Method and apparatus for determining blade axis position based on airfoil geometric profile characteristics

Abstract

This application discloses a method and apparatus for determining the blade axis position based on airfoil geometry. The method includes: selecting a target section based on the maximum chord length section of the blade; determining the positions of the maximum thickness points of the suction surface and pressure surface of multiple sections of a first segment based on the blade's chord length distribution curve, relative thickness distribution curve, geometric data of a standard airfoil, and relative thickness of the standard airfoil, wherein the first segment is bounded by the target section and the blade tip; calculating the blade axis position of multiple sections of the first segment based on the positions of the maximum thickness points of the suction surface and pressure surface, the chord length and distance information of the multiple sections, and the blade root diameter, wherein the distance information represents the distance from the section to the blade root; and calculating the blade axis position of multiple sections of the second segment based on the blade's chord length distribution curve and blade root diameter.

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 airfoil geometric features. 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 axis position based on airfoil geometry features, in order 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 airfoil geometry features, including:

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

[0009] Based on the chord length distribution curve and relative thickness distribution curve of the blade, the geometric shape data of the standard airfoil and the relative thickness of the standard airfoil, the positions of the maximum thickness points of the suction surface and the pressure surface of multiple sections in the first segment are determined. The first segment is bounded by the target section and the blade tip.

[0010] Based on the positions of the maximum thickness points of the suction surface and the pressure surface of multiple cross sections in the first segment, the chord length and distance information of multiple cross sections, and the blade root diameter, the blade axis positions of multiple cross sections in the first segment are calculated. The distance information represents the distance from the cross section to the blade root.

[0011] For the second segment of the blade, the blade axis positions of multiple cross sections of the second segment are calculated based on the chord length distribution curve of the blade and the blade root diameter.

[0012] Optionally, for the second segment of the blade, based on the chord length distribution curve and the blade root diameter, the blade axis positions of multiple sections of the second segment are calculated, including:

[0013] Multiple cross sections are selected in the second section of the blade;

[0014] Based on the chord length distribution curve of the blade, determine the chord length of multiple sections in the second segment, with the target section and the blade root as the boundary of the second segment;

[0015] Based on the chord length of multiple sections in the second segment and the blade root diameter, the blade axis position of multiple sections in the second segment is obtained.

[0016] Optionally, based on the blade's chord length distribution curve, relative thickness distribution curve, standard airfoil geometry data, and standard airfoil relative thickness, determine the locations of the maximum thickness points on the suction surface and pressure surface of multiple cross-sections in the first segment, including:

[0017] Select multiple cross sections in the first segment of the blade;

[0018] Based on the chord length distribution curve and relative thickness distribution curve of the blade, determine the relative thickness of multiple sections of the first segment;

[0019] Based on the geometric shape data of the standard airfoil, determine the location information of the maximum thickness point of the standard airfoil. The location information of the maximum thickness point includes the location of the maximum thickness point on the pressure surface and the location of the maximum thickness point on the suction surface.

[0020] Based on the relative thickness of multiple sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, interpolation is used to obtain the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections.

[0021] Optionally, based on the locations of the maximum thickness points of the suction and pressure surfaces at multiple cross-sections of the first segment, the chord lengths and distances of the multiple cross-sections, and the blade root diameter, the blade axis positions of the multiple cross-sections of the first segment are calculated, including:

[0022] Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple cross sections in the first segment, as well as the blade root diameter, the location information of the pressure surface thickness of multiple cross sections in the first segment is calculated.

[0023] Based on the location, chord length, and distance information of the maximum suction surface thickness of multiple cross sections in the first segment, as well as the blade root diameter, the suction surface thickness location information of multiple cross sections in the first segment is calculated.

[0024] The blade shaft positions of multiple sections in the first segment are calculated based on the pressure surface thickness and suction surface thickness information of multiple sections in the first segment.

[0025] Optionally, the target section can be selected based on the maximum chord length section of the blade, including:

[0026] Select the section with the maximum chord length of the blade as the target section;

[0027] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0028] A second aspect of this application provides a device for determining the blade shaft position based on airfoil geometry features, comprising:

[0029] The selection unit is used to select the target section based on the maximum chord length section of the blade.

