the target section based on the maximum chord section of the blade comprises: selecting the maximum chord length section of the blade as a target section; Or selecting a section with a preset value of the maximum chord length section distance of the blade as a target section.
4. An apparatus for determining a position of a blade axis based on airfoil geometry characteristics, comprising: a selection unit for selecting a target section according to a maximum chord section of the blade; The determining unit is used for determining positions of suction surface maximum thickness points and positions of pressure surface maximum thickness points of a plurality of sections of a first section according to the chord length distribution curve, the relative thickness distribution curve, the geometric shape data of the standard airfoil and the relative thickness of the standard airfoil of the blade, wherein the first section takes the target section and the blade tip of the blade as boundaries; A first calculating unit, configured to calculate blade axis positions of a plurality of sections of the first section according to positions of suction surface maximum thickness points and pressure surface maximum thickness points of the plurality of sections of the first section, chord lengths and distance information of the plurality of sections, and blade root diameters of the blades, where the distance information indicates distances from the sections to blade roots of the blades; A second calculation unit, configured to calculate, for a second section of the blade, a blade axis position of a plurality of sections of the second section according to a chord length distribution curve of the blade and a root diameter of the blade; the calculating, according to the positions of the maximum thickness points of the suction surface and the maximum thickness points of the pressure surface of the multiple sections of the first section, the chord lengths and the distance information of the multiple sections, and the root diameter of the blade, the positions of the blade axes of the multiple sections of the first section, includes: calculating the thickness position information of the pressure surfaces of the sections of the first section according to the maximum thickness point position, chord length and distance information of the pressure surfaces of the sections of the first section and the root diameter of the blade; Calculating suction surface thickness position information of the sections of the first section according to the position, chord length and distance information of the maximum thickness points of the suction surfaces of the sections of the first section and the root diameter of the blade; Calculating the blade axis positions of the multiple sections of the first section according to the pressure surface thickness position information and the suction surface thickness position information of the multiple sections of the first section, wherein the calculating comprises the steps of calculating average thickness information according to the pressure surface thickness position information and the suction surface thickness position information of the multiple sections of the first section, calculating according to a formula (Dr-K_ave (Ri-R1))/(2 x Ci) for the ith section to obtain the blade axis position of the ith section, wherein Dr is the blade root diameter of the blade, K_ave is the average thickness information, ri is the distance from the ith section to the blade root, R1 is the distance from the target section to the blade root, and Ci is the chord of the ith section; the second calculating unit is specifically configured to, for a second section of the blade, calculate, according to a chord length distribution curve of the blade and a root diameter of the blade, blade shaft positions of a plurality of sections of the second section: Selecting a plurality of cross-sections at a second section of the blade; Determining the chord lengths of a plurality of sections in the second section according to the chord length distribution curve of the blade, wherein the second section takes the target section and the blade root of the blade as boundaries; And obtaining the positions of blade shafts of the sections in the second section according to the chord lengths of the sections in the second section and the root diameters of the blades, wherein the calculated positions of the blade shafts of the sections are Dr/(2 x Ci) for each section i of the second section.
5. The device according to claim 4, wherein the determining unit is configured to determine, based on the chord length distribution curve, the relative thickness distribution curve, the geometric profile data of the standard airfoil, and the standard airfoil relative thickness, suction surface maximum thickness point positions and pressure surface maximum thickness point positions of the plurality of sections of the first section: selecting a plurality of cross-sections at a first section of the blade; determining the relative thicknesses of the sections of the first section according to the chord length distribution curve and the relative thickness distribution curve of the blade; determining maximum thickness point position information of the standard airfoil according to geometric shape data of the standard airfoil, wherein the maximum thickness point position information comprises a pressure surface maximum thickness point position and a suction surface maximum thickness point position; and interpolating to obtain the positions of the maximum thickness points of the suction surfaces and the positions of the maximum thickness points of the pressure surfaces of the sections according to the relative thicknesses of the sections, the relative thicknesses of the standard airfoil sections and the position information of the maximum thickness points of the standard airfoil sections.
