Method and apparatus for determining blade shaft position based on main beam offset method

Abstract

The application discloses a method and device for determining a blade axis position based on a main beam offset method, and the method comprises the following steps: selecting a target section according to a maximum chord length section of a blade; determining suction surface maximum thickness point positions of multiple sections in a first section of the blade according to a chord length distribution curve, a relative thickness distribution curve, suction surface maximum thickness point positions of the multiple sections in the first section, and a standard airfoil relative thickness, the first section being bounded by the target section and a blade tip of the blade; calculating front edge point positions of the multiple sections in the first section based on the suction surface maximum thickness point positions of the multiple sections in the first section and a front edge offset of the maximum thickness point positions relative to a front edge of the blade axis; obtaining the blade axis positions of the multiple sections in the first section according to the front edge point positions of the multiple sections in the first section and chord lengths of the multiple sections in the first section; and calculating the blade axis positions of multiple sections in a second section of the blade according to blade root distances of the multiple sections in the second section, a front edge point position of the target section, and a blade root distance of the target section.

Description

Technical Field

[0001] This application belongs to the field of wind power generation technology, and in particular relates to a method and apparatus for determining the blade shaft position based on the main beam offset method. Background Technology

[0002] With the development of the wind power industry, wind turbine blades are becoming longer and heavier. To minimize blade weight, continuous improvements and optimizations are needed in aerodynamics, structure, materials, and load characteristics. Among these, accurately detecting the position of the blade shaft has a significant impact on the aerodynamic shape and load of the blade.

[0003] Existing methods for determining the blade axis position are mainly based on experience. For example, the blade axis position is generally determined empirically at a distance of 30% of the chord length from the leading edge of the cross-section. At the same time, in order to ensure the smoothness of the blade's aerodynamic shape, the position of the blade axis is manually adjusted.

[0004] The problem with this method is that it ignores the thickness characteristics of the blade airfoil, leading to an excessive deviation between the location of the maximum thickness at each section of the blade and the determined blade axis position. This excessive deviation results in low structural efficiency of the main beam. Structural efficiency reflects the relationship between the material usage and structural strength of the main beam. When the structural efficiency is low, the material usage of the main beam is higher for the same structural strength requirements.

[0005] Therefore, existing methods for determining the position of the blade axis are not conducive to reducing the weight of the blade. Summary of the Invention

[0006] Therefore, this application discloses a method and apparatus for determining the blade shaft position based on the main beam offset method, so as to reduce the weight of the blade.

[0007] The first aspect of this application provides a method for determining the blade shaft position based on the main beam offset method, including:

[0008] Select the target section based on the maximum chord length of the blade;

[0009] Based on the chord length distribution curve, relative thickness distribution curve, location of the maximum thickness point of the suction surface, and relative thickness of the standard airfoil, the locations of the maximum thickness points of the suction surface of multiple cross sections in the first segment of the blade are determined, with the target cross section and the blade tip as the boundaries of the first segment;

[0010] Based on the location of the maximum thickness point of the suction surface of multiple cross sections in the first segment, the location of the leading edge point of multiple cross sections in the first segment is calculated.

[0011] Based on the leading edge point positions and chord lengths of multiple cross sections in the first segment, the blade shaft positions of multiple cross sections in the first segment are obtained;

[0012] For the second segment of the blade, the blade axis position of the multiple cross-sections in the second segment is calculated based on the blade root distance of the multiple cross-sections in the second segment, the leading edge position of the target cross-section, and the blade root distance of the target cross-section. The second segment is bounded by the target cross-section and the blade root.

[0013] Optionally, selecting the target section based on the maximum chord length section of the blade includes:

[0014] Select the section with the maximum chord length of the blade as the target section;

[0015] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0016] Optionally, determining the location of the maximum suction surface thickness point of multiple cross-sections in the first segment of the blade based on the chord length distribution curve, relative thickness distribution curve, location of the maximum suction surface thickness point, and relative thickness of the standard airfoil includes:

[0017] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation;

[0018] Based on the standard airfoil geometry, determine the location of the point with the maximum thickness of the suction surface;

[0019] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the suction surface in the multiple sections in the first segment is obtained by interpolation.

