CN107742011B - Design method of impeller blade drag reduction micro-texture - Google Patents
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Abstract
The invention discloses a design method of a blade surface drag reduction micro-texture, and belongs to the field of blade drag reduction. Establishing a flow field area according to an impeller blade model; carrying out numerical simulation on the flow field area to obtain a flow chart of the middle section of the blade in the height direction, and accordingly determining a backflow area of an airfoil pressure surface, a boundary layer separation area and an airfoil suction surface as a microtexture placing area; arranging a micro-texture section in a micro-texture placing area in close contact with the airfoil shape of the blade, and enabling the micro-texture section to be swept into ribs or grooves on the surface of the blade along the height direction of the blade; and (3) optimizing the placing position and the cross section shape of the micro texture by adopting finite element simulation on the blade model with the rib or groove micro texture to obtain the placing position and the cross section shape of the micro texture with the best resistance reduction, so as to construct the resistance reduction micro texture on the surface of the blade. The resistance of the optimized blade surface resistance-reducing micro-texture reaches 5 to 10 percent, the energy consumption is reduced, the fuel oil resource is saved, and the design method of the resistance-reducing micro-texture can be popularized and applied to other fields.
Description
Technical Field
The invention relates to a design method of an impeller blade drag reduction micro-texture, and relates to a blade which is mainly a wind blade, wherein the incoming flow speed is between 50m/s and 100m/s, and the design method belongs to the field of blade drag reduction.
Background
Turbomachines have wide application in the fields of aviation, aerospace, energy, traffic, chemical engineering, petroleum and the like. The blade is a key part of turbomachinery such as an aircraft engine, a gas turbine, a fan and the like, and the pneumatic drag reduction performance of the blade directly influences the working performance of the product. In order to improve the aerodynamic drag reduction performance of the blade, experts and scholars at home and abroad conduct a great deal of research work on the aspect of optimization design of the blade, and a great deal of exploration is conducted on the aspects of blade structure optimization, blade surface texture design and the like, so that the aerodynamic drag reduction performance of the turbine machinery is improved from a design source. In various drag reduction technologies, the surface of the bionic microstructure prepared by the micro-nano manufacturing technology has a remarkable drag reduction effect, the design with the bionic micro-nano texture can be applied to the fields of drag reduction of aero-engine blades and the like, and the special functions and performances of drag reduction and the like are obtained through the special surface texture, so that the functions and performances of products are improved. At present, the microtexture drag reduction technology is mostly applied to surfaces of wings and the like moving at high speed in fluid, but is rarely applied to engine blades, because the current blade drag reduction microtexture design is mainly that triangular grooves or ribs which are regularly distributed are arranged on the whole surface of a blade according to research experience, or a layer of adhesive film with different micro structures is additionally attached to the surface of the blade, and then a structure with a drag reduction effect is screened out through experiments. However, when the flow field state is changed, the original drag reduction effect is likely to disappear. Therefore, these design methods lack universality for different flow field states, which not only wastes a lot of resources and time, but also lacks pertinence and flexibility.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a simple and feasible method for designing a microtexture with resistance reduction performance on a blade according to the actual working environment of different blades, and improves the efficiency and flexibility of the resistance reduction microtexture design.
In order to achieve the design purpose, the design steps involved in the invention are as follows:
step 1): and establishing a flow field area according to the impeller blade model. The flow field domain is characterized in that: the width W of the flow field area is twice of the circumferential distance of adjacent blades of the impeller; the height H of the flow field area is 1-1.1 times of the height of the blade; the flow field trajectory curve 1 is obtained by fitting two airfoil center lines of the blade bottom and the blade top, solving a bisector and extending the front and the back of the bisector by 2-3 times of the chord length of the blade bottom. The above characteristics can make the flow field state of the designed flow field more approximate to the real flow field state.
Step 2): and (2) carrying out grid division on the flow field obtained in the step 1) and numerically simulating the airflow resistance of the blade.
Step 3): and (3) establishing a middle section at the middle position in the height direction of the blade according to the numerical simulation result in the step 2), and obtaining a fluid velocity flow chart of the section. According to the method, microtextured sections are arranged in three areas of the pressure surface of the airfoil, the boundary layer separation area and the backflow area of the suction surface of the airfoil.