6. The device according to claim 4, wherein the selection unit is adapted to, when selecting the target section according to the maximum chord section of the blade: selecting the maximum chord length section of the blade as a target section; Or selecting a section with a preset value of the maximum chord length section distance of the blade as a target section.

Description

Method and apparatus for determining blade shaft position based on airfoil geometry characteristics Technical Field The application belongs to the technical field of wind power generation, and particularly relates to a method and a device for determining the position of a blade shaft based on geometrical profile characteristics of an airfoil. Background With the development of the wind power industry, the blades of the wind power generator are longer and longer, the weight is increasing. In order to reduce blade weight as much as possible, improvements and optimization in terms of aerodynamics, structure, materials, loads, etc. are continually needed. Wherein, accurately detect the position of blade axle, have important influence to the aerodynamic appearance and the blade load of blade. Existing methods of determining the position of a blade axis are mainly based on experience, e.g. the position at 30% chord length from the front edge point of the cross-section is typically determined empirically as the position of the blade axis. Meanwhile, in order to ensure the smoothness of the pneumatic shape of the blade, the position of the blade shaft can be manually adjusted. The problem with this approach is that the thickness characteristics of the blade airfoil are ignored, resulting in an excessive deviation between the maximum thickness position of each section of the blade and the determined blade axis position, which may result in a less efficient construction of the main girder. The structural efficiency reflects the relation between the material consumption and the structural strength of the main girder, and when the structural efficiency is lower, the material consumption of the main girder is higher under the requirement of the same structural strength. Therefore, existing methods of determining the position of the blade shaft are disadvantageous in terms of weight saving of the blade. Disclosure of Invention To this end, the present application discloses a method and apparatus for determining the position of a blade shaft based on airfoil geometry characteristics to reduce the weight of the blade. A first aspect of the application provides a method of determining a position of a blade axis based on airfoil geometry characteristics, comprising: selecting a target section according to the maximum chord length section of the blade; Determining positions of maximum thickness points of suction surfaces and positions of maximum thickness points of pressure surfaces of a plurality of sections of a first section according to a chord length distribution curve, a relative thickness distribution curve, geometric shape data of a standard airfoil and the relative thickness of the standard airfoil of the blade, wherein the first section takes a target section and the blade tip of the blade as boundaries; calculating to obtain the positions of blade shafts of the sections of the first section according to the positions of the maximum thickness points of the suction surfaces and the maximum thickness points of the pressure surfaces of the sections of the first section, the chord lengths and the distance information of the sections and the diameters of the blade roots of the blades, wherein the distance information represents the distances from the sections to the blade roots of the blades; And calculating the positions of blade shafts of a plurality of sections of the second section of the blade according to the chord length distribution curve of the blade and the root diameter of the blade. Optionally, for the second section of the blade, calculating, according to the chord length distribution curve of the blade and the root diameter of the blade, the blade axis positions of the sections of the second section, including: Selecting a plurality of cross-sections in a second section of the blade; determining the chord lengths of a plurality of sections in a second section according to the chord length distribution curve of the blade, wherein the second section takes a target section and a blade root of the blade as boundaries; The blade axis positions of the plurality of sections in the second section are obtained based on the chord lengths of the plurality of sections in the second section and the root diameters of the blades. Optionally, determining the suction surface maximum thickness point position and the pressure surface maximum thickness point position of the multiple sections of the first section according to the chord length distribution curve, the relative thickness distribution curve, the geometric profile data of the standard airfoil and the relative thickness of the standard airfoil of the blade includes: Selecting a plurality of cross-sections at a first section of the blade; determining the relative thicknesses of the sections of the first section according to the chord length distribution curve and the relative thickness distribution curve of the blade; determining maximum thickness point position infor