[0020] Optionally, calculating the leading edge positions of the multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction surface of the multiple cross-sections of the first segment includes:

[0021] The offset of the maximum thickness point position relative to the leading edge of the blade axis is determined based on the blade root diameter.

[0022] The initial leading edge point positions of the plurality of cross sections are determined based on the leading edge offset and the position of the maximum thickness point of the suction surface of the plurality of cross sections.

[0023] The positions of the leading edges of the multiple cross sections are obtained by fitting the initial leading edge positions of the multiple cross sections.

[0024] Optionally, before fitting the initial leading edge point positions of the plurality of cross-sections to obtain the leading edge point positions of the plurality of cross-sections of the first segment, the method further includes:

[0025] Identify whether the initial leading edge positions of the multiple cross sections meet the preset fitting conditions;

[0026] The positions of the initial leading edge points that do not meet the fitting conditions are corrected.

[0027] A second aspect of this application provides a device for determining the blade shaft position based on a main beam offset method, comprising:

[0028] The selection unit is used to select the target section based on the maximum chord length section of the blade.

[0029] The determining unit is used to determine the position of the maximum thickness point of the suction surface of multiple cross sections in the first segment of the blade based on the chord length distribution curve, relative thickness distribution curve, position of the maximum thickness point of the suction surface and the relative thickness of the standard airfoil. The first segment is bounded by the target cross section and the blade tip.

[0030] The first calculation unit is used to calculate the position of the leading edge point of multiple sections in the first segment based on the position of the maximum thickness point of the suction surface of multiple sections in the first segment.

[0031] The obtaining unit is used to obtain the blade shaft position of multiple cross-sections in the first segment based on the leading edge point position and chord length of multiple cross-sections in the first segment;

[0032] The second calculation unit is used to calculate the blade axis position of multiple cross sections in the second segment based on the blade root distance of multiple cross sections in the second segment, the leading edge position of the target cross section, and the blade root distance of the target cross section. The second segment is bounded by the target cross section and the blade root.

[0033] Optionally, when the selection unit selects the target section based on the maximum chord length section of the blade, it is specifically used for:

[0034] Select the section with the maximum chord length of the blade as the target section;

[0035] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0036] Optionally, when the determining unit determines the location of the maximum suction surface thickness point of multiple sections in the first segment of the blade based on the chord length distribution curve, relative thickness distribution curve, location of the maximum suction surface thickness point, and relative thickness of the standard airfoil, it is specifically used for:

[0037] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation;

[0038] Based on the standard airfoil geometry, determine the location of the point with the maximum thickness of the suction surface;

[0039] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the suction surface in the multiple sections in the first segment is obtained by interpolation.

[0040] Optionally, when the first calculation unit calculates the leading edge positions of multiple cross-sections of the first segment based on the positions of the points with the maximum thickness of the suction surface of multiple cross-sections of the first segment, it is specifically used for:

[0041] The offset of the maximum thickness point position relative to the leading edge of the blade axis is determined based on the blade root diameter.

[0042] The initial leading edge point positions of the plurality of cross sections are determined based on the leading edge offset and the position of the maximum thickness point of the suction surface of the plurality of cross sections.

[0043] The positions of the leading edges of the multiple cross sections are obtained by fitting the initial leading edge positions of the multiple cross sections.

[0044] Optionally, the first computing unit is further configured to:

[0045] Identify whether the initial leading edge positions of the multiple cross sections meet the preset fitting conditions;

[0046] The positions of the initial leading edge points that do not meet the fitting conditions are corrected.

