Rotor Blade Generation Method, Device, Computer, and Storage Medium

Abstract

The present invention relates to a method, device, computer and storage medium for generating a rotor blade. Among them, the method includes: specifying the basic parameters at different blade heights according to general blade design rules; discretizing the blade along the blade height direction to obtain a plurality of airfoil sections, and generating the mean camber line of each of the airfoil sections; setting bionic structure parameters and calculating the function of the bionic structure parameters changing with the radius according to a predetermined strategy; calculating the blade shape of each of the airfoil sections according to the basic parameters and the bionic structure parameters; translating the rotated blade shape correspondingly into three-dimensional space to form the blade shape corresponding to each of the airfoil sections in three-dimensional space; combining the blade shapes of each of the airfoil sections to finally form an integral blade. By integrating the design of bionic structure parameters in the blade design process, it is more compatible with the blade twist, bend, sweep and other shapes, the blade surface is smoother, the aerodynamic performance is better, and the aerodynamic noise of the entire rotor can be reduced.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of engine blades, and in particular, to a method and device for generating rotor blades, a computer, and a storage medium. Background Art

[0002] With the change of international oil prices and the continuous improvement of environmental protection policies, the economy and environmental performance of aero-engines have received attention. In recent years, propfans and contra-rotating open rotor (CROR) engines have ushered in a new development opportunity period. Their basic structure includes a hub 700, a front rotor 701, and a rear rotor 702, as specifically shown in Figure 1 FIG. The traditional airfoil design technology and flow control technology have become relatively perfect after decades of development. The effectiveness of drag reduction and noise reduction methods has relatively entered a bottleneck period, and it is difficult to further improve the blade performance by using existing design methods. Summary of the Invention

[0003] The embodiments of the present invention provide a method and device for generating rotor blades, a computer, and a storage medium, which have the advantages of improving the propulsion efficiency and reducing noise.

[0004] To solve the above technical problems, an embodiment of the present invention adopts a technical solution as follows:

[0005] A method for generating rotor blades, comprising:

[0006] Specifying the basic parameters of the blade at different blade heights according to general blade design rules;

[0007] Discretizing the blade along the blade height direction to obtain a plurality of airfoil sections, and generating the mean camber line of each airfoil section by using a predetermined generation method according to the basic parameters;

[0008] Setting bionic structure parameters and calculating the function of the bionic structure parameters changing with the radius according to a predetermined strategy, where the bionic structure parameters include: the bionic structure blade height range, the bionic structure type and curve equation, the bionic structure period number, and the bionic structure scale amplitude;

[0009] Calculating the blade shape of each airfoil section according to the basic parameters and the bionic structure parameters;

[0010] Taking the blade shape centroid as a reference, translating the rotated blade shape correspondingly into three-dimensional space to form the blade shape corresponding to each airfoil section in three-dimensional space;

[0011] Combining the blade shapes of each airfoil section to finally form an integral blade.

[0012] As a preferred embodiment of the present invention, the basic parameters include: the blade profile thickness curve, the function of thickness varying with radius, the function of chord length varying with radius, the blade profile angle of attack, the leading edge angle of the blade profile, the trailing edge angle of the blade profile, and the blade profile stacking axis.

[0013] As a preferred embodiment of the present invention, the specific method for generating the mean camber line is specifically: the parabola method, the double circular arc method, or the multi-circular arc method.

[0014] As a preferred embodiment of the present invention, the height range of the bionic structure includes the starting blade height R min and the ending blade height R max , and the types and curves of the bionic structure include: sawtooth wave, triangular wave, and sine wave;

[0015] After setting the number of cycles of the bionic structure as N wav , calculate the cycle length L c , where the cycle length L c =(R max -R min ) / N wav ;

[0016] After setting the scale amplitude A LE , A TE , calculate the change in leading edge chord length L LE and the change in trailing edge chord length L TE at each blade height.

[0017] As a preferred embodiment of the present invention, after determining the type and curve of the bionic structure, specify its starting phase ψ start , and the curve equation is denoted as z = f(r, ψ start ), where r = R c / R, R c is the current blade height radius, and R is the total blade height.

[0018] As a preferred embodiment of the present invention, the specific process of calculating the blade profile of each airfoil section according to the basic parameters and bionic structure parameters includes:

[0019] After generating the pressure surface and suction surface curves according to the specified mean camber line generation method, modify the leading edge and trailing edge according to the bionic structure parameters;

[0020] Select a deformation center within a predetermined range on the blade chord length, and perform chordwise equal-proportion scaling on the first half and / or the second half of the blade according to the bionic structure parameters;

[0021] Scale the blade profile of each corresponding airfoil section proportionally according to the required chord length and thickness to finally generate the blade profile at this blade height.