[0030] The determination unit is used to determine the location of the maximum thickness point of the suction surface and the maximum thickness point of the pressure surface of multiple sections of the first segment based on the chord length distribution curve of the blade, the relative thickness distribution curve, the geometric shape data of the standard airfoil and the relative thickness of the standard airfoil. The first segment is bounded by the target section and the blade tip.

[0031] The first calculation unit is used to calculate the blade axis position of multiple cross sections of the first segment based on the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple cross sections, the chord length and distance information of multiple cross sections, and the blade root diameter. The distance information represents the distance from the cross section to the blade root.

[0032] The second calculation unit is used to calculate the blade axis position of multiple sections of the second segment of the blade based on the chord length distribution curve of the blade and the blade root diameter.

[0033] Optionally, when the second calculation unit calculates the blade axis positions of multiple sections of the second segment of the blade based on the blade chord length distribution curve and the blade root diameter, it is specifically used for:

[0034] Multiple cross sections are selected in the second section of the blade;

[0035] Based on the chord length distribution curve of the blade, determine the chord length of multiple sections in the second segment, with the target section and the blade root as the boundary of the second segment;

[0036] Based on the chord length of multiple sections in the second segment and the blade root diameter, the blade axis position of multiple sections in the second segment is obtained.

[0037] Optionally, when determining the location of the maximum thickness points of the suction surface and pressure surface at multiple sections of the first segment based on the blade's chord length distribution curve, relative thickness distribution curve, standard airfoil geometry data, and standard airfoil relative thickness, the determining unit is specifically used for:

[0038] Select multiple cross sections in the first segment of the blade;

[0039] Based on the chord length distribution curve and relative thickness distribution curve of the blade, determine the relative thickness of multiple sections of the first segment;

[0040] Based on the geometric shape data of the standard airfoil, determine the location information of the maximum thickness point of the standard airfoil. The location information of the maximum thickness point includes the location of the maximum thickness point on the pressure surface and the location of the maximum thickness point on the suction surface.

[0041] Based on the relative thickness of multiple sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, interpolation is used to obtain the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections.

[0042] Optionally, when the first calculation unit calculates the blade axis positions of multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction and pressure surfaces of multiple cross-sections, the chord lengths and distances of the multiple cross-sections, and the blade root diameter, it is specifically used for:

[0043] Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple cross sections in the first segment, as well as the blade root diameter, the location information of the pressure surface thickness of multiple cross sections in the first segment is calculated.

[0044] Based on the location, chord length, and distance information of the maximum suction surface thickness of multiple cross sections in the first segment, as well as the blade root diameter, the suction surface thickness location information of multiple cross sections in the first segment is calculated.

[0045] The blade shaft positions of multiple sections in the first segment are calculated based on the pressure surface thickness and suction surface thickness information of multiple sections in the first segment.

[0046] Optionally, when the selection unit selects the target section based on the maximum chord length section of the blade, it is specifically used for:

[0047] Select the section with the maximum chord length of the blade as the target section;

[0048] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0049] The beneficial effects of this plan are as follows:

[0050] 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

[0051] 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.

[0052] Figure 1 This is a flowchart illustrating a method for determining the blade shaft position based on airfoil geometric features, as provided in an embodiment of this application.

[0053] Figure 2 This is a flowchart illustrating a method for calculating the blade shaft position of the first segment of a blade, as provided in an embodiment of this application.

[0054] Figure 3 This is a flowchart illustrating a method for calculating the blade shaft position of the second segment of a blade, as provided in an embodiment of this application.

[0055] Figure 4 This is a schematic diagram of a blade segmentation provided in an embodiment of this application;

[0056] Figure 5 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.

[0057] Figure 6 This is a schematic diagram of a device for determining the blade shaft position based on airfoil geometry, provided in an embodiment of this application. Detailed Implementation

[0058] 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.

[0059] This application provides a method for determining the blade shaft position based on airfoil geometry features. Please refer to [link to relevant documentation]. Figure 1 Here is a flowchart of the method, which may include the following steps.

