CN111783222A - Grid encryption method suitable for high-precision simulation of forward-flying rotor blade tip vortex - Google Patents

Grid encryption method suitable for high-precision simulation of forward-flying rotor blade tip vortex Download PDF

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CN111783222A
CN111783222A CN202010539684.8A CN202010539684A CN111783222A CN 111783222 A CN111783222 A CN 111783222A CN 202010539684 A CN202010539684 A CN 202010539684A CN 111783222 A CN111783222 A CN 111783222A
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叶舟
展凤江
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Nanjing Changkong Technology Co ltd
Nanjing Pukou High-Tech Industrial Development Zone Management Committee
Nanjing University of Aeronautics and Astronautics
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Nanjing Changkong Technology Co ltd
Nanjing Pukou High-Tech Industrial Development Zone Management Committee
Nanjing University of Aeronautics and Astronautics
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Abstract

The invention provides a grid encryption method suitable for high-precision simulation of a front flying rotor blade tip vortex, which comprises the following steps of: step 1: generating an initial two-dimensional airfoil grid in advance, and selecting a reference grid line in the normal direction in the grid as an interpolation reference; step 2: generating a new grid line; and step 3: traversing each grid point on a new grid line, projecting the grid point onto a reference grid line, and recording the position information and coordinates of the points; step 4, encrypting the grid lines on all the reference grid lines around the airfoil direction to obtain an encrypted two-dimensional airfoil grid; step 5, encrypting the blade tip grid nodes of the linear interpolation section of the blade to generate a C-O type blade body-fitted grid; and 6, encrypting the blade tip turnover grids to obtain the encrypted blade grids. The encryption method can encrypt the grid nodes in the normal direction and the span direction of the blade grid, so that a set of blade grid with the high-precision capturing capability of the tip vortex is generated.