[0022] As a preferred embodiment of the present invention, the method of corresponding translation of the rotated airfoil to form an airfoil in three-dimensional space with respect to the centroid of the airfoil specifically includes:

[0023] After calculating the angle of attack of the oncoming flow according to the actual working conditions and design specifications, specify a rotation axis to rotate the airfoil;

[0024] With the centroid of the airfoil as the reference, translate it to the corresponding position in three-dimensional space along the stacking axis;

[0025] Map each coordinate point on the airfoil to a cylindrical surface with r = 0 and a radius equal to the corresponding airfoil height to form an airfoil in three-dimensional space.

[0026] To solve the above technical problems, an embodiment of the present invention also provides a bionic open rotor blade generation device, including:

[0027] A parameter setting unit for specifying the basic parameters at different airfoil heights of the blade according to general blade design rules;

[0028] A first generation unit for discretizing the blade in the airfoil height direction to obtain a plurality of airfoil sections, and generating the mean camber line of each airfoil section using a predetermined generation method according to the basic parameters;

[0029] A bionic calculation unit for setting bionic structure parameters and calculating the function of bionic structure parameters varying with the radius according to a predetermined strategy. The bionic structure parameters include: the bionic structure airfoil height range, the type and curve equation of the bionic structure, the number of bionic structure periods, and the bionic structure scale amplitude;

[0030] An airfoil calculation unit for calculating the airfoil of each airfoil section according to the basic parameters and bionic structure parameters;

[0031] A three-dimensional mapping unit for corresponding translation of the rotated airfoil to form an airfoil in three-dimensional space corresponding to each airfoil section with the centroid of the airfoil as the reference;

[0032] A second generation unit for combining the airfoils of each airfoil section to finally form an integral blade.

[0033] As a preferred embodiment of the present invention, the basic parameters set by the parameter setting unit include: the airfoil thickness curve, the function of thickness varying with the radius, the function of chord length varying with the radius, the airfoil angle of attack, the airfoil leading edge angle, the airfoil trailing edge angle, and the airfoil stacking axis.

[0034] As a preferred embodiment of the present invention, the predetermined generation method for generating the mean camber line by the first generation unit specifically includes: the parabola method, the double circular arc method, or the multi-circular arc method.

[0035] As a preferred embodiment of the present invention, in the bionic structure parameters set by the bionic computing unit, the bionic structure blade height range includes a starting blade height R min and an ending blade height R max , and the bionic structure types and curves include: sawtooth wave, triangular wave, and sine wave;

[0036] After setting the number of bionic structure periods as N wav , calculate the period length L c , where the period length L c =(R max -R min ) / N wav ;

[0037] After setting the bionic structure scale amplitudes A LE , A TE , calculate the leading edge chord length change amount L LE and the trailing edge chord length change amount L TE at each blade height.

[0038] As a preferred embodiment of the present invention, after the bionic computing unit determines the bionic structure type and curve, it specifies its starting phase ψ start , and the curve equation is denoted as z = f(r, ψ start ), where r = R c / R, R c is the current blade height radius, and R is the total blade height.

[0039] As a preferred embodiment of the present invention, the airfoil calculation unit includes:

[0040] A shaping module, which is used to generate the pressure surface and suction surface curves according to the specified mean camber line generation method, and then shape the leading edge and trailing edge according to the bionic structure parameters;

[0041] A scaling module, which is used to select a deformation center within a predetermined range on the blade chord length, and perform chordwise equal-proportion scaling on the front half and / or the rear half of the blade according to the bionic structure parameters;

[0042] An airfoil generation module, which is used to proportionally scale the airfoil shapes of the corresponding airfoil sections according to the required chord length and thickness to finally generate the airfoil shape at this blade height.

[0043] As a preferred embodiment of the present invention, the three-dimensional mapping unit includes:

[0044] An airfoil rotation module, which is used to calculate the angle of attack of the oncoming flow according to the actual working conditions and design indicators, and then specify a rotation axis to rotate the airfoil shape;

[0045] A three-dimensional translation module, which is used to translate to the corresponding position in the three-dimensional space with the airfoil centroid as the reference along the stacking axis;

[0046] A three-dimensional mapping module, configured to map each coordinate point on the blade profile to a cylindrical surface with r = 0 and a radius equal to the corresponding blade height to form a blade profile in three-dimensional space.