[0047] The beneficial effects of this plan are as follows:

[0048] By combining the relative thickness distribution curve of the blades, the blade axis position is determined, thereby reducing the deviation between the determined blade axis position of each section and the maximum thickness position of the blade. This achieves the structural efficiency of the main beam based on the blade axis position, thereby reducing the material usage of the main beam and lightening the weight of the blades without affecting the structural strength. Attached Figure Description

[0049] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0050] Figure 1 This is a flowchart of a method for determining the blade shaft position based on the main beam offset method provided in an embodiment of this application;

[0051] Figure 2 This is a flowchart of another method for determining the blade shaft position based on the main beam offset method provided in this application embodiment;

[0052] Figure 3 This is a schematic diagram of a blade segmentation provided in an embodiment of this application;

[0053] Figure 4 This is a schematic diagram showing the location of the maximum thickness of the i-th cross-section of a blade, provided in an embodiment of this application.

[0054] Figure 5 This is a schematic diagram of a device for determining the blade shaft position based on the main beam offset method provided in an embodiment of this application. Detailed Implementation

[0055] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0056] This application provides a method for determining the blade shaft position based on the main beam offset method. Please refer to [link to relevant documentation]. Figure 1 Here is a flowchart of the method, which may include the following steps.

[0057] S101, Select the target section based on the maximum chord length section of the blade.

[0058] Optionally, the implementation of step S101 may include:

[0059] Select the section with the maximum chord length of the blade as the target section;

[0060] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0061] For example, when determining the target section in the latter way, first determine the maximum chord length section of the blade, and then select the section 10 cm to the right of the maximum chord length (denoted as Cmax) section as the target section, or select the section 10 cm to the left of the maximum chord length section as the target section.

[0062] The above preset values ​​can be set according to actual conditions, and this embodiment does not impose any limitations.

[0063] S102. Based on the chord length distribution curve, relative thickness distribution curve, location of the maximum thickness point of the suction surface, and relative thickness of the standard airfoil, determine the location of the maximum thickness point of the suction surface of multiple sections in the first segment of the blade.

[0064] The first segment is bounded by the target cross-section and the blade tip.

[0065] For example, please see Figure 3 This is a schematic diagram of the segmentation of the blade provided in this embodiment. The cross section at a distance r1 from the blade root is the target cross section determined in S101 of this embodiment. In this example, the maximum chord length cross section of the blade is used as the target cross section.

[0066] The portion from the right side of the target cross section to the leaf tip is the first segment of the blade in this embodiment, and the portion from the left side of the target cross section to the leaf root is the second segment of the blade in this embodiment.

[0067] Figure 3 In this context, R2 represents the distance from the leaf base to the leaf tip, which can also be understood as the length of the leaf.

[0068] Optionally, the specific implementation of step S102 may include...

[0069] A1. Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation.

[0070] A2. Determine the location of the point with the maximum thickness of the suction surface based on the standard airfoil geometry information;

[0071] A3. Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the suction surface of multiple sections in the first segment is obtained by interpolation.

[0072] Please see Figure 2 The flowchart shows another method for determining the blade shaft position based on the main beam offset method provided in this embodiment.

[0073] In this process, steps S1 and S2 are equivalent to the implementation of step A1 above, step S3 is equivalent to step A2 above, and step S4 is equivalent to step A3 above.

[0074] S1, select n cross sections.

[0075] S2, interpolation yields the chord length Ci and relative thickness RTi of section i.

[0076] S3, obtains the position of the maximum thickness point of the standard airfoil on the suction surface.

[0077] S4, interpolation is used to obtain the position of the maximum thickness point of the i-th section on the suction surface.

[0078] When performing step S1, based on the aerodynamic shape of the blade, n sections can be selected one by one from the target section to the blade tip in the first segment of the blade. The distance from the selected i-th section to the blade root is denoted as Ri. The target section is denoted as the selected i-th section, and the numbering increases from the target section to the blade tip.

[0079] The distance from section i to the blade root can be measured after selecting the section, or it can be calculated based on the distance from the target section to the blade root and the rules for selecting the section.

[0080] The specific value of n can be set according to actual needs and is not limited. For example, it can be set to 10.

[0081] When selecting n sections, they can be selected at equal intervals, i.e., according to the rule that the distance between any two sections on the r-axis is equal, or they can be selected according to other rules, without any limitation.