Description

Grid encryption method suitable for high-precision simulation of forward-flying rotor blade tip vortex
Technical Field
The invention belongs to the technical field of helicopter rotor Computational Fluid Dynamics (CFD), and particularly relates to a grid encryption method suitable for high-precision simulation of a front flying rotor blade tip vortex.
Background
A high-quality grid system is the basis of high-precision numerical simulation of rotor tip vortex, and the requirements of different aerodynamic problems on grids are greatly different. For the simulation of the rotor tip vortex wake flow field, the conventional grid generation and encryption method cannot meet the precision requirement. The blade tip vortex is formed on the boundary layer of the blade tip, high-precision capture of boundary layer airflow is the key of generation and evolution simulation of the blade tip vortex, and the traditional blade grid generation method can only be used for calculation of aerodynamic force of the rotor blade and cannot meet the fine capture requirement of the blade tip vortex. Therefore, the blade grid encryption method becomes a core technology for high-precision simulation of the tip vortex, and the blade grid encryption has two key points:
the key point is as follows: and the normal nodes of the two-dimensional airfoil grid of the blade section are encrypted. The generation and evolution processes of the blade tip vortex are captured in the span-wise section of the blade, and the normal grid nodes of the span-wise grid are consistent with the normal grid nodes of the two-dimensional airfoil section, so that the normal grid nodes of the two-dimensional airfoil section need to be encrypted.
The key point II is as follows: and (4) encryption of the paddle spanwise grid. The method comprises the encryption of two grids, wherein one grid is a span-wise turnover area of the blade grid, and the other grid is a span-wise linear interpolation area of the blade grid at the blade tip. The generation of the blade tip vortex and the capture of the evolution process are realized by simulating the flowing details of the transverse airflow, and the transverse airflow is mainly concentrated at the rotor blade tip, so that the encryption of the grid node distribution of the two areas is particularly important.
Disclosure of Invention
The invention aims to provide a blade grid encryption method suitable for high-precision simulation of a rotor tip vortex. C-O type blade grids are generated by adopting a traditional method, and normal and spanwise grid nodes of the blade grids are encrypted by adopting the encryption method disclosed by the invention on the basis, so that a set of blade grids with high-precision blade tip vortex capture capability is generated.
The technical scheme for realizing the above purpose of the invention is as follows:
a grid encryption method suitable for high-precision simulation of a front flying rotor blade tip vortex comprises the following steps:
step 1: generating an initial two-dimensional airfoil grid with good orthogonality in advance, and selecting a reference grid line in the normal direction in the grid as an interpolation reference, wherein the reference grid line is a grid line 1;
step 2: generating a new grid line which meets the high-precision capturing requirement of the tip vortex, namely a grid line 2;
and step 3: traversing each grid point on a new grid line, projecting the grid point onto a reference grid line, recording the position information of the points on the reference grid line, and calculating the coordinates of the grid points on the reference grid line;
step 4, surrounding the airfoil shape direction, encrypting grid lines on all the reference grid lines to obtain an encrypted two-dimensional airfoil shape grid;
step 5, encrypting the blade tip grid nodes of the linear interpolation section of the blade to generate a C-O type blade body-fitted grid;
and 6, encrypting the blade tip turnover grid on the basis of the existing blade grid to obtain the encrypted blade grid.
Further, the calculation formula of the initial two-dimensional airfoil grid generation in step 1 is as follows:
Figure BDA0002538472870000021
in the above formula, J is Jacobian matrix, and P (xi, eta) and Q (xi, eta) are control source terms.
Further, the step 3 specifically includes: a certain grid point on grid line 2 is located at a point of grid line 1Between j and point j +1, the stored location information includes: the ratio r of the positions of the associated mesh segment j and the projection point, where r is dr/dj, drRepresenting the distance of the projection point to point j, djAnd (3) representing the distance from the point j to the point j +1, and calculating to obtain the new grid node coordinate as (X, Y) according to the position information, wherein X is (1-r) X (i, j) + r X (i, j +1), and Y is (1-r) Y (i, j) + r Y (i, j + 1).
Further, the step 4 specifically includes: and (3) enabling the corresponding relation between grid lines in all j directions of the encrypted two-dimensional airfoil grid and the grid lines in the j direction of the initial two-dimensional airfoil grid to be the same as the corresponding relation between the grid lines 2 and the grid lines 1, traversing the direction i, interpolating all normal grid nodes according to the position information stored in the past, and calculating to obtain the encrypted two-dimensional airfoil grid, wherein the direction i is the direction surrounding the airfoil, and the direction j is the normal direction of the airfoil.
Further, the specific process of generating the C-O type blade body-fitting grid in the step 5 is as follows:
step S501, dividing a two-dimensional airfoil grid of a spanwise section according to parameters of a real rotor blade;
step S502, rotating, zooming and translating the wing section grids of the spanwise sections according to the twisting, chord length changing, up/down reversing and tapering information of the blades, and then sequentially calculating two-dimensional wing section grids on each spanwise node between every two spanwise sections by adopting a Lagrange interpolation method;
step S503, turning over the characteristic wing section grids of the oar root and the oar tip by taking the central arc lines of the wing section at the oar root and the oar tip as rotating shafts, uniformly turning over the grids according to the turning-over times, and combining the last two faces obtained by turning over, namely, only adopting the grid coordinates of one face of the two turned-over faces.
Further, in the step 5, at a position close to the tip of the mesh, a mesh node in the spanwise direction of the tip of the propeller needs to meet the requirement of capturing the vortex of the tip of the propeller, the encryption range is from the tip of the propeller to a position 0.2c to 0.5c away from the tip of the propeller, and c is the chord length of the airfoil.
Further, in step 6, if the influence of the mass jet control is considered, interpolation processing needs to be performed on the grid cells corresponding to the mass jet ports, grid nodes are uniformly inserted into the corresponding grid cells, and finally, the encrypted blade grid is obtained.
Compared with the prior art, the invention has the following remarkable advantages:
the invention provides a blade grid encryption method suitable for high-precision simulation of a rotor blade tip vortex, which improves the capturing capability of the blade grid on the rotor blade tip vortex by encrypting the grid nodes in the normal direction and the span direction of the blade grid on the basis of keeping the good orthogonality of the original grid, thereby accurately carrying out high-precision simulation on the rotor blade tip vortex.
The present invention will be described in further detail with reference to the following drawings.
Drawings
FIG. 1 is a schematic diagram of an initial two-dimensional airfoil grid.
FIG. 2 is a schematic diagram of reference grid line selection.
FIG. 3 is a projection relationship diagram of new gridlines and reference gridlines.
Fig. 4 is a two-dimensional encrypted airfoil grid obtained by interpolation.
FIG. 5 is a schematic diagram of a C-O type blade skin mesh generation process.
FIG. 6 is a schematic diagram of a C-O type blade skin grid obtained by interpolation calculation.
FIG. 7 is a final grid diagram of the fitted grid of the encrypted C-O type blade.
Detailed Description
The technical content of the invention is explained in detail below by way of example and with reference to the attached drawings, as follows:
a blade grid encryption method suitable for high-precision simulation of rotor tip vortex comprises the following steps:
step 1, generating an initial two-dimensional airfoil grid with good orthogonality in advance, and selecting a reference grid line in the normal direction in the grid as an interpolation reference; the reference grid line selected on the initial grid is grid line 1, as shown in fig. 1 and 2;
step 2, generating a new grid line meeting the high-precision capturing requirement of the tip vortex; the grid line 2 is shown in fig. 2, in the figure, the grid line 1 is a reference airfoil grid selected from an initial two-dimensional airfoil grid, and the grid line 2 is a new grid line generated to meet the requirement of high-precision capturing of the tip vortex;
step 3, traversing each grid point on a new grid line, projecting the grid point onto a reference grid line, recording the position information of the points on the reference grid line, and calculating the coordinates of the grid point on the reference grid line; a certain grid point on grid line 2 is located between point j and point j +1 of grid line 1, and the stored position information is: the new mesh node coordinate calculated according to the position information is (X, Y), as shown in fig. 3, where r is dr/dj, drRepresenting the distance of the projection point to point j, djThe distance from the point j to the point j +1 is shown, in the figure, the position information projected to the grid line 1 by the grid node of the grid line 2 comprises the position ratio r of the grid section (subscript j) of the point on the grid line 1 and the projection point; x and Y are coordinates of points on the grid line 2 projected to the grid line 1;
step 4, surrounding the airfoil shape direction, encrypting grid lines on all the reference grid lines to obtain an encrypted two-dimensional airfoil shape grid; making the corresponding relation between grid lines in all j directions of the encrypted two-dimensional airfoil grid and grid lines in the j direction of the initial grid identical to the corresponding relation between the grid lines 2 and the grid lines 1, traversing the i direction, interpolating all normal grid nodes according to the position information stored in the past, and obtaining the encrypted two-dimensional airfoil grid by calculation as shown in FIG. 4, wherein the i direction is the surrounding airfoil direction, and the j direction is the airfoil normal direction;
step 5, encrypting the blade tip grid nodes of the linear interpolation section of the blade to generate a C-O type blade body-fitted grid; at the position close to the grid tip, the grid node in the spanwise direction of the tip of the propeller should meet the catching requirement of the tip vortex of the propeller, the encryption range of the grid node is from the tip of the propeller to the position 0.2 c-0.5 c (c is the chord length of the airfoil), the diameter of the vortex core of the tip vortex of the propeller is about 0.1c generally, and the encryption area can ensure that the movement range of the tip vortex of the propeller at the tip of the propeller is completely covered; the blade grid generation process is as shown in fig. 5 and 6;
step 6, encrypting the blade tip turnover grid on the basis of the existing blade grid to obtain an encrypted blade grid; in addition, if the influence of the mass jet control is considered, interpolation processing needs to be performed on grid cells corresponding to the mass jet ports, a certain number of grid nodes are uniformly inserted into the corresponding grid cells, and finally, an encrypted blade grid is obtained as shown in fig. 7.
Further, the calculation formula of the initial two-dimensional airfoil grid generation in step 1 is as follows:
Figure BDA0002538472870000041
in the formula, J is a Jacobian matrix, and P (xi, eta) and Q (xi, eta) are control source terms.
Further, with reference to fig. 5 and 6, the specific process of generating the C-O type blade skin mesh in step 5 is as follows:
step S501, dividing a two-dimensional airfoil grid of a spanwise section according to parameters (including radius, chord length and undercut) of a real rotor blade;
step S502, rotating, scaling and translating the airfoil grids of the spanwise sections according to the twisting, chord length variation, up/down inversion and tapering information of the blades, and then sequentially calculating two-dimensional airfoil grids on each spanwise node between every two spanwise sections by adopting a Lagrange interpolation method, as shown in FIG. 5;
step S503, turning over the characteristic airfoil grid of the blade root and the blade tip with the mean camber line of the airfoil at the blade root and the blade tip as a rotation axis, and turning over the grid uniformly according to the turning-over times, so as to avoid the influence caused by numerical errors, merging the last two faces obtained by turning over, that is, only using the grid coordinates of one face of the two turned-over faces, as shown in fig. 6.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (7)