[0047] To solve the above technical problems, an embodiment of the present invention further provides a computer device, including a memory and a processor. Computer-readable instructions are stored in the memory. When the computer-readable instructions are executed by the processor, the processor executes the steps of the above-mentioned bionic open rotor blade generation method.

[0048] To solve the above technical problems, an embodiment of the present invention further provides a storage medium storing computer-readable instructions. When the computer-readable instructions are executed by one or more processors, the one or more processors execute the steps of the above-mentioned bionic open rotor blade generation method.

[0049] In summary, the present invention has the following beneficial effects:

[0050] By providing a rotor blade generation method, device, computer, and storage medium, the present invention incorporates bionic structure parameter design in the blade design process, enabling the generated blades to have bionic structures. Compared with the traditional method of directly modifying the blade on a three-dimensional blade, this method can fully combine the blade profile characteristics at different blade heights, better fit the blade twist, bend, sweep, etc. The blade surface is smoother, the aerodynamic performance is better, which can reduce the aerodynamic noise of the entire rotor, and the blades generated by the present invention can ensure that the blade surface area and volume are basically the same as those of the blades designed by the traditional method, thereby having less impact on the overall design of the engine and other systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0052] Figure 1 It is a schematic diagram of the basic structure of an open rotor in the background art of the present invention.

[0053] Figure 2 It is a schematic diagram of the basic process of the bionic open rotor blade generation method in an embodiment of the present invention.

[0054] Figure 3 It is a schematic diagram of generating a mean camber line in an embodiment of the present invention.

[0055] Figure 4Schematic diagram of the parameters in the spanwise direction for the embodiments of the present invention.

[0056] Figure 5 Schematic diagram of the bionic structure parameters for the embodiments of the present invention.

[0057] Figure 6 Schematic diagram of the trailing edge triangular wave curve for the embodiments of the present invention.

[0058] Figure 7 Schematic diagram of the first half of the blade scaled proportionally in the chordwise direction according to the structural parameters with point O as the center of variation for the embodiments of the present invention.

[0059] Figure 8 Schematic diagram of the original blade shape generated for the embodiments of the present invention.

[0060] Figure 9 Schematic diagram of the bionic blade shape at a certain blade height generated according to the given bionic structure parameters for the embodiments of the present invention.

[0061] Figure 10 Schematic diagram of the blade shape after being scaled proportionally according to the thickness and chord length for the embodiments of the present invention.

[0062] Figure 11 is Figure 10 an enlarged view of the left part.

[0063] Figure 12 Schematic diagram of the blade shape after translation and rotation in a certain blade height section for the embodiments of the present invention.

[0064] Figure 13 Schematic diagram of the blade model generated for the embodiments of the present invention.

[0065] Figure 14 Schematic diagram of the final open rotor blade generated for the embodiments of the present invention.

[0066] Figure 15 Comparison diagram of the far-field directivity results of the noise of the bionic open rotor and the open rotor without bionic structure generated for the embodiments of the present invention.

[0067] Figure 16 Schematic diagram of the basic structure of the bionic open rotor blade generation device for the embodiments of the present invention;

[0068] Figure 17 Basic structure block diagram of the computer for the embodiments of the present invention.

[0069] The corresponding component names represented by the numbers and letters in the figure:

[0070] 700, Wheel hub; 701, Front rotor; 702, Rear rotor; 801, Parameter setting unit; 802, First generation unit; 803, Bionic computing unit; 804, Blade profile computing unit; 805, Three-dimensional mapping unit; 806, Second generation unit. Detailed implementation manners

[0071] In order to enable those skilled in the art of the present technology to better understand the solution of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0072] In some processes described in the specification, claims and the above-mentioned accompanying drawings of the present invention, a plurality of operations appear in a specific order. However, it should be clearly understood that these operations may not be executed in the order in which they appear herein or may be executed in parallel. The serial numbers of the operations, such as 101, 102, etc., are only used to distinguish different operations, and the serial numbers themselves do not represent any execution order. In addition, these processes may include more or fewer operations, and these operations may be executed in sequence or in parallel. It should be noted that the descriptions such as "first" and "second" in this article are used to distinguish different messages, devices, modules, etc., and do not represent a sequence, nor do they limit that "first" and "second" are of different types.

[0073] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present invention.

[0074] Specifically, please refer to Figure 2 , Figure 2 , which is a schematic diagram of the basic process of the rotor blade generation method in this embodiment.