[0082] In step S2, the chord length Ci and relative thickness RTi of each section i in the selected n sections can be interpolated based on the known blade chord length distribution curve and relative thickness distribution curve.

[0083] Among them, the blade chord length distribution curve and the relative thickness distribution curve are pre-defined curves. The blade chord length distribution curve reflects the relationship between the chord length of any section on the blade and the distance R from that section to the blade root, while the relative thickness distribution curve reflects the relationship between the relative thickness of any section on the blade and the distance R from that section to the blade root.

[0084] Therefore, in S2, for any selected section i, its distance Ri from the blade root can be substituted into the blade chord length distribution curve, and the chord length Ci of section i can be determined based on the correlation represented by the curve. Similarly, the distance Ri from section i to the blade root can be substituted into the relative thickness distribution curve, and the relative thickness RTi of section i can be determined based on the correlation represented by the curve.

[0085] In step S3, the geometric shape of the standard airfoil of the current blade can be determined first, that is, the profile of the maximum chord length section of the current blade. Based on this shape, the location of the maximum thickness point of the suction surface corresponding to this geometric shape is found from the standard airfoil data table, that is, the y-direction position of the point on the geometric shape of the standard airfoil that is farthest from the chord line perpendicularly. In this embodiment, the location of the maximum thickness point of the suction surface on the geometric shape of the standard airfoil is denoted as ya_ss.

[0086] The direction of the y-axis can be found in [reference]. Figure 4 .

[0087] In step S4, for the selected i-th section, the position (y-direction position) of the maximum thickness point of the suction surface of the i-th section can be obtained by interpolation based on the relative thickness RTi of the i-th section, the relative thickness of the standard airfoil, and the position information of the maximum thickness point.

[0088] The location information of the point with the maximum thickness is the aforementioned ya_ss.

[0089] The relative thickness of a standard airfoil can be understood as the relative thickness of the blade's maximum chord length section. This data can be obtained by consulting a standard airfoil data table based on the airfoil's geometry. In this embodiment, the relative thickness of the standard airfoil can be denoted as RT0.

[0090] For the selected i-th section, the above data can be substituted into the following formula to calculate the location of the maximum thickness point of the suction surface of the i-th section:

[0091] ya_ss / relative thickness of standard airfoil RT0*RTi=yi_ss.

[0092] S103, based on the position of the maximum thickness point of the suction surface of multiple sections in the first segment and the offset of the maximum thickness point position relative to the leading edge of the blade shaft, the leading edge point position of multiple sections in the first segment is calculated.

[0093] The specific implementation of step S103 may include:

[0094] B1, determine the offset of the maximum thickness point position relative to the leading edge of the blade axis based on the blade root diameter;

[0095] B2. Determine the initial leading edge point positions of multiple cross sections based on the leading edge offset and the position of the maximum thickness point of the suction surface of multiple cross sections.

[0096] B3, by fitting the initial leading edge point positions of multiple cross sections, the leading edge point positions of multiple cross sections are obtained.

[0097] exist Figure 2 In the process shown, step S103 may include the following steps:

[0098] S5, determine the offset L_disp of the maximum thickness point position relative to the leading edge of the blade shaft.

[0099] S6, calculate the initial y-position yi of each section.

[0100] S7, select the distance Ri and the initial position yi in the y direction of multiple cross sections.

[0101] S8, the curve expression of the leading edge of the first blade segment is obtained by fitting.

[0102] Wherein, S5 is equivalent to the aforementioned step B1, S6 is equivalent to step B2, and S7 and S8 are equivalent to step B3.

[0103] In step S5, the leading edge offset can be calculated according to the formula: L_disp=Dr / 2*b.

[0104] Where Dr represents the diameter of the leaf root, and b is a preset constant, which can generally be selected within the range of greater than 0 and less than or equal to 0.2.

[0105] The purpose of determining the leading edge offset is to ensure that there is a certain distance between the blade shaft and the leading edge line of the blade, so that the main load-bearing component of the blade, the beam cap, can be properly installed into the blade.