1. A grid encryption method suitable for high-precision simulation of a front flying rotor blade tip vortex is characterized by comprising the following steps:
step 1: generating an initial two-dimensional airfoil grid with good orthogonality in advance, and selecting a reference grid line in the normal direction in the grid as an interpolation reference, wherein the reference grid line is a grid line 1;
step 2: generating a new grid line which meets the high-precision capturing requirement of the tip vortex, namely a grid line 2;
and step 3: traversing each grid point on a new grid line, projecting the grid point onto a reference grid line, recording the position information of the points on the reference grid line, and calculating the coordinates of the grid points on the reference grid line;
step 4, surrounding the airfoil shape direction, encrypting grid lines on all the reference grid lines to obtain an encrypted two-dimensional airfoil shape grid;
step 5, encrypting the blade tip grid nodes of the linear interpolation section of the blade to generate a C-O type blade body-fitted grid;
and 6, encrypting the blade tip turnover grid on the basis of the existing blade grid to obtain the encrypted blade grid.
2. The method according to claim 1, wherein the calculation formula for the initial two-dimensional airfoil grid generation in step 1 is:
Figure FDA0002538472860000011
in the above formula, J is Jacobian matrix, and P (xi, eta) and Q (xi, eta) are control source terms.
3. The method according to claim 1, wherein step 3 specifically comprises: a certain grid point on grid line 2 is located between point j and point j +1 of grid line 1, and the stored position information includes: the ratio r of the positions of the associated mesh segment j and the projection point, where r is dr/dj, drRepresenting the distance of the projection point to point j, djRepresenting point j to point jAnd the distance of +1 is calculated according to the position information to obtain the new grid node coordinate of (X, Y), wherein X is (1-r) X (i, j) + r X (i, j +1), and Y is (1-r) Y (i, j) + r Y (i, j + 1).
4. The method according to claim 3, wherein the step 4 specifically comprises: and (3) enabling the corresponding relation between grid lines in all j directions of the encrypted two-dimensional airfoil grid and the grid lines in the j direction of the initial two-dimensional airfoil grid to be the same as the corresponding relation between the grid lines 2 and the grid lines 1, traversing the direction i, interpolating all normal grid nodes according to the position information stored in the past, and calculating to obtain the encrypted two-dimensional airfoil grid, wherein the direction i is the direction surrounding the airfoil, and the direction j is the normal direction of the airfoil.
5. The method according to claim 4, wherein the C-O type blade skin grid generation in the step 5 is realized by the following specific process:
step S501, dividing a two-dimensional airfoil grid of a spanwise section according to parameters of a real rotor blade;
step S502, rotating, zooming and translating the wing section grids of the spanwise sections according to the twisting, chord length changing, up/down reversing and tapering information of the blades, and then sequentially calculating two-dimensional wing section grids on each spanwise node between every two spanwise sections by adopting a Lagrange interpolation method;
step S503, turning over the characteristic wing section grids of the oar root and the oar tip by taking the central arc lines of the wing section at the oar root and the oar tip as rotating shafts, uniformly turning over the grids according to the turning-over times, and combining the last two faces obtained by turning over, namely, only adopting the grid coordinates of one face of the two turned-over faces.
6. The method as claimed in claim 5, wherein in the step 5, near the mesh tip, the mesh nodes in the tip span direction need to meet the requirement of tip vortex capture, and the encryption range is from the tip to a position 0.2c to 0.5c away from the tip, where c is the airfoil chord length.
7. The method according to claim 6, wherein in step 6, if the influence of the mass jet control is considered, interpolation processing needs to be performed on grid cells corresponding to the mass jet ports, and grid nodes are uniformly inserted into corresponding grid cells, so as to finally obtain the encrypted blade grid.
CN202010539684.8A 2020-06-15 2020-06-15 Grid encryption method suitable for high-precision simulation of forward-flying rotor blade tip vortex Pending CN111783222A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112926148A (en) * 2021-01-28 2021-06-08 西北工业大学 Propeller airfoil aerodynamic shape design method considering influence of three-dimensional effect
CN117556548A (en) * 2024-01-03 2024-02-13 中国空气动力研究与发展中心计算空气动力研究所 Automatic calculation method applicable to paddle load foundation points of arbitrary grid surface