[0075] As Figure 2 shown, a rotor blade generation method includes:

[0076] S100. Specify the basic parameters at different blade heights according to the general blade design rules, where the basic parameters include: blade profile thickness curve, thickness variation function with radius, chord length variation function with radius, blade profile attack angle, blade profile leading edge angle, blade profile trailing edge angle, and blade profile stacking axis.

[0077] S200. Discretize the blade along the blade height direction to obtain a plurality of airfoil sections, and generate the mean camber line of each airfoil section by using a predetermined generation method according to the basic parameters. The specific predetermined generation method for generating the mean camber line includes: parabola method, double circular arc method, or multi-circular arc method.

[0078] S300. Set the bionic structure parameters and calculate the function of the bionic structure parameters varying with the radius according to a predetermined strategy. The bionic structure parameters include: the bionic structure blade height range, the bionic structure type and curve equation, the number of bionic structure periods, and the bionic structure scale amplitude.

[0079] Specifically, the bionic structure blade height range includes the starting blade height R min and the ending blade height R max . The bionic structure types and curves include: sawtooth wave, triangular wave, and sine wave. After determining the bionic structure type and curve, specify its starting phase ψ start . The curve equation is denoted as z = f(r, ψ start ), where r is the normalized blade height, r = R c / R, R c is the current blade height radius, and R is the total blade height; after setting the number of bionic structure periods as N wav , calculate the period length L c , where the period length L c =(R max -R min ) / N wav ; after setting the bionic structure scale amplitudes A LE and A TE , calculate the leading edge chord length variation L LE and the trailing edge chord length variation L TE at each blade height. The bionic structure scale amplitude is related to the blade height and the chord length corresponding to that blade height, and can be expressed as A LE (r, C), or can be a constant.

[0080] S400. Calculate the blade shapes of each airfoil section according to the basic parameters and the bionic structure parameters.

[0081] Specifically, it includes:

[0082] S401. After generating the pressure surface and suction surface curves according to the specified mean camber line generation method, modify the leading edge and trailing edge according to the bionic structure parameters;

[0083] S402. Select a deformation center within a predetermined range on the blade chord length, and perform chordwise equal - ratio scaling on the first half and / or the second half of the blade according to the bionic structure parameters. Generally, the predetermined range on the chord length can be set at 30% - 70%. For the leading edge, after specifying the deformation center, perform chordwise equal - ratio scaling on the first half of the blade according to the bionic structure parameters. For the trailing edge, after specifying the deformation center (the deformation center can be the same as the one specified for the leading edge), perform chordwise equal - ratio scaling on the second half of the blade according to the bionic structure parameters;

[0084] S403. Scale the corresponding airfoil sections proportionally according to the required chord length and thickness to finally generate the airfoil shape at this blade height.

[0085] S500. With the centroid of the airfoil shape as the reference, translate the rotated airfoil shape correspondingly into the three-dimensional space to form the airfoil shape corresponding to each airfoil section in the three-dimensional space.

[0086] Specifically, it includes:

[0087] S501. After calculating the oncoming flow angle of attack according to the actual working conditions and design indicators, specify a rotation axis to rotate the airfoil shape;

[0088] S502. With the centroid of the airfoil shape as the reference, translate it to the corresponding position in the three-dimensional space along the stacking axis;

[0089] S503. Map each coordinate point on the airfoil shape to a cylindrical surface with r = 0 and a radius equal to the corresponding blade height to form the airfoil shape in the three-dimensional space, where r is the blade height value.

[0090] S600. Combine the airfoil shapes of each airfoil section to finally form the overall blade.

[0091] After generating a group of blades with bionic structures through the above method, replicating several blades around the circumference according to requirements can complete the design of the entire rotor.

[0092] In the actual design process, different treatments can be selected for the leading edge and trailing edge of the front rotor and the rear rotor of the open rotor engine as needed, that is, the leading edge of the front rotor, the trailing edge of the front rotor, the leading edge of the rear rotor, and the trailing edge of the rear rotor, a total of four positions, are processed as needed; at the same time, at each position (such as the trailing edge of the front rotor), the partial blade height range within 10%-100% of the total blade height can be processed according to the design requirements. For each position, the key parameters of the bionic structure include the number of bionic structure periods N wav , the scale amplitude A(r, C) of the bionic structure, the starting phase ψ start , and the bionic structure curve z = f(r, ψ start ) etc.