[0106] In step S6, the initial y-direction position of each section i can be denoted as yi, and yi can be calculated according to the formula: yi=L_disp +yi_ss*Ci.

[0107] The initial y-position of section i is the same as the initial leading edge position of that section in step B2.

[0108] In step S7, any number of sections can be selected from the n sections of the first segment according to the actual situation. This embodiment does not limit the specific selection method.

[0109] For example, sections 1, n / 3, 2 / 3n, and n can be selected to obtain the distance Ri from these sections to the leaf root, as well as the initial y-position yi of these sections.

[0110] Optionally, if n / 3 and / or 2 / 3n are not integers, they can be rounded up or down.

[0111] In step S8, the distance Ri and the initial position yi in the y direction of the obtained cross sections can be fitted based on any curve equation. In this embodiment, the specific curve equation used for fitting is not limited.

[0112] For example, a cubic curve equation can be selected to fit the data obtained in S7. The expression for the leading edge of the blade in the first segment obtained after fitting can be represented by the following formula:

[0113] .

[0114] In this formula, a1 to a4 are the coefficients in the curve equation that need to be determined by fitting, and yinew represents the position of the leading edge point of any section Ri in the fitted curve.

[0115] Optionally, the leading edge positions of multiple cross-sections are fitted to obtain the leading edge positions of multiple cross-sections in the first segment. This includes, before executing S8:

[0116] Identify whether the initial leading edge positions of multiple cross sections meet the preset fitting conditions;

[0117] The positions of the initial leading edge points that do not meet the fitting conditions are corrected.

[0118] The fitting condition here can be that, for the distance Ri and the initial y-position yi of the multiple cross sections obtained in S7, the initial y-position yi of the previous cross section i should be greater than the initial y-position yi+1 of the next cross section i+1.

[0119] Between any two cross sections on a blade, the cross section closer to the blade root is defined as the former cross section, and the cross section farther from the blade root is defined as the latter cross section.

[0120] Therefore, the way to identify whether the initial leading edge position of multiple cross sections meets the preset fitting conditions is to determine whether there is yi≤yi+1 for each of the multiple cross sections obtained in S7. If there is a case of yi≤yi+1 between any two cross sections, it is considered that the initial leading edge position of these two cross sections does not meet the fitting conditions.

[0121] The correction method for the initial leading edge point position that does not meet the conditions can be:

[0122] The initial leading edge position of the preceding cross section is adjusted based on the initial leading edge position of the following cross section. For example, when the initial leading edge positions of two cross sections do not meet the fitting conditions, the initial leading edge position of the preceding cross section can be corrected using the following formula:

[0123] yi = yi + 1 * 1.01.

[0124] The above formula means that the initial leading edge position yi of the previous section is set to 1.01 times the initial leading edge position yi+1 of the next section. In this way, it can be ensured that the initial leading edge position of each section in the first segment is greater than the initial leading edge position of the next section, thereby ensuring that the initial leading edge position of each section satisfies the above fitting condition.

[0125] The purpose of performing the above steps is to ensure that the distance from the blade shaft to the blade leading edge line decreases continuously from the target section to the blade tip, thus avoiding errors in the curve expression obtained by subsequent fitting due to failure to meet this condition.

[0126] After fitting the curve expression of the first blade leading edge line, for any section i among the n sections, simply substitute its distance Ri from the blade root into the expression to calculate the position yinew of the leading edge point of that section.

[0127] S104. Based on the leading edge point positions and chord lengths of multiple sections in the first segment, the blade shaft positions of multiple sections in the first segment are obtained.

[0128] Step S104 is equivalent to Figure 2 In step S9 of the process shown, the position of the blade shaft of the first segment is calculated.

[0129] In S104, for any selected section i in the first segment, the leading edge position yinew of the section can be obtained through step S103. Then, based on yinew and the chord length Ci of the section, the blade shaft position of the section is calculated using the formula: yinew / Ci.

