CN113217462A - Subsonic vortex blowing type compressor blade - Google Patents
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- CN113217462A CN113217462A CN202110634527.XA CN202110634527A CN113217462A CN 113217462 A CN113217462 A CN 113217462A CN 202110634527 A CN202110634527 A CN 202110634527A CN 113217462 A CN113217462 A CN 113217462A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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Abstract
A row of air blowing holes are distributed on the suction surface of the blade of the air blowing type compressor along the spanwise direction, and all the air blowing holes are communicated with an air blowing cavity. A row of vortex generators are arranged on the rear edge of the suction surface of the blade along the unfolding direction, and the vortex generators are in one-to-one correspondence with the air blowing holes. The shape of each vortex generator is triangular pyramid, and the direction of the front edge is consistent with that of the front edge of the blade. The subsonic vortex air blowing type blade effectively controls the flow separation of the suction surface of the blade while increasing the load by virtue of the air blowing cavity penetrating the blade in the blade span direction, the air blowing holes formed in the suction surface of the blade and the vortex generator arranged at the rear edge of the suction surface of the blade, so that the boundary layer separation is effectively inhibited after high-energy fluid is injected into the air blowing cavity, the complicated working condition in the compressor is adapted to a certain extent, and the pressure ratio and the load of the compressor are further improved.
Description
Technical Field
The invention relates to the field of compressors, in particular to a vortex air blowing type compressor blade.
Background
The development of modern aeronautical technologies requires aeroengines to have higher thrust-to-weight ratios. Therefore, further improvement of the stage load and the stage pressure ratio of the compressor is required to meet the requirement of higher thrust-weight ratio. However, the working environment inside the high-load compressor is very harsh, and the flow separation phenomenon inevitably occurs inside the compressor under a strong adverse pressure gradient, which causes the flow loss and the aerodynamic performance reduction inside the compressor. In order to meet the requirement of high aerodynamic load of the compressor, researchers have conducted a great deal of research on flow control of the compressor. The current flow control methods are mainly divided into two types: passive flow control techniques and active flow control techniques.
The passive flow control technology controls a flow field by changing the geometric shapes of the blades and the end wall of the compressor, such as methods of a vortex generator, three-dimensional blade design, end wall modeling and the like. The vortex generator has a certain control function on delaying the occurrence of boundary layer separation. Liu Yanming et al studied the influence of the end wall vortex generator on the flow field of the blade cascade of the gas compressor in the numerical simulation of controlling the separation of the blade cascade corner regions by the slope-type vortex generator (the 38 th volume, 06 th phase of 2020 in the academic journal of aerodynamics), explored the influence mechanism of various geometric parameters and the incoming flow attack angle of the vortex generator, and the results show that the flow direction vortex generated by the vortex generator interacts with the secondary flow of the end wall, so that the development of the channel vortex to the suction surface is inhibited, and the main flow high-energy fluid is involved in the corner regions, so that the corner region separation is weakened, and the optimal vortex generator scheme reduces the total pressure loss by 7.82%. The influence of the vortex generator on the aerodynamic performance of the wing is researched by reverie et al in the influence of the vortex generator on the maximum lift force and the stall attack angle of the wing (journal of university of aerospace, 1998, 03 th), and the result shows that the vortex generator can delay the separation of the boundary layer on the wing, improve the maximum lift force and the stall attack angle of the wing and improve the aerodynamic characteristics of the low-speed and large attack angle of the airplane. In the above researches, the vortex generator controls the flow separation of the blade/wing, so as to improve the aerodynamic performance, however, under the non-design working condition, especially under the working condition of large attack angle or high load, the control effect of the vortex generator is obviously reduced, and even the negative effect is generated on the flow field.
Compared with a passive flow control technology, the active flow control technology controls flow separation by locally applying excitation, namely injecting energy from the outside, can adapt to different working states and always ensure a better flow control effect. For example, the scheme of blowing by adopting the boundary layer in the compressor can effectively control the flow separation.