[0060] S101, Select the target section based on the maximum chord length section of the blade.

[0061] Optionally, the implementation of step S101 may include:

[0062] Select the section with the maximum chord length of the blade as the target section;

[0063] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0064] 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.

[0065] The above preset values ​​can be set according to actual conditions, and this embodiment does not impose any limitations.

[0066] S102, based on the chord length distribution curve, relative thickness distribution curve, geometric shape data of the standard airfoil, and relative thickness of the standard airfoil, determine the location of the maximum thickness point of the suction surface and the maximum thickness point of the pressure surface of multiple sections of the first segment.

[0067] The first segment is bounded by the target cross-section and the blade tip.

[0068] For example, please see Figure 4 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.

[0069] 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.

[0070] Figure 4 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.

[0071] Optionally, a specific implementation of step S102 may include:

[0072] A1, Select multiple sections in the first segment of the blade;

[0073] A2. Based on the chord length distribution curve and relative thickness distribution curve of the blade, determine the relative thickness of multiple sections of the first segment;

[0074] A3. Based on the geometric shape data of the standard airfoil, determine the location information of the maximum thickness point of the standard airfoil. The location information of the maximum thickness point includes the location of the maximum thickness point on the pressure surface and the location of the maximum thickness point on the suction surface.

[0075] A4. Based on the relative thickness of multiple sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, interpolation is used to obtain the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections.

[0076] Please see Figure 2 This is a flowchart of a method for determining the blade axis position of each section in the first segment of a blade, provided in this embodiment.

[0077] Step S102 of this embodiment may include... Figure 2 The process shown includes the following steps:

[0078] S21, select n cross sections.

[0079] S22, interpolation yields the chord length Ci and relative thickness RTi of the cross section.

[0080] S23, determine the location of the maximum thickness point of the standard airfoil on the pressure and suction sides.

[0081] S24, interpolation is used to obtain the position of the maximum thickness point of the i-th section on the pressure surface and suction surface.

[0082] Wherein, S21 is equivalent to step A1 above, S22 is equivalent to step A2 above, step S23 is equivalent to step A3 above, and S24 is equivalent to step A4 above.

[0083] When performing step S21, 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.

[0084] 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.

[0085] The specific value of n can be set according to actual needs and is not limited. For example, it can be set to 10.

[0086] 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.

[0087] In step S22, 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.

[0088] 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.

[0089] Therefore, in S22, 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.

[0090] In step S23, the geometric shape of the current blade's standard airfoil 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 suction surface point on the standard airfoil's geometric shape that is farthest from the chord line. In this embodiment, the location of the maximum thickness point of the suction surface on the standard airfoil's geometric shape is denoted as ya_ss.

[0091] The direction of the y-axis can be found in [reference]. Figure 5 .

[0092] Similar to the location of the maximum thickness point of the suction surface, the location of the maximum thickness point of the pressure surface corresponding to the standard airfoil geometry of the current blade can be obtained by looking up a table. This is the y-axis position of the pressure surface point on the standard airfoil geometry that is furthest from the chord line. In this embodiment, the location of the maximum thickness point of the pressure surface on the standard airfoil geometry is denoted as ya_ps.

[0093] In step S24, for the selected i-th section, the position of the maximum thickness point (y-direction position) yi_ss 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 of the maximum thickness point of the standard airfoil, and the position of the maximum thickness point yi_as of the pressure surface of the i-th section.

[0094] The locations of the maximum thickness points of the i-th cross-section on the suction surface and on the pressure surface can be found in [reference]. Figure 5 .

[0095] 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.

[0096] For the selected i-th section, the position of the maximum thickness point ya_ss of the standard airfoil on the suction surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section can be substituted into the following formula to calculate the position of the maximum thickness point of the suction surface of the i-th section:

[0097] ya_ss / relative thickness of standard airfoil RT0*RTi=yi_ss.