[0130] S105, for the second segment of the blade, the blade axis position of multiple sections in the second segment is calculated based on the blade root distance of multiple sections in the second segment, the leading edge position of the target section, and the blade root distance of the target section.

[0131] A specific implementation of S105 may include... Figure 2 Steps S10 to S15 in the process shown:

[0132] S10, select m cross-sections.

[0133] S11, interpolation yields the chord length Ci of the second section i.

[0134] S12, determine the end section position R0 and leading edge position y0 of the cylindrical section of the blade.

[0135] S13, determine the position yref and distance Rref of the leading edge point of the target section.

[0136] S14, calculate the y-direction position of the i-th section of the second segment.

[0137] S15, calculate the blade shaft position of the second segment.

[0138] The method of selecting m cross-sections in step S10 can be the same as the method of selecting n cross-sections in step S1, and will not be repeated here.

[0139] The value of m can be equal to or less than n. The specific value is determined based on the actual situation and is not limited.

[0140] In step S11, the distance Ri from each section i to the leaf root in the above m sections can be determined first. The method of determination can be the same as the method of determining the distance from the section to the leaf root in the first section, and will not be repeated here.

[0141] Then, for each section i among the m sections, its distance Ri from the leaf root is substituted into the predetermined chord length distribution curve for interpolation calculation, thereby obtaining the chord length Ci of that section.

[0142] In step S12, the position R0 of the end section of the cylindrical blade segment can be determined by measurement, that is, the distance from the end section of the cylindrical blade segment to the blade root, and the position y0 of the leading edge point of the end section of the cylindrical blade segment.

[0143] Wherein, y0 can be calculated according to the formula after measuring the leaf root diameter Dr: y0=Dr / 2.

[0144] In step S13, the position yref and distance Rref of the leading edge of the target section can be obtained as follows:

[0145] First, along Figure 3 The distance from the target section to the blade root is measured along the direction of the R-axis, resulting in Rref. Then, Rref is substituted into the expression for the blade leading edge line fitted in S8, and the calculated result is the position yref of the leading edge point of the target section.

[0146] The distance Rref from the target section is the blade root distance of the target section in S105.

[0147] In step S14, for any section i among the m sections of the second segment, the distance Ri from section i to the blade root (that is, the blade root distance of the section i) can be substituted into the following interpolation formula to calculate the y-direction position of the leading edge point of the section:

[0148] yi=(yref-y0) / (Rref-R0)*(Ri-R0)+y0.

[0149] In step S15, for any section i among the m sections of the second segment, the blade shaft position of the section can be calculated according to the formula: yi / Ci, based on the y-direction position yi of the leading edge point of the section and the chord length Ci of the section.

[0150] Thus, this scheme has determined the blade axis positions of several cross sections in the first and second segments of the blade. When it is necessary to lay the main beam in the blade, on the one hand, a curve representing the blade axis can be fitted based on the blade axis positions of each cross section, and the shape of the blade main beam can be designed based on this curve. On the other hand, during the laying of the main beam, the position of the main beam at each cross section of the first and second segments can be checked in a timely manner to ensure that it is consistent with the blade axis position at that cross section, so as to ensure that the blade main beam is laid according to the position of the blade axis.

[0151] The beneficial effects of this plan are as follows:

[0152] By combining the relative thickness distribution curve of the blades, the blade axis position is determined, thereby reducing the deviation between the determined blade axis position of each section and the maximum thickness position of the blade. This achieves the structural efficiency of the main beam based on the blade axis position, thereby reducing the material usage of the main beam and lightening the weight of the blades without affecting the structural strength.

[0153] On the other hand, existing detection methods, after initially determining the position of the blade shaft based on experience, still require manual adjustment of the blade shaft position, which is a time-consuming process. In contrast, the detection method provided in this embodiment can directly calculate the position of the blade shaft using relevant blade data, eliminating the need for manual adjustment and shortening the time required to determine the blade shaft position.

[0154] According to an embodiment of this application, a method for determining the blade shaft position based on a main beam offset method is provided. This application also provides an apparatus for determining the blade shaft position based on a main beam offset method. Please refer to [link to relevant documentation]. Figure 5 This is a schematic diagram of the structure of the device, which may include the following units.