[0093] The rotor blade generation method of the embodiment of the present invention incorporates the design of bionic structure parameters in the blade design process, making the generated blades have bionic structures. Compared with the traditional method of directly modifying the blade on the three-dimensional blade, this method can fully combine the airfoil shape characteristics at different blade heights, is more compatible with the blade twist, bend, sweep and other shapes, the blade surface is smoother, the aerodynamic performance is better, it can reduce the aerodynamic noise of the entire rotor, and the blades generated by the present invention can ensure that the blade surface area and volume are basically the same as those of the blades designed by the traditional method, thus having less impact on the overall design of the engine and other systems.

[0094] The rotor blade generation method of the present invention will be further described below with a specific embodiment. This specific embodiment takes the blade with a serrated structure added to the trailing edge of the front rotor as an example, and specifically includes:

[0095] Step 1: According to the general blade design rules and design condition requirements, specify the basic parameters at different blade heights. These basic parameters are obtained by theoretical calculations of the design of high-subsonic propfan blades or open-rotor engine blades or by engineering experience. The basic parameters include the blade thickness curve y = f(x), the function of thickness varying with radius T = T(r), the function of chord length varying with radius C = C(r), the blade angle of attack α = α(r), the leading-edge angle of the blade shape χ1(r), the trailing-edge angle of the blade shape χ2(r), the stacking axis of the blade shape S = S(r), etc.

[0096] Step 2: For different blade height positions r, design the mean camber line according to the leading-edge angle and trailing-edge angle of the blade shape. In this embodiment, the double-circular arc method is used to generate the mean camber line. The generated mean camber line and the generated basic blade are as Figure 3 shown.

[0097] Step 3: Calculate the trailing-edge structure parameters of the front rotor according to the given basic parameters, and obtain the function of the bionic structure parameters varying with radius. In this embodiment, only the trailing edge of the front rotor adds a serrated bionic structure. Specify the blade height range of the bionic structure as the starting blade height R min = 0.84R, the ending blade height R max = R, as Figure 4 shown, Figure 4 is the schematic diagram of the blade height direction parameters in the embodiment of the present invention; as Figure 5 shown, Figure 5 is the schematic diagram of the bionic structure parameters in the embodiment of the present invention. Specify the type of the bionic structure as a triangular wave, the number of bionic structure periods N wav = 7, the scale amplitude of the bionic structure A LE = 0, A TE = 0.15C, the length of each period L c = (R max - R min ) / N wav = 0.0229R; According to the above parameters, calculate the elongation of the trailing-edge chord length L TE at each blade height, as Figure 6 shown, Figure 6 is the schematic diagram of the trailing-edge triangular wave curve in the embodiment of the present invention, where the blade shape in a certain section near the blade tip is as Figure 7 shown.

[0098] Step 4: For each discrete section, calculate the blade shape at each blade height according to the selected blade shape, mean camber line equation, chord length, thickness, and bionic structure parameters. First, generate the pressure side and suction side curves according to the blade shape and the specified mean camber line equation, as specifically shown in Figure 8 as follows, Figure 8 is the schematic diagram of the original blade shape generated in the embodiment of the present invention; in this embodiment, for the trailing edge, the specified deformation center is 0.5C, and the second half of the blade is scaled proportionally according to the bionic structure parameters, as shown in Figure 9 as follows, Figure 9 is the schematic diagram of the bionic blade shape at a certain blade height generated according to the given bionic structure parameters in the embodiment of the present invention; finally, scale the blade shape proportionally according to the chord length and thickness required for the cross-section at this blade height to generate the blade shape at this blade height, as shown in Figure 10 and Figure 11 as follows, Figure 10 is the schematic diagram of the blade shape scaled proportionally according to the thickness and chord length in the embodiment of the present invention, Figure 11 is Figure 10 the enlarged view of the left part.

[0099] Step 5: Translate the rotated blade shape to the corresponding position in three-dimensional space along the stacking axis S(r). In this embodiment, a S(r) with sweep is specified for each of the two rows of rotors, and the S direction is taken as the axis direction, that is, the z-axis direction. The translation vector for each cross-section is Then, according to the working conditions and design specifications, calculate the appropriate incoming flow angle of attack α(r), and specify a rotation axis to rotate the blade shape; in this embodiment, it is specified that the incoming flow angle of attack of each cross-section is parallel to the incoming flow velocity under this working condition, and α(r) can be obtained through the calculation of the velocity triangle. The result after rotation and translation of a certain cross-section can be referred to Figure 12 , Figure 12 is the schematic diagram of the blade shape after translation and rotation at a certain blade height cross-section in the embodiment of the present invention; finally, draw a perpendicular line from each coordinate point on the blade shape to the axis, and intercept a length point at the radius of the specified cross-section blade height on the perpendicular line as the actual coordinate point of the blade shape. The actual coordinate points of the blade shape are mapped onto a cylindrical surface with r = 0 as the axis and a radius equal to the corresponding blade height.