[0098] For the selected i-th section, the location of the maximum thickness point ya_ps of the standard airfoil on the pressure surface, the relative thickness RT0 of the standard airfoil, and the relative thickness RTi of the i-th section can be substituted into the following formula to calculate the location of the maximum thickness point of the pressure surface of the i-th section:

[0099] ya_ps / relative thickness of standard airfoil RT0*RTi=yi_ps.

[0100] S103. Based on the positions of the maximum thickness points of the suction surface and the pressure surface of the multiple cross sections of the first segment, the chord length and distance information of the multiple cross sections, and the blade root diameter, the blade axis positions of the multiple cross sections of the first segment are calculated.

[0101] Distance information represents the distance from the cross section to the blade root.

[0102] Optionally, a specific implementation of step S103 may include:

[0103] B1. Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple sections in the first segment, as well as the blade root diameter, the pressure surface thickness location information of multiple sections in the first segment is calculated.

[0104] B2. Based on the location, chord length, and distance information of the maximum thickness point of the suction surface of multiple sections of the first segment, as well as the blade root diameter, the suction surface thickness location information of multiple sections of the first segment is calculated.

[0105] B3. The blade shaft positions of multiple sections of the first segment are calculated based on the pressure surface thickness position information and suction surface thickness position information of multiple sections of the first segment.

[0106] Step S103 in this embodiment can be equivalent to Figure 2 Steps S25 to S27 of the process shown:

[0107] S25, calculate the pressure surface Ki_ps and suction surface Ki_ss for each cross section.

[0108] S26, calculate the average value of Ki for multiple cross sections.

[0109] S27, calculate the blade axis position of section i.

[0110] Wherein, S25 is equivalent to steps B1 and B2 above, and S26 and S27 are equivalent to step B3 above.

[0111] In step S25, for each section i of the first segment, the pressure surface thickness position information of the section can be recorded as Ki_ps, and the suction surface thickness position information of the section can be recorded as Ki_ss.

[0112] The location information of the pressure surface thickness at section i can be calculated using the following formula:

[0113] Ki_ps=(Dr-2*yi_ps*Ci) / (2*(Ri-R1)).

[0114] In this formula, Dr is the diameter of the blade root, Ri is the distance from the i-th section to the blade root, R1 is the distance from the target section determined in S101 to the blade root, and Ci is the chord length of the i-th section.

[0115] The location information of the suction surface thickness at section i can be calculated using the following formula:

[0116] Ki_ss=(Dr-2*yi_ss*Ci) / (2*(Ri-R1)).

[0117] In step S26, for the n cross sections of the first segment, the average thickness information K_ave of these cross sections can be calculated according to the following formula.

[0118]

[0119] In step S26, for the i-th section, the blade axis position of the i-th section can be calculated as (Dr-K_ave*(2*(Ri-R1))) / (2*Ci) based on the distance from the section to the blade root, the chord length of the section, and the average thickness information of the n sections in the first segment.

[0120] S104, for the second segment of the blade, the blade axis positions of multiple cross sections of the second segment are calculated based on the chord length distribution curve of the blade and the blade root diameter.

[0121] Optionally, for the second segment of the blade, based on the chord length distribution curve and the blade root diameter, the blade axis positions of multiple sections of the second segment are calculated, including:

[0122] C1, select multiple sections in the second segment of the blade;

[0123] C2. Based on the chord length distribution curve of the blade, determine the chord length of multiple sections in the second segment. The second segment is bounded by the target section and the blade root.

[0124] C3. Based on the chord length of multiple sections in the second segment and the blade root diameter, obtain the blade axis position of multiple sections in the second segment.

[0125] Please see Figure 3 The flowchart below shows a method for calculating the blade shaft position of the second segment of a blade, provided in an embodiment of this application. This process can be regarded as an optional specific implementation of step S104, and the process may include the following steps.

[0126] S31, select m cross-sections.

[0127] S32, interpolation yields the chord length Ci of section i.

[0128] S33, calculate the blade axis position of section i.

[0129] Wherein, step S31 is equivalent to step C1 above, step S32 is equivalent to step C2 above, and step S33 is equivalent to step C3 above.

[0130] The method of selecting m cross-sections in step S31 is the same as the method of selecting n cross-sections in step S21 above, and will not be repeated here.