Culley et al studied the effect of suction side multihole blowing on the aerodynamic performance of a Compressor cascade in an Active Flow Separation Control of a State valve Using an aerated introduction in a Multistage Compressor Experiment (ASME Journal of turbo engineering 2004: 01), and showed that the suction side blowing scheme was effective in controlling Flow Separation, with losses reduced by 25% compared to an un-blown cascade when the blowing Flow was 1% inlet volume Flow. Cao et al, in the comprehensive of aerobic Characteristics of betweeen a novel high utility Loaded Injected Blade with varied Induced Pressure-Recovery Concept and one with controlled Design (phase Journal of Aero-acoustics 2017, 03), designed a high load blowing Blade with a diffusion factor of 0.61, compared to the Conventional Design Blade, the blowing Blade effectively controlled the large-scale flow separation of the suction surface of the Blade, but the blowing mass flow was higher, being 4.75% of the mass flow at the inlet of the Blade. Further, as shown in the Active Flow Control using step flowing for a Low-Pressure Turbine Cascade (document No. GT2004-53646) published by McAuliffe et al in ASME, the influence of the constant air Blowing Control on the Flow of a certain Low-Pressure Turbine Cascade is studied, and the study shows that the Control effect is greatly influenced by the incoming Flow speed, the constant air Blowing can improve the Cascade Flow only under the condition of Low mach number, and the air Blowing Control can increase the internal loss of the Turbine Cascade under the conditions of high incoming Flow mach number and high turbulence. The research controls the flow separation of the blades of the air compressor through the blowing of the suction surface, but the method is only suitable for limited working conditions, and the blowing of the suction surface has a plurality of limitations and even brings negative effects under non-designed working conditions.
Zhang et al, in Experimental and Numerical Study on the Flat-Plate Film coating Enhancement Using the Vortex Generator Down for the Fan-Shaped Hole Configuration (ASME Journal of turbo improvement year 2020, 03), studied the combination of air-blown blades and Vortex generators for improving the Cooling effect of a turbine. However, it is only found in flat plate experiments, and is a conceptual research, and does not appear in the practical application of the turbine.
The above documents show that the blowing of the boundary layer can effectively inhibit the flow separation inside the compressor, and can improve the stage load and the stage pressure ratio of the compressor to a certain extent, but the application conditions of the blowing of the boundary layer have many limitations and cannot adapt to a series of complex non-design working conditions of the compressor in practical application, so that the application value is deficient.
Disclosure of Invention
In order to overcome the defects in the prior art, widen the application conditions of the air blowing type blades and improve the load of the air blowing type blades, the invention provides a subsonic vortex air blowing type compressor blade.
The upper surface of the subsonic vortex air blowing type compressor blade provided by the invention is a suction surface, and the lower surface is a pressure surface. An air blowing cavity in the spanwise direction is arranged between the suction surface and the pressure surface of the air blowing type compressor blade.
The invention comprises an air blowing cavity, an air blowing hole and a vortex generator; and a row of air blowing holes are distributed on the suction surface of the air blowing type compressor blade along the unfolding direction, and the air blowing holes are communicated with the air blowing cavity. A row of vortex generators are arranged on the rear edge of the suction surface of the blade along the unfolding direction, and the vortex generators are in one-to-one correspondence with the air blowing holes. The leading edge of each vortex generator is in the same direction with the leading edge of the blade.
The chord length of the blowing type compressor blade is 65 mm; the center of each air blowing hole orifice is positioned at the position of 58.7 percent of the chord length of the blade on the suction surface; the center distance between the orifices of the adjacent air blowing holes is 10 mm. The intersection point of the front edge of the vortex generator and the suction surface is located at 73.2% of the chord length of the subsonic velocity vortex air blowing type blade suction surface.
The chord length of the blowing type compressor blade is 65mm, the span length is 100mm, the inlet geometric angle is 25.5 degrees, and the outlet geometric angle is-20.5 degrees. A curvature mutation point 5 is formed at the intersection of the suction surface of the blade of the vortex air blowing type compressor and the hole of the air blowing cavity; the curvature break point is located 56.6% of the blade chord length above the suction surface.
The air blowing cavity penetrates through the subsonic velocity vortex air blowing type blade along the spanwise direction of the blade, so that the starting point of the air blowing cavity is located at 0% of the spanwise direction, and the terminal point of the air blowing cavity is located at 100% of the spanwise direction; the profile of the upper surface in the blowing cavity is the same as the profile of the suction surface of the blade, and the profile of the lower surface in the blowing cavity is the same as the profile of the pressure surface of the blade. The front edge of the air blowing cavity is located at the position, in the chord length direction, of 21.5% of the chord length of the subsonic speed vortex air blowing type blade, and the tail edge of the air blowing cavity is located at the position, in the chord length direction, of 69% of the chord length of the subsonic speed vortex air blowing type blade.