[0100] Step 6: Combine the blade shapes at different blade heights to generate the overall blade shape. In this embodiment, the finally combined blade is as shown in Figure 13 and Figure 14 as follows, Figure 13 is the schematic diagram of the blade model generated in the embodiment of the present invention, Figure 14 is the schematic diagram of the open rotor blade finally generated in the embodiment of the present invention.

[0101] According to the bionic open rotor blade of this embodiment, it is imported into the computational fluid dynamics simulation calculation software for calculation. The calculation is smooth and converges well, and the flow field and noise characteristics under the corresponding working conditions are obtained. Refer to Figure 15 ,Figure 15 This is a comparison chart of the far-field directivity results of the bionic open rotor and the open rotor without bionic structure generated in the embodiment of the present invention. It can be seen from Figure 15 that the noise of this blade is generally reduced compared with the blade without bionic structure, which proves that the blade generated by this method can effectively reduce noise.

[0102] To solve the above technical problems, the embodiment of the present invention also provides a rotor blade generation device.

[0103] Specifically, please refer to Figure 16 , Figure 16 which is a schematic diagram of the basic structure of the rotor blade generation device in this embodiment.

[0104] As Figure 16 shown, a rotor blade generation device includes: a parameter setting unit 801 for specifying basic parameters at different blade heights according to general blade design rules; a first generation unit 802 for discretizing the blade height and then generating a mean camber line according to the basic parameters by using a predetermined generation method; a bionic calculation unit 803 for setting bionic structure parameters and calculating the function of bionic structure parameters varying with the radius according to a predetermined strategy, where the bionic structure parameters include: the bionic structure blade height range, the bionic structure type and curve equation, the number of bionic structure periods, and the bionic structure scale amplitude; a blade shape calculation unit 804 for calculating the blade shape at each blade height according to the basic parameters and bionic structure parameters corresponding to the discrete cross-sections at each blade height; a three-dimensional mapping unit 805 for taking the blade shape centroid as a reference and translating the rotated blade shape to the three-dimensional space correspondingly to form the blade shape corresponding to each blade height in the three-dimensional space; a second generation unit 806 for combining the blade shapes at each blade height to finally generate an overall blade.

[0105] Among them, the basic parameters set by the parameter setting unit 801 include: the blade shape thickness curve, the function of thickness varying with the radius, the function of chord length varying with the radius, the blade shape angle of attack, the blade shape leading edge angle, the blade shape trailing edge angle, and the blade shape stacking axis; the predetermined generation method for the first generation unit 802 to generate the mean camber line specifically includes: the parabola method, the double circular arc method, or the multi-circular arc method.

[0106] Among the bionic structure parameters set by the bionic computing unit 803, the bionic structure leaf height range includes the starting leaf height R_min and the ending leaf height R_max. The bionic structure types and curves include: sawtooth wave, triangular wave, and sine wave. After setting the number of bionic structure periods as N_wav, the period length L_c is calculated, where the period length L_c = 〖(R_max - R_min) / N〗_wav. After setting the bionic structure scale amplitudes A_LE and A_TE, the leading edge chord length change L_LE and the trailing edge chord length change L_TE at each leaf height are calculated. After the bionic computing unit 803 determines the bionic structure type and curve, its starting phase ψ_start is specified, and the curve equation is denoted as z = f(r, ψ_start), where r = R_c / R, R_c is the current leaf height radius, and R is the total leaf height.

[0107] In some embodiments, the airfoil calculation unit 804 includes: a profiling module, which is used to generate the pressure surface and suction surface curves according to the specified mean camber line generation method, and then profile the leading edge and trailing edge according to the bionic structure parameters; a scaling module, which is used to select a deformation center within a predetermined range of the blade chord length, and perform chordwise equal-proportion scaling on the front half and / or the rear half of the blade according to the bionic structure parameters; an airfoil generation module, which is used to proportionally scale the airfoil shape of each corresponding airfoil section according to the required chord length and thickness to finally generate the airfoil shape at this leaf height.