The cross section is taken at the middle position in the height direction of the blade, because the turbulent flow is most obviously developed, and the microtexture drag reduction effect determined according to the cross section is the best. The micro-texture is arranged in the boundary layer separation area because the micro-texture can change the attack angle of the incoming flow, can delay the separation of the tail boundary layer and can help to inhibitThe generation of turbulent flow accords with the aerodynamic theory. The cross section of the microtexture is triangular or quadrangular, and one edge of the microtexture is tightly attached to the cross section airfoil. The height H of the microtexture is the maximum dimension H of the turbulent vortex system in the section in the normal direction of the blade max4% -7% of the total height of the whole structure, but the minimum height is not less than 0.05mm, and the maximum height is not more than 1 mm; the microtexture of the airfoil pressure surface is arranged in the area from the leading edge of the airfoil to the front 50% of the trailing edge of the airfoil, because the included angle between the incoming flow direction and the blade is smaller at the front end of the airfoil pressure surface, the pressure difference resistance brought by the increased microtexture is smaller than the reduced viscous resistance, and therefore the total resistance is reduced; at the back end, due to the twist of the blade, the included angle between the incoming flow direction and the blade surface is too large, and the pressure difference resistance caused by increasing the microtexture is larger than the reduced viscous resistance, so the total resistance can be increased. The microtexturing of the airfoil suction surface is arranged in the range of the front 50% of the airfoil suction surface from the start to the end of the backflow, so that the adverse pressure gradient of the airfoil suction surface is reduced, and the inhibition of the diffusion of the turbulent flow is facilitated. Only one microtexture is arranged in the boundary layer separation area. In the micro texture of the backflow area of the airfoil pressure surface and the airfoil suction surface, the center distance l of the bottom edge of the cross section of the micro texture is 1.5-2.5 times of the height h; the included angle theta between the incident flow edge of the micro-texture and the incoming flow direction is between 50 degrees and 90 degrees; the micro-texture of the pressure surface of the airfoil is a groove structure, namely, the cross section of the micro-texture is embedded in the airfoil, because the laminar flow is mainly used on the pressure surface of the airfoil, and the airflow can form micro-vortex in the groove, thereby greatly reducing the viscous resistance. The boundary layer separation area and the backflow area of the airfoil suction surface are of rib structures, and the section of the microtexture protrudes out of the airfoil.
Step 4): and (3) taking the micro-texture section arranged in the step 3) as a generatrix, and sweeping the generatrix into ribs or grooves on the surface of the blade along the height direction of the blade. The specific process is as follows: and establishing a projection plane on the suction surface of the airfoil, wherein the projection plane is parallel to the height direction of the blade and the chord length direction of the airfoil of the blade in the middle section. And (3) locating the middle point of the bottom edge created in the step 3), namely the bottom edge, which is the side of the micro-texture section side in the airfoil. And vertically projecting to a projection plane. A parallel line beam passing through the above projected points is made in the projection plane. The parallel line bundle starts at the leaf base to 5% of the leaf height and ends at the 95% position. Then the parallel linear beams are projected to the blade to obtain a projection curve. And taking the projection curves as guide lines, taking the sections of the micro-textures as generating lines, and sweeping the generating lines into grooves and ribs to complete the creation of the micro-textures.
Step 5): and (4) carrying out numerical simulation again on the blade model with the rib and groove micro-texture built in the step 4), calculating the resistance borne by the model, and comparing the resistance with the resistance obtained before. By continuously adjusting the position and the cross section shape of the microtexture, the microtexture arrangement with the optimal resistance reduction performance is finally obtained by taking the given resistance reduction ratio as an optimization target.
The micro-texture designed by the method can reduce the airflow resistance of the blade by 5 to 10 percent through numerical simulation verification, thereby greatly reducing the energy consumption and saving the resources.