[0155] Selection unit 501 is used to select the target section based on the maximum chord length section of the blade;

[0156] The determining unit 502 is used to determine the position of the maximum thickness point of the suction surface of multiple sections in the first segment of the blade based on the chord length distribution curve, relative thickness distribution curve, position of the maximum thickness point of the suction surface and the relative thickness of the standard airfoil. The first segment is bounded by the target section and the blade tip.

[0157] The first calculation unit 503 is used to calculate the position of the leading edge point of multiple sections in the first segment based on the position of the maximum thickness point of the suction surface of multiple sections in the first segment.

[0158] Unit 504 is used to obtain the blade shaft position of multiple sections in the first segment based on the leading edge point position and chord length of multiple sections in the first segment;

[0159] The second calculation unit 505 is used to calculate the blade axis position of multiple sections in the second segment of the blade based on the blade root distance of multiple sections in the second segment, the leading edge position of the target section, and the blade root distance of the target section.

[0160] Optionally, when selecting the target section based on the maximum chord length section of the blade, the selection unit 501 is specifically used for:

[0161] Select the section with the maximum chord length of the blade as the target section;

[0162] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0163] Optionally, when determining the location of the maximum suction surface thickness point in multiple sections of the first segment of the blade based on the blade's chord length distribution curve, relative thickness distribution curve, location of the maximum suction surface thickness point, and standard airfoil relative thickness, the determining unit 502 is specifically used for:

[0164] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the chord length and relative thickness of multiple sections in the first segment of the blade are obtained by interpolation.

[0165] Based on the standard airfoil geometry, determine the location of the point with the maximum thickness of the suction surface;

[0166] Based on the chord length and relative thickness of multiple sections in the first segment, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the suction surface of multiple sections in the first segment is obtained by interpolation.

[0167] Optionally, when the first calculation unit 503 calculates the positions of the leading edge points of multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction surfaces of multiple cross-sections of the first segment, it is specifically used for:

[0168] The offset of the maximum thickness point relative to the leading edge of the blade axis is determined based on the blade root diameter.

[0169] The initial leading edge point positions of multiple cross sections are determined based on the leading edge offset and the position of the maximum thickness point of the suction surface of multiple cross sections.

[0170] The positions of the leading edges of multiple cross sections are obtained by fitting the initial leading edge positions of multiple cross sections.

[0171] Optionally, the first computing unit 503 is also used for:

[0172] Identify whether the initial leading edge positions of multiple cross sections meet the preset fitting conditions;

[0173] The positions of the initial leading edge points that do not meet the fitting conditions are corrected.

[0174] The device for determining the blade shaft position based on the main beam offset method provided in this embodiment has the same working principle and beneficial effects as the method for determining the blade shaft position based on the main beam offset method provided in this application embodiment, and will not be repeated here.

[0175] It should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0176] For ease of description, the above systems or devices are described separately as various modules or units based on their functions. Of course, in implementing this application, the functions of each unit can be implemented in one or more software and / or hardware components.

[0177] As can be seen from the above description of the embodiments, those skilled in the art can clearly understand that this application can be implemented by means of software plus necessary general-purpose hardware platforms. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in various embodiments or some parts of the embodiments of this application.

[0178] Finally, it should be noted that in this document, relational terms such as first, second, third, and fourth are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0179] The above description is only a preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A method of determining a blade shaft position based on a main beam biasing method, characterized by, The method comprises the following steps: selecting a target section according to a maximum chord section of the blade; determining suction surface maximum thickness point positions of a plurality of sections in a first section of the blade according to a chord distribution curve, a relative thickness distribution curve, suction surface maximum thickness point positions of the blade, and a standard airfoil relative thickness, the first section being bounded by the target section and a blade tip of the blade; calculating leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section; obtaining blade axis positions of the plurality of sections in the first section according to the leading edge point positions and chords of the plurality of sections in the first section; calculating blade axis positions of a plurality of sections in a second section of the blade according to blade root distances of the plurality of sections in the second section, a leading edge point position of the target section, and a blade root distance of the target section, the second section being bounded by the target section and a blade root of the blade; wherein the calculating of the leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section comprises: determining a leading edge offset of the maximum thickness point position relative to the blade axis according to a blade root diameter of the blade; determining initial leading edge point positions of the plurality of sections according to the leading edge offset and the suction surface maximum thickness point positions of the plurality of sections; fitting the initial leading edge point positions of the plurality of sections to obtain the leading edge point positions of the plurality of sections.