[0108] In some embodiments, the three-dimensional mapping unit 805 includes: an airfoil rotation module, which is used to calculate the inflow attack angle according to the actual working conditions and design indicators, and then specify a rotation axis to rotate the airfoil shape; a three-dimensional translation module, which is used to translate to the corresponding position in the three-dimensional space with the airfoil centroid as the reference along the stacking axis; a three-dimensional mapping module, which is used to map each coordinate point on the airfoil shape to a cylindrical surface with r = 0 and a radius equal to the corresponding leaf height to form the airfoil shape in the three-dimensional space.

[0109] By integrating the bionic structure parameter design into the blade design process, the bionic open rotor blade generation device makes the generated blade have a bionic structure. Compared with the traditional method of directly profiling the blade on the three-dimensional blade, this method can fully combine the airfoil shape characteristics at different leaf heights, be more compatible with the blade twist, bend, sweep and other shapes, the blade surface is smoother, the aerodynamic performance is better, which can reduce the aerodynamic noise of the entire rotor, and the blade generated by the present invention can ensure that the blade surface area and volume are basically the same as those of the blade designed by the traditional method, and thus has less impact on the overall design of the engine and other systems.

[0110] To solve the above technical problems, the embodiment of the present invention also provides a computer device. For details, please refer to Figure 17 , Figure 17 which is the basic structural block diagram of the computer in this embodiment.

[0111] AsFigure 17 As shown, it is a schematic diagram of the internal structure of a computer device. The computer device includes a processor, a non-volatile storage medium, a memory, and a network interface connected through a system bus. Among them, the non-volatile storage medium of the computer device stores an operating system, a database, and computer-readable instructions. The control information sequence can be stored in the database. When the computer-readable instructions are executed by the processor, the processor can implement a method for generating bionic open rotor blades. The processor of the computer device is used to provide computing and control capabilities to support the operation of the entire computer device. Computer-readable instructions can be stored in the memory of the computer device. When the computer-readable instructions are executed by the processor, the processor can execute a method for generating bionic open rotor blades. The network interface of the computer device is used to connect and communicate with the terminal. Those skilled in the art can understand that Figure 16 the structure shown in [the figure] is only a block diagram of some structures related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0112] In this embodiment, the processor is used to execute Figure 16 the specific functions of the parameter setting unit 801, the first generation unit 802, the bionic calculation unit 803, the blade shape calculation unit 804, the three-dimensional mapping unit 805, and the second generation unit 806 in [the figure]. The memory stores the program codes and various types of data required to execute the above modules. The network interface is used for data transmission between the user terminal or the server. The server can call the program codes and data of the server to execute the functions of all sub-modules.

[0113] When the computer device generates a blade, by integrating the bionic structure parameter design in the blade design process, the generated blade has a bionic structure. Compared with the traditional method of directly modifying the blade on a three-dimensional blade, this method can fully combine the blade shape characteristics at different blade heights, is more compatible with the blade twist, bend, sweep and other shapes, the blade surface is smoother, the aerodynamic performance is better, it can reduce the aerodynamic noise of the entire rotor, and the blade generated by the present invention can ensure that the blade surface area and volume are basically the same as those of the blade designed by the traditional method, and thus has less impact on the overall design of the engine and other systems.

[0114] The present invention also provides a storage medium storing computer-readable instructions. When the computer-readable instructions are executed by one or more processors, one or more processors are caused to execute the steps of the method for generating bionic open rotor blades in any of the above embodiments.

[0115] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above methods. Among them, the aforementioned storage medium can be a non-volatile storage medium such as a magnetic disk, an optical disk, a read-only memory (ROM), or a random access memory (RAM), etc.

[0116] It should be understood that although the steps in the flowchart of the accompanying drawings are shown in sequence according to the indication of the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless there is a clear indication in this article, the execution of these steps has no strict order limit and can be executed in other orders. Moreover, at least a part of the steps in the flowchart of the accompanying drawings may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. Their execution order is not necessarily sequential, but can be executed alternately or alternately with at least a part of other steps or sub-steps or stages of other steps.