Drawings
FIG. 1 is a blade and flow field model diagram;
FIG. 2 is a mid-section flow diagram;
FIG. 3 is a microtexture layout;
FIG. 4 is an airfoil pressure face groove drag reduction mechanism;
FIG. 5 is a triangular rib microtexture model of the airfoil suction surface;
in the figure:
w-flow field width;
h-flow field height;
l-center distance of the bottom edge of the section of the microtexture;
h-microtexture height;
Hmax-maximum dimension of turbulent vortices at the intermediate section along the normal of the airfoil;
theta is the included angle between the airflow direction and the microtexture incident flow surface;
1-flow field trajectory curve;
2-airfoil mid-line;
3-a bisector obtained by fitting the airfoil mean line (2);
4-middle section;
5-airfoil pressure surface;
6-boundary layer separation zone;
7-airfoil suction surface;
8-airfoil profile;
9-area of fig. 3;
10-airfoil leading edge;
11-airfoil trailing edge;
12-refluxing;
13-microtextured cross section;
14-riblet microtexturing;
15-projection plane;
16-parallel linear beams;
Detailed Description
TABLE 1 Point coordinate data for leaf certification
TABLE 2 numerical simulation model parameters
| Name (R) | Parameter(s) |
| Entry velocity (m/s) | 75 |
| Fluid, especially for a motor vehicle | Ideal gas |
| Temperature (k) | 300 |
| Turbulence model | k-ε(2eqn)；Realizable |
| Wall function | Enhanced Wall Treatment |
TABLE 3 Experimental results of microtexture height h and drag reduction effect
| Microtexture heights H and HmaxRatio/%) | Percent drag reduction% |
| 3.6 | 3.1 |
| 4 | 5 |
| 4.4 | 6.1 |
| 4.8 | 6 |
| 5.2 | 5.5 |
| 5.6 | 4 |
| 6 | 3.1 |
| 6.4 | 1.1 |
| 6.8 | 0.5 |
| 7.2 | -1.3 |
TABLE 4 Experimental results of center distance l of section bottom edge of micro texture and drag reduction effect
| Ratio of center distance l to height of bottom edge of micro-texture cross section | Percent |
| 1 | 0.1 |
| 1.5 | 1.3 |
| 2 | 5 |
| 2.5 | 4.5 |
| 3 | 1.1 |
TABLE 5 Experimental results of the angle theta between the incident flow edge and the incoming flow direction of the microtexture and the drag reduction effect
| Included angle theta/degree between micro-texture incident flow edge and incoming flow direction | Percent drag reduction% |
| 45 | 0.2 |
| 65 | 1.5 |
| 85 | 3.5 |
The data for a given free-form blade is shown in Table 1. The design method of the blade drag reduction micro-texture is explained by combining the attached drawings:
1) establishing a flow field area according to an impeller blade model;
as shown in fig. 1, the width W of the flow field is twice the circumferential distance between adjacent blades of the impeller; the height H of the flow field area is 1.05 times of the height of the blade; the flow field trajectory curve 1 is obtained by fitting two airfoil center lines 2 of the blade bottom and the blade top to obtain a bisector 3, and then respectively extending the bisector 3 in front and at back by 2 times of the chord length of the blade bottom. The above characteristics can make the flow field state of the designed flow field more approximate to the real flow field state.
2) And (2) carrying out grid division on the flow field obtained in the step 1) and numerically simulating the airflow resistance of the blade. The boundary conditions and turbulence model used in this case are shown in table 2, and the resistance calculation result is 41.692N.
3) According to the numerical simulation result in the step 2), establishing a middle section 4 at the middle position in the height direction of the blade, and obtaining a fluid velocity flow chart of the section, such as the flow chart shown in fig. 2. Accordingly, triangular microtextured sections are arranged in three areas of the pressure surface 5 of the airfoil, the boundary layer separation area 6 and the backflow area of the suction surface of the airfoil.