The arc radius of the front edge of the blowing cavity is 1mm, and the arc radius of the tail edge of the blowing cavity is 0.6 mm. The thickness between the blowing cavity and the suction surface and the pressure surface of the blade is 1 mm.
The aperture of each air blowing hole is 1mm, and the air blowing holes are uniformly distributed along the spanwise direction of the blades of the air blowing type compressor. The central line of the air blowing hole is a straight line, and the included angle between the central line of the air blowing hole and the chord length direction is 3.8 degrees. The center of the orifice of each blowhole on the suction surface is positioned at 58.7% of the chord length of the blade on the suction surface. The center distance between the orifices of the adjacent air blowing holes is 10 mm.
The vortex generator is block-shaped, the shape of the vortex generator is triangular pyramid, and the vortex generator comprises a bottom surface and three triangular side surfaces. Wherein the bottom surface is a mounting surface of the vortex generator. One edge in the triangular pyramid is the leading edge of the vortex generator; the vortex-generator leading edge is perpendicular to the bottom surface of the vortex generator.
The intersection point of the front edge of the vortex generator and the bottom surface is b, and the intersection point b is positioned at 73.2% of the chord length of the blade on the suction surface; the intersection points of the other two edges of the vortex generator and the bottom surface are respectively c1And c2(ii) a Intersection point c1And point of intersection c2Are all positioned at 75.9 percent of the chord length of the blade on the surface of the suction surface of the subsonic vortex blowing type blade.
The length between the vertex a of the vortex generator and the intersection point b is 1mm, and the intersection point c1And c2The length between the two is 1.6mm, and the intersection point b and the intersection point c1The length between the point of intersection b and the point of intersection c2The lengths between the two parts are equal and are all 2 mm.
The subsonic vortex air blowing type blade provided by the invention is innovated on a flow control structure, namely, an air blowing cavity, a certain number of air blowing holes and vortex generators are added in the blade, so that separation of boundary layers is effectively inhibited after high-energy fluid is injected into the air blowing cavity, the air blowing cavity is adapted to complex working conditions in an air compressor to a certain extent, and the pressure ratio and the load of the air compressor are further improved.
And curvature catastrophe points exist on the suction surface of the subsonic speed vortex air blowing type blade. Under the design condition, the static pressure of the air flow on the suction surface is rapidly increased after passing through the curvature mutation point, the blade load is obviously increased, but the flow separation is easy to occur on the suction surface of the original blade due to the overhigh counter pressure gradient, so the original blade needs to be subjected to flow control.
In the subsonic velocity vortex air blowing type blade, an air blowing cavity is formed by penetrating the blade in the blade unfolding direction, an air blowing hole is formed by forming an opening in the suction surface of the blade, and a vortex generator is arranged on the rear edge of the suction surface of the blade, so that the subsonic velocity vortex air blowing type blade effectively controls the flow separation of the suction surface of the blade while increasing the load.
The profile of the inner surface of the blowing cavity is the same as the profile of the suction surface of the blade, and the profile of the inner surface of the blowing cavity is the same as the profile of the pressure surface of the blade, so that the structural strength of the subsonic vortex blowing type blade is ensured on the premise of meeting the requirement of sufficient blowing flow.
Through a plurality of air blowing holes which are arranged on the suction surface of the air blowing type blade and are communicated with the air blowing cavity, high-energy fluid in the air blowing cavity is blown out through the air blowing holes, energy is provided for low-energy fluid in the flow separation area, the mass flow required by the air blowing holes is 0.58% of the mass flow of the inlet under the design working condition, and the flow separation is effectively inhibited.
By the vortex generator arranged at the rear edge of the suction surface of the blade, high-energy fluid blown out from the air blowing hole can form two vortices with opposite rotation directions after passing through the vortex generator, so that the control range of air blowing is expanded, and flow separation is further inhibited.