[0131] In step S32, the distance Ri from each section i to the leaf root in the above m sections can be determined first. The method of determination is 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.

[0132] 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.

[0133] In step S33, for each section i of the second segment, the blade axis position of the section can be calculated as Dr / (2*Ci) based on the chord length Ci of the section and the diameter Dr of the blade root.

[0134] 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.

[0135] The beneficial effects of this plan are as follows:

[0136] 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.

[0137] 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.

[0138] This application also provides a device for determining the blade shaft position based on airfoil geometry features. Please refer to [link to relevant documentation]. Figure 6 This is a schematic diagram of the structure of the device, which may include the following units.

[0139] Selection unit 601 is used to select the target section based on the maximum chord length section of the blade;

[0140] The determining unit 602 is used to determine the location of the maximum thickness point of the suction surface and the maximum thickness point of the pressure surface of multiple sections of the first segment based on the chord length distribution curve of the blade, the relative thickness distribution curve, the geometric shape data of the standard airfoil and the relative thickness of the standard airfoil. The first segment is bounded by the target section and the blade tip.

[0141] The first calculation unit 603 is used to calculate the blade axis position of multiple cross sections of the first segment based on the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of multiple cross sections, the chord length and distance information of multiple cross sections, and the blade root diameter. The distance information represents the distance from the cross section to the blade root.

[0142] The second calculation unit 604 is used to calculate the blade axis position of multiple sections of the second segment of the blade based on the chord length distribution curve of the blade and the blade root diameter.

[0143] Optionally, when the second calculation unit 604 calculates the blade axis positions of multiple sections of the second segment of the blade based on the blade chord length distribution curve and the blade root diameter, it is specifically used for:

[0144] Multiple cross sections are selected in the second section of the blade;

[0145] Based on the chord length distribution curve of the blade, determine the chord length of multiple sections in the second segment, with the target section and the blade root as the boundary of the second segment;

[0146] Based on the chord length of multiple sections in the second segment and the blade root diameter, the blade axis position of multiple sections in the second segment is obtained.

[0147] Optionally, when determining the location of the maximum thickness point of the suction surface and the maximum thickness point of the pressure surface of multiple sections of the first segment based on the chord length distribution curve, relative thickness distribution curve, geometric shape data of the standard airfoil, and relative thickness of the standard airfoil, the determining unit 602 is specifically used for:

[0148] Select multiple cross sections in the first segment of the blade;

[0149] Based on the chord length distribution curve and relative thickness distribution curve of the blade, determine the relative thickness of multiple sections of the first segment;

[0150] Based on the geometric shape data of the standard airfoil, determine the location information of the maximum thickness point of the standard airfoil. The location information of the maximum thickness point includes the location of the maximum thickness point on the pressure surface and the location of the maximum thickness point on the suction surface.

[0151] Based on the relative thickness of multiple sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, interpolation is used to obtain the location of the maximum thickness point of the suction surface and the location of the maximum thickness point of the pressure surface of multiple sections.

[0152] Optionally, when the first calculation unit 603 calculates the blade axis position of the multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction surface and the pressure surface of the multiple cross-sections, the chord length and distance information of the multiple cross-sections, and the blade root diameter, it is specifically used for:

[0153] Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple cross sections in the first segment, as well as the blade root diameter, the location information of the pressure surface thickness of multiple cross sections in the first segment is calculated.

[0154] Based on the location, chord length, and distance information of the maximum suction surface thickness of multiple cross sections in the first segment, as well as the blade root diameter, the suction surface thickness location information of multiple cross sections in the first segment is calculated.

[0155] The blade shaft positions of multiple sections in the first segment are calculated based on the pressure surface thickness and suction surface thickness information of multiple sections in the first segment.

[0156] Optionally, when selecting the target section based on the maximum chord length section of the blade, the selection unit 601 is specifically used for:

[0157] Select the section with the maximum chord length of the blade as the target section;

[0158] Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

[0159] The device for determining the blade shaft position based on airfoil geometric features provided in this embodiment has the same working principle and beneficial effects as the method for determining the blade shaft position based on airfoil geometric features provided in this application embodiment, and will not be repeated here.