The reason for taking the intermediate section 4 at the intermediate position in the blade height direction is that the turbulence development is most obvious here, and the microtextured drag reduction determined from this is the best. The reason for the micro-texture in the boundary layer separation region 6 is that the micro-texture changes the attack angle of the incoming flow, delays the separation of the trailing boundary layer, helps to suppress the generation of turbulence, and conforms to the aerodynamic theory. The cross-sectional shape of the microtexture is triangular, and one side of the microtexture is tightly attached to the cross-sectional airfoil 8. As shown in FIG. 3, the height H of the microtexture is the largest dimension H of the turbulent vortex in the slice in the normal direction of the blademaxAnd 5% of (3) is 0.2 mm. The microtexture on one side of the airfoil pressure surface is arranged in the front 50% area of the airfoil leading edge 10 to the airfoil trailing edge 11, because the included angle between the incoming flow direction and the blade is smaller at the front end of the airfoil pressure surface, the pressure difference resistance brought by the increase of the microtexture is smaller than the reduced viscous resistance, and therefore the total resistance is reduced; at the rear end, the incoming flow is square due to the twisting of the bladesThe pressure differential resistance due to the increased microtexturing is greater than the reduced viscous resistance, and the total resistance is increased. The microtexturing of the recirculation region of the airfoil suction surface is arranged in this region from the beginning to the first 50% in the direction of the recirculation 12, which reduces the counter pressure gradient at the airfoil suction surface and helps to suppress the diffusion of turbulence. Only one microtexture is arranged at the boundary layer separation. The micro-texture of the backflow area of the airfoil pressure surface and the airfoil suction surface is arranged with the center distance l of the bottom edge of the section of the micro-texture being 2 times of the height h, and the included angle theta between the incident flow edge of the micro-texture and the incoming flow direction is 60 degrees. The micro-texture of the pressure surface of the airfoil is a groove structure, namely, the section of the triangular micro-texture is embedded in the airfoil 8. This is because in the pressure side of the airfoil, mainly laminar flow, the air flow will form micro-vortices in the grooves, greatly reducing viscous drag, as shown in fig. 4. The micro-texture of the boundary layer separation area and the backflow area of the airfoil suction surface is a rib structure, namely the section of the triangular micro-texture is positioned outside the airfoil.
4) Taking the triangular micro-texture section 13 arranged in the step 3) as a generatrix, and sweeping the generatrix on the surface of the blade into a triangular rib micro-texture 14 or a groove along the height direction of the blade.
On the side of the suction surface of the airfoil a projection plane 15 is established, which is parallel to the blade height direction and parallel to the chord length direction of the blade airfoil in the intermediate section 4. And (3) setting the middle point of the bottom edge of the triangle created in the step 3), namely the bottom edge as one edge of the triangle positioned in the airfoil. Projected perpendicularly to the projection plane 15. In this plane, a parallel line beam 16 is made through the above projected points. The parallel line bundle starts at the leaf base to 5% of the leaf height and ends at the 95% position. Then the parallel linear beams are projected to the blade to obtain a projection curve. And (3) taking the projection curves as guide lines, taking the section 13 of the triangular microtexture as a generatrix, and sweeping the triangular groove and the rib microtexture 14 to complete the creation of the microtexture, as shown in fig. 5.
5) Numerical simulation is carried out again on the blade model with the triangular rib and groove micro-texture built in the step 4), the resistance of the blade is calculated to be 39.004N, and the resistance is reduced by 6.447% compared with the resistance 41.692N obtained before. The result is optimized by adjusting the position and the cross-sectional shape of the microtexture according to the principle, and the optimal drag reduction rate can be improved to 8 percent.
It is worth to be noted that the height H of the flow field is set to be 1 to 1.1 times of the blade height, and the extension length of the flow field trajectory curve 1 on both sides of the bisector 3 is 2 to 3 times of the chord length of the blade bottom, because when the range is exceeded, the obtained result is greatly different from the real result, and even in this case, the drag reduction effect is still achieved. To investigate the effect of microtexture height h on drag reduction, 8 sets of validation examples were performed herein for case blades, and the results are shown in table 3. In order to investigate the influence of the center distance l of the bottom edge of the microtextured section on the drag reduction effect, 7 groups of verification examples are carried out on case blades, and the results are shown in table 4. In order to investigate the influence of the included angle theta between the flow-facing edge of the microtexture and the incoming flow direction on the drag reduction effect, 5 groups of verification examples are carried out on case blades, and the results are shown in table 5. When the above parameters are taken as the exploration objects, other parameters are unchanged, and the values are the same as the cases. Similar examples are carried out on other types of blades, and the conclusion of the drag reduction effect is similar.