The invention is provided with the vortex generator at the rear edge of the suction surface of the blade, obtains an optimal combined flow control scheme by determining the shape and the position of the optimal vortex generator and the position and the structure of the blowing hole on the high-load blowing type blade corresponding to the vortex generator, and increases the stage load and the stage pressure ratio of the compressor to the highest level of the existing stage as far as possible.
Compared with the prior art, the invention has the following beneficial effects:
the invention is based on a subsonic speed vortex blowing type blade design method, and adopts a full three-dimensional pneumatic optimization design method to design blades. In the design, a flow control method of combining the air blowing holes with the vortex generator is adopted to control the flow separation of the blades and improve the load of the blades. After the initial design of the subsonic velocity vortex air blowing type blades is completed, the subsonic velocity vortex air blowing type blades are distributed on a blade grid plate according to the design working condition, and three-dimensional numerical simulation is carried out.
When the subsonic vortex blowing type blade provided by the invention is arranged on the grid plate, the grid distance is 35.71mm, and the installation angle is 26.5 degrees. Under the design condition, the inlet Mach number is 0.6, and the inlet airflow angle is 52 degrees. FIG. 9 is a Mach number cloud diagram at 50% of the blade span of an original blade under a design condition, and FIG. 10 is a Mach number cloud diagram at 50% of the blade span of the subsonic velocity vortex air blowing type blade under the design condition. As can be seen from the figure, in the cascade channel of the original blade, the airflow passes through the curvature mutation point 5 of the suction surface and then generates large-area flow separation, which causes serious cascade loss; compared with the original blade 1, the subsonic speed vortex air blowing type blade designed in the invention effectively controls the flow separation of the suction surface, and the flow separation area 6 is almost eliminated. When the mass flow blown out from the air blowing hole 3 is 0.58% of the inlet flow, the flow separation of the suction surface of the subsonic velocity vortex air blowing type blade is effectively controlled, the static pressure ratio of the inlet and the outlet of the blade cascade is 1.17, and the diffusion factor reaches 0.62.
The control principle is as follows:
in the invention, the center of the orifice of the blowing hole 3 is positioned at the chord length of 58.7 percent of the blade of the suction surface, the mass flow blown out by the blowing hole is 0.58 percent of the inlet flow, and the design principle is as follows: the airflow is continuously accelerated in the front half part of the suction surface of the subsonic vortex blowing type blade until the airflow reaches a curvature mutation point 5 at 56.6% of the chord length of the blade on the suction surface, the curvature mutation point can enable the static pressure of the airflow to rise suddenly, so that the load and the diffusion capacity of the blade are improved, but the increase of the inverse pressure gradient can cause the airflow to be seriously separated after passing through the curvature mutation point, the air blowing holes are just positioned at the curvature mutation point, and the blown high-energy fluid 7 can obviously inhibit flow separation.
In the invention, the intersection point of the front edge of the vortex generator and the bottom surface of the vortex generator is b, the intersection point b is positioned at 73.2% of the chord length of the subsonic velocity vortex air blowing type blade suction surface, and the design principle is as follows: because only one blowing hole with the diameter of 1mm is arranged every 10mm along the spanwise direction, the flow control range of the high-energy fluid 7 blown out from the blowing hole 3 is limited, the whole spanwise direction cannot be covered, and the vortex generator 4 is arranged behind each blowing hole, so that the high-energy fluid blown out from the blowing hole can form two vortices with opposite vortex directions, the generated vortices can be developed towards the direction of higher spanwise direction and lower spanwise direction respectively, the control range of blowing is expanded, and flow separation is further inhibited.
The front edge of the air blowing cavity 2 is positioned at the position of 21.5 percent of blade chord of the subsonic speed vortex air blowing type blade in the chord length direction, the tail edge of the air blowing cavity is positioned at the position of 69 percent of blade chord of the subsonic speed vortex air blowing type blade in the chord length direction, the thickness between the air blowing cavity and the suction surface and the pressure surface of the blade is 1mm, the air blowing flow of 0.58 percent of inlet flow is met, and the structural strength of the subsonic speed vortex air blowing type blade is also ensured.
Drawings
FIG. 1 is a front view of a raw blade;
FIG. 2 is a top view of the original blade;
FIG. 3 is a front view of the blade of the present invention;
FIG. 4 is a top view of a blade of the present invention;
FIG. 5 is a three-dimensional view of the present invention;
figure 6 is an isometric three-dimensional view of a vortex generator.