2. The method of claim 1, wherein, The selecting of the target section according to the maximum chord section of the blade comprises: selecting the maximum chord section of the blade as the target section; or selecting a section with a preset distance from the maximum chord section of the blade as the target section.

3. The method of claim 1, wherein, The determining of the suction surface maximum thickness point positions of the plurality of sections in the first section of the blade according to the chord distribution curve, the relative thickness distribution curve, the suction surface maximum thickness point positions of the blade, and the standard airfoil relative thickness comprises: interpolating chords and relative thicknesses of the plurality of sections in the first section of the blade according to the chord distribution curve and the relative thickness distribution curve of the blade; determining the suction surface maximum thickness point positions according to standard airfoil geometric shape information; interpolating the suction surface maximum thickness point positions of the plurality of sections in the first section according to the chords and the relative thicknesses of the plurality of sections in the first section, the standard airfoil relative thickness, and the suction surface maximum thickness point positions.

4. The method of claim 3, wherein, Before the fitting of the initial leading edge point positions of the plurality of sections to obtain the leading edge point positions of the plurality of sections in the first section, the method further comprises: identifying whether the initial leading edge point positions of the plurality of sections satisfy a preset fitting condition; correcting the initial leading edge point positions that do not satisfy the fitting condition.

5. An apparatus for determining a blade shaft position based on a main beam biasing method, the apparatus comprising: a main beam biasing method; and a blade shaft position determination method. The method comprises the following steps: a selecting unit configured to select a target section according to a maximum chord section of a blade; a determining unit configured to determine suction surface maximum thickness point positions of a plurality of sections in a first section of the blade according to a chord distribution curve, a relative thickness distribution curve, suction surface maximum thickness point positions of the blade, and a standard airfoil relative thickness, the first section being bounded by the target section and a blade tip of the blade; The first computing unit is configured to calculate the leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section. The obtaining unit is configured to obtain the blade axis positions of the plurality of sections in the first section according to the leading edge point positions and the chord lengths of the plurality of sections in the first section. The second computing unit is configured to calculate the blade axis positions of the plurality of sections in the second section of the blade according to the blade root distances of the plurality of sections in the second section, the leading edge point position of the target section, and the blade root distance of the target section, the second section being bounded by the target section and a blade root of the blade. The first computing unit is configured to calculate the leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section. The first computing unit is configured to calculate the leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section. The first computing unit is configured to calculate the leading edge point positions of the plurality of sections in the first section based on the suction surface maximum thickness point positions of the plurality of sections in the first section. The selection unit is configured to select the target section according to the maximum chord length section of the blade.

6. The apparatus of claim 5, wherein, The selection unit is configured to select the target section according to the maximum chord length section of the blade. The determination unit is configured to determine the suction surface maximum thickness point positions of the plurality of sections in the first section of the blade according to the chord length distribution curve, the relative thickness distribution curve, the suction surface maximum thickness point position, and the standard airfoil relative thickness of the blade. The determination unit is configured to determine the suction surface maximum thickness point positions of the plurality of sections in the first section of the blade according to the chord length distribution curve, the relative thickness distribution curve, the suction surface maximum thickness point position, and the standard airfoil relative thickness of the blade.

7. The apparatus of claim 5, wherein, The first computing unit is further configured to: The first computing unit is further configured to: The first computing unit is further configured to: The first computing unit is further configured to:

8. The apparatus of claim 5, wherein, ​ ​ ​

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