Claims

1. A method for generating a rotor blade, characterized in that, Including: Specify the basic parameters at different heights of the blade according to the general blade design rules; Along the height direction of the blade, discretize the blade to obtain multiple airfoil sections, and generate the mean camber line of each airfoil section using a predetermined generation method according to the basic parameters; Set the bionic structure parameters and calculate the function of the bionic structure parameters changing with the radius according to a predetermined strategy. The bionic structure parameters include: the bionic structure height range, the type and curve equation of the bionic structure, the number of bionic structure periods, and the bionic structure scale amplitude; After generating the pressure surface and suction surface curves according to the specified mean camber line generation method, modify the leading edge and trailing edge according to the bionic structure parameters; Select a deformation center within a predetermined range of the blade chord length, and perform chordwise equal-proportion scaling on the first half and / or the second half of the blade according to the bionic structure parameters; Scale the airfoil shape proportionally according to the required chord length and thickness for each corresponding airfoil section to finally generate the airfoil shape at this height; Based on the centroid of the airfoil shape, translate the rotated airfoil shape to the corresponding position in three-dimensional space to form the airfoil shape corresponding to each airfoil section in three-dimensional space; Combine the airfoil shapes of each airfoil section to finally form the overall blade.

2. The rotor blade generation method according to claim 1, characterized in that, The basic parameters include: the airfoil thickness curve, the function of the thickness changing with the radius, the function of the chord length changing with the radius, the airfoil angle of attack, the airfoil leading edge angle, the airfoil trailing edge angle, and the airfoil stacking axis.

3. The rotor blade generation method according to claim 2, characterized in that, The specific predetermined generation method for generating the mean camber line includes: the parabola method, the double-arc method, or the multi-arc method.

4. The rotor blade generation method according to claim 3, wherein The height range of the bionic structure includes the starting height R min and the ending height R max , and the types and curves of the bionic structure include: sawtooth wave, triangular wave, and sine wave; Set the number of bionic structure periods as N wav After that, calculate the period length L c , where the period length L c =(R max -R min ) / N wav ; Set the amplitude A of the bionic structure scale LE , A TE After that, calculate the change amount L of the leading edge chord length at each blade height LE and the change amount L of the trailing edge chord length TE .

5. The rotor blade generation method according to claim 4, characterized in that, After determining the type and curve of the bionic structure, specify its starting phase ψ start , and the curve equation is denoted as z = f(r, ψ start ), where r = R c / R, R c is the current blade height radius, and R is the total blade height.

6. The rotor blade generation method according to claim 1, characterized in that, The step of translating the rotated airfoil shape to the corresponding position in three-dimensional space based on the centroid of the airfoil shape to form the airfoil shape corresponding to each airfoil section in three-dimensional space specifically includes: After calculating the incoming flow angle of attack according to the actual working conditions and design indicators, specify a rotation axis to rotate the airfoil shape; Based on the centroid of the airfoil shape, translate it to the corresponding position in three-dimensional space according to the stacking axis; Map each coordinate point on the airfoil shape to a cylindrical surface with r = 0 and a radius equal to the corresponding blade height to form the airfoil shape in three-dimensional space.

7. A rotor blade generating device, characterized in that, Including: A parameter setting unit for specifying the basic parameters at different heights of the blade according to the general blade design rules; A first generation unit for discretizing the blade along the height direction to obtain multiple airfoil sections, and generating the mean camber line of each airfoil section using a predetermined generation method according to the basic parameters; A bionic calculation unit for setting the bionic structure parameters and calculating the function of the bionic structure parameters changing with the radius according to a predetermined strategy. The bionic structure parameters include: the bionic structure height range, the type and curve equation of the bionic structure, the number of bionic structure periods, and the bionic structure scale amplitude; An airfoil shape calculation unit for generating the pressure surface and suction surface curves according to the specified mean camber line generation method, and then modifying the leading edge and trailing edge according to the bionic structure parameters; selecting a deformation center within a predetermined range of the blade chord length, and performing chordwise equal-proportion scaling on the first half and / or the second half of the blade according to the bionic structure parameters; scaling the airfoil shape proportionally according to the required chord length and thickness for each corresponding airfoil section to finally generate the airfoil shape at this height; A three-dimensional mapping unit, configured to translate the rotated leaf shape to a three-dimensional space with the centroid of the leaf shape as a reference to form a leaf shape corresponding to each of the airfoil sections in the three-dimensional space; A second generation unit, configured to combine the leaf shapes of each of the airfoil sections to finally form an integral blade.

8. A computer, comprising a memory and a processor, wherein computer-readable instructions are stored in the memory, and when the computer-readable instructions are executed by the processor, the processor is caused to execute the steps of the rotor blade generation method according to any one of claims 1 to 6.

9. A storage medium storing computer-readable instructions, and when the computer-readable instructions are executed by one or more processors, the one or more processors are caused to execute the steps of the rotor blade generation method according to any one of claims 1 to 6.

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