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CN109747818A (en) * 2018-12-30 2019-05-14 南京航空航天大学 Lifting airscrew aerodynamic interference control method based on blade tip quality spray
CN110457860A (en) * 2019-08-22 2019-11-15 中国商用飞机有限责任公司北京民用飞机技术研究中心 The automatically generating of grid, device, equipment and storage medium

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CN109747818A (en) * 2018-12-30 2019-05-14 南京航空航天大学 Lifting airscrew aerodynamic interference control method based on blade tip quality spray
CN110457860A (en) * 2019-08-22 2019-11-15 中国商用飞机有限责任公司北京民用飞机技术研究中心 The automatically generating of grid, device, equipment and storage medium

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Title
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112926148A (en) * 2021-01-28 2021-06-08 西北工业大学 Propeller airfoil aerodynamic shape design method considering influence of three-dimensional effect
CN112926148B (en) * 2021-01-28 2023-02-03 西北工业大学 Propeller airfoil aerodynamic shape design method considering influence of three-dimensional effect
CN117556548A (en) * 2024-01-03 2024-02-13 中国空气动力研究与发展中心计算空气动力研究所 Automatic calculation method applicable to paddle load foundation points of arbitrary grid surface
CN117556548B (en) * 2024-01-03 2024-05-14 中国空气动力研究与发展中心计算空气动力研究所 Automatic calculation method applicable to paddle load foundation points of arbitrary grid surface

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