[0160] 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.

[0161] 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.

[0162] 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.

[0163] 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.

[0164] 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 for determining the blade axis position based on airfoil geometry, characterized in that, include: Select the target section based on the maximum chord length of the blade; Based on the chord length distribution curve and relative thickness distribution curve of the blade, the geometric shape data of the standard airfoil and the relative thickness of the standard airfoil, the positions of the maximum thickness points of the suction surface and the pressure surface of multiple cross sections of the first segment are determined, with the target cross section and the blade tip as the boundary of the first segment. Based on the positions of the maximum thickness points of the suction surface and the pressure surface of the multiple cross sections of the first segment, the chord length and distance information of the multiple cross sections, and the blade root diameter, the blade axis positions of the multiple cross sections of the first segment are calculated, and the distance information represents the distance from the cross section to the blade root. For the second segment of the blade, the blade axis positions of multiple cross sections of the second segment are calculated based on the chord length distribution curve of the blade and the blade root diameter. The step of calculating the blade axis position of the multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction surface and the pressure surface of the multiple cross-sections of the first segment, the chord length and distance information of the multiple cross-sections, and the blade root diameter of the blade includes: Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple cross sections of the first segment, as well as the root diameter of the blade, the pressure surface thickness location information of multiple cross sections of the first segment is calculated. Based on the location, chord length, and distance information of the maximum thickness point of the suction surface of multiple cross sections of the first segment, as well as the root diameter of the blade, the position information of the suction surface thickness of multiple cross sections of the first segment is calculated. The blade shaft positions of the multiple cross-sections of the first segment are calculated based on the pressure surface thickness position information and the suction surface thickness position information of the multiple cross-sections of the first segment, including: calculating the average thickness information based on the pressure surface thickness position information and the suction surface thickness position information of the multiple cross-sections of the first segment; for the i-th cross-section, the blade shaft position of the i-th cross-section is calculated according to the formula (Dr-K_ave*(2*(Ri-R1))) / (2*Ci), where Dr is the blade root diameter, K_ave is the average thickness information, Ri is the distance from the i-th cross-section to the blade root, R1 is the distance from the target cross-section to the blade root, and Ci is the chord of the i-th cross-section; Specifically, for the second segment of the blade, the blade axis positions of multiple cross-sections of the second segment are calculated based on the chord length distribution curve of the blade and the blade root diameter, including: Multiple cross sections are selected in the second section of the blade; Based on the chord length distribution curve of the blade, the chord lengths of multiple sections in the second segment are determined, with the target section and the blade root as the boundary of the second segment; Based on the chord length of multiple cross sections in the second segment and the blade root diameter, the blade axis position of multiple cross sections in the second segment is obtained; wherein, for each cross section i in the second segment, the calculated blade axis position of the cross section is Dr / (2*Ci).

2. The method according to claim 1, characterized in that, The step of determining the locations of the maximum thickness points of the suction surface and the pressure surface at multiple cross-sections of the first segment based on the chord length distribution curve, relative thickness distribution curve, geometric shape data of the standard airfoil, and relative thickness of the standard airfoil includes: Multiple cross sections are selected in the first segment of the blade; Based on the chord length distribution curve and relative thickness distribution curve of the blade, the relative thickness of multiple cross sections of the first segment is determined; Based on the geometric shape data of the standard airfoil, the location information of the maximum thickness point of the standard airfoil is determined. The location information of the maximum thickness point includes the location of the maximum thickness point of the pressure surface and the location of the maximum thickness point of the suction surface. Based on the relative thickness of the multiple cross sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, the locations of the maximum thickness points of the suction surface and the pressure surface of the multiple cross sections are obtained by interpolation.