The above description is directed to specific embodiments of the present invention, but the present invention is not limited to the above description. Any equivalent modifications and alterations to this technical solution would be considered within the scope of this invention by those skilled in the art. Accordingly, equivalent changes and modifications made without departing from the spirit and scope of the present invention should be covered by the present invention.
Claims (1)
1. A design method of an impeller blade drag reduction micro-texture is characterized by comprising the following steps:
step 1): according to the impeller blade model, a flow field domain is established, and the flow field domain is characterized in that: the width W of the flow field area is twice of the circumferential distance of adjacent blades of the impeller; the height H of the flow field area is 1-1.1 times of the height of the blade; the flow field trajectory curve (1) is obtained by fitting two airfoil profile center lines (2) of the blade bottom and the blade top to obtain a bisector (3), and then respectively extending the bisector (3) in front and at back by 2-3 times of the chord length of the blade bottom;
step 2): carrying out numerical simulation on the flow field obtained in the step 1), and calculating the airflow resistance of the blade;
step 3): according to the numerical simulation result in the step 2), establishing a middle section (4) at the middle position in the height direction of the blade to obtain a velocity flow diagram of the section, and accordingly determining that microtextured sections (13) are arranged in three areas of an airfoil pressure surface (5), a boundary layer separation area (6) and a backflow area of an airfoil suction surface; the cross-sectional shape and specific position of the microtexture are: the cross section of the microtexture is triangular or quadrangular, and one edge of the microtexture is tightly attached to the cross section airfoil profile (8); the height H of the microtexture is the maximum dimension H of the turbulent vortex system in the section in the normal direction of the blademax4% -7% of the total height of the whole structure, but the minimum height is not less than 0.05mm, and the maximum height is not more than 1 mm; the microtexture of the airfoil pressure surface is arranged in the area from the airfoil leading edge (10) to the front 50% of the airfoil trailing edge (11); the microtexture of the airfoil suction surface is arranged in the range of the first 50% of the airfoil suction surface from the start to the end of the backflow; only one microtexture is arranged in the boundary layer separation area (6); in the micro texture of the backflow area of the airfoil pressure surface and the airfoil suction surface, the center distance l of the bottom edge of the cross section of the micro texture is 1.5-2.5 times of the height h; the included angle theta between the incident flow edge of the micro-texture and the incoming flow direction is between 50 degrees and 90 degrees; the micro-texture of the pressure surface of the airfoil profile is a groove structure, namely the cross section of the micro-texture is embedded in the airfoil profile (8), and the boundary layer separation area and the backflow area of the suction surface of the airfoil profile are rib structures, namely the cross section of the micro-texture protrudes out of the airfoil profile (8);
step 4): taking the micro-texture section (13) arranged in the step 3) as a generatrix, and sweeping the surface of the blade into a rib micro-texture (14) or a groove along the height direction of the blade, wherein the specific process is as follows: establishing a projection plane (15) on the airfoil suction surface, wherein the plane is parallel to the height direction of the blade and the chord length direction of the airfoil of the blade in the middle section (4); the middle point of the bottom edge created in the step 3) is positioned on the side of the micro-texture section side length in the airfoil profile; making a vertical projection to the projection plane (15); making a parallel linear beam (16) which passes through the projection points in the projection plane (15), wherein the parallel linear beam starts from the leaf bottom to the position 5% of the leaf height direction and ends at the position 95%, then projecting the parallel linear beam to the leaf to obtain projection curves, taking the projection curves as guide lines and the microtexture section (13) as a generating line, and sweeping the groove microtexture and the rib microtexture (14) to complete the creation of the microtexture;
step 5): carrying out numerical simulation again on the blade model with the rib and groove micro-texture built in the step 4), calculating the resistance borne by the model, and comparing the resistance with the resistance obtained before; by continuously adjusting the position and the cross section shape of the microtexture, the microtexture arrangement with the optimal resistance reduction performance is finally obtained by taking the given resistance reduction ratio as an optimization target.
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