3. The method according to claim 1, characterized in that, The step of selecting the target section based on the maximum chord length section of the blade includes: Select the section with the maximum chord length of the blade as the target section; Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

4. A device for determining the blade shaft position based on airfoil geometry, characterized in that, include: The selection unit is used to select the target section based on the maximum chord length section of the blade. The determining unit is used to determine the location of the maximum thickness point of the suction surface and the maximum thickness point of the pressure surface of multiple cross sections of the first segment based on the chord length distribution curve, relative thickness distribution curve of the blade, geometric shape data of the standard airfoil and relative thickness of the standard airfoil. The first segment is bounded by the target cross section and the blade tip. The first calculation unit is used to calculate the blade axis position of the multiple cross sections of the first segment based on the position of the maximum thickness point of the suction surface and the position of the maximum thickness point of the pressure surface of the multiple cross sections, the chord length and distance information of the multiple cross sections, and the blade root diameter of the blade. The distance information represents the distance from the cross section to the blade root. The second calculation unit is used to calculate the blade axis position of multiple cross sections of the second segment of the blade based on the chord length distribution curve of the blade and the blade root diameter. The step of calculating the blade axis position of the multiple cross-sections of the first segment based on the positions of the maximum thickness points of the suction surface and the pressure surface of the multiple cross-sections of the first segment, the chord length and distance information of the multiple cross-sections, and the blade root diameter of the blade includes: Based on the location, chord length, and distance information of the maximum thickness point of the pressure surface of multiple cross sections of the first segment, as well as the root diameter of the blade, the pressure surface thickness location information of multiple cross sections of the first segment is calculated. Based on the location, chord length, and distance information of the maximum thickness point of the suction surface of multiple cross sections of the first segment, as well as the root diameter of the blade, the position information of the suction surface thickness of multiple cross sections of the first segment is calculated. The blade shaft positions of the multiple cross-sections of the first segment are calculated based on the pressure surface thickness position information and the suction surface thickness position information of the multiple cross-sections of the first segment, including: calculating the average thickness information based on the pressure surface thickness position information and the suction surface thickness position information of the multiple cross-sections of the first segment; for the i-th cross-section, the blade shaft position of the i-th cross-section is calculated according to the formula (Dr-K_ave*(2*(Ri-R1))) / (2*Ci), where Dr is the blade root diameter, K_ave is the average thickness information, Ri is the distance from the i-th cross-section to the blade root, R1 is the distance from the target cross-section to the blade root, and Ci is the chord of the i-th cross-section; Specifically, when the second calculation unit calculates the blade axis positions of multiple cross-sections of the second segment of the blade based on the chord length distribution curve and the blade root diameter, it is used for: Multiple cross sections are selected in the second section of the blade; Based on the chord length distribution curve of the blade, the chord lengths of multiple sections in the second segment are determined, with the target section and the blade root as the boundary of the second segment; Based on the chord length of multiple cross sections in the second segment and the blade root diameter, the blade axis position of multiple cross sections in the second segment is obtained; wherein, for each cross section i in the second segment, the calculated blade axis position of the cross section is Dr / (2*Ci).

5. The apparatus according to claim 4, characterized in that, When the determining unit determines the positions of the maximum thickness points of the suction surface and the pressure surface of multiple cross-sections of the first segment based on the chord length distribution curve, relative thickness distribution curve, geometric shape data of the standard airfoil, and relative thickness of the standard airfoil, it is specifically used for: Multiple cross sections are selected in the first segment of the blade; Based on the chord length distribution curve and relative thickness distribution curve of the blade, the relative thickness of multiple cross sections of the first segment is determined; Based on the geometric shape data of the standard airfoil, the location information of the maximum thickness point of the standard airfoil is determined. The location information of the maximum thickness point includes the location of the maximum thickness point of the pressure surface and the location of the maximum thickness point of the suction surface. Based on the relative thickness of the multiple cross sections, the relative thickness of the standard airfoil, and the location of the maximum thickness point of the standard airfoil, the locations of the maximum thickness points of the suction surface and the pressure surface of the multiple cross sections are obtained by interpolation.

6. The apparatus according to claim 4, characterized in that, When the selection unit selects the target section based on the maximum chord length section of the blade, it is specifically used for: Select the section with the maximum chord length of the blade as the target section; Alternatively, select a section whose distance from the maximum chord length section of the blade is a preset value as the target section.

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