Fig. 7 is a three-dimensional view of the vortex generator in elevation.
Fig. 8 is a left side view of the vortex generator.
FIG. 9 is a Mach number cloud for a raw blade at 50% of the spanwise cross-section of the blade under design conditions;
FIG. 10 is a Mach number cloud for a 50% spanwise cross-section of a blade according to the present invention at design conditions.
In the figure: 1. original leaves; 2. an air blowing cavity; 3. a gas blowing hole; 4. a vortex generator; 5. a curvature discontinuity; 6. a flow separation zone; 7. a high energy fluid.
Detailed Description
The embodiment is a subsonic vortex air blowing type compressor blade. The upper surface of the blowing type compressor blade is a suction surface, and the lower surface of the blowing type compressor blade is a pressure surface. An air blowing cavity 2 which is through along the span direction of the blade is arranged between the suction surface and the pressure surface of the blade. And a row of air blowing holes 3 are distributed on the suction surface along the unfolding direction, and the air blowing holes are communicated with the air blowing cavity. A row of vortex generators 4 are arranged on the rear edge of the suction surface of the blade along the unfolding direction, and the vortex generators are in one-to-one correspondence with the air blowing holes. When the vortex generator is installed, the direction of the front edge of each vortex generator is consistent with the direction of the front edge of each blade.
The center of each air blowing hole orifice is positioned at the position of 58.7 percent of the chord length of the blade on the suction surface; the center distance between the orifices of the adjacent air blowing holes is 10 mm. The intersection point of the front edge of the vortex generator and the suction surface is located at 73.2% of the chord length of the subsonic velocity vortex air blowing type blade suction surface.
The subsonic speed vortex air blowing type blade is obtained on the basis of the original blade 1. The chord length of the subsonic vortex air blowing type blade obtained after the improvement is 65mm, the span length is 100mm, the inlet geometric angle is 25.5 degrees, and the outlet geometric angle is-20.5 degrees. A curvature break point 5 exists on the suction surface of the subsonic vortex blowing type blade, and the curvature break point is located at the 56.6% of the chord length of the blade on the suction surface.
And a through air blowing cavity 2 is arranged between the suction surface and the pressure surface of the subsonic vortex air blowing type blade. The air blowing cavity penetrates through the subsonic velocity vortex air blowing type blade along the spanwise direction of the blade, so that the starting point of the air blowing cavity is located at 0% of the spanwise direction, and the terminal point of the air blowing cavity is located at 100% of the spanwise direction; the profile of the upper surface in the blowing cavity is the same as the profile of the suction surface of the blade, and the profile of the lower surface in the blowing cavity is the same as the profile of the pressure surface of the blade. The front edge of the air blowing cavity is located at the position, in the chord length direction, of 21.5% of the chord length of the subsonic speed vortex air blowing type blade, and the tail edge of the air blowing cavity is located at the position, in the chord length direction, of 69% of the chord length of the subsonic speed vortex air blowing type blade. The two ends of the air blowing cavity are arc-shaped, the arc radius of the front edge of the air blowing cavity is 1mm, and the arc radius of the tail edge of the air blowing cavity is 0.6 mm. The thickness between the blowing cavity and the suction surface and the pressure surface of the blade is 1 mm.
And a plurality of air blowing holes 3 communicated with the air blowing cavity 2 are distributed on the suction surface of the designed subsonic vortex air blowing type blade. The aperture of the air blowing hole 3 is 1mm, is a circular hole and is evenly distributed along the span direction of the blade. The central line of the air blowing hole is a straight line, and the included angle between the central line of the air blowing hole and the chord length direction is 3.8 degrees. The center of each air blowing hole opening is positioned at 58.7 percent of the chord length of the blade on the suction surface. The center distance between the orifices of the adjacent air blowing holes is 10 mm.
The vortex generator 4 is block-shaped, and has a triangular pyramid shape including a bottom surface and three triangular side surfaces. Wherein the bottom surface is a mounting surface of the vortex generator. One edge in the triangular pyramid is the leading edge of the vortex generator; the leading edge of the vortex generator is perpendicular to the bottom surface of the vortex generator. The intersection point of the front edge and the bottom surface is b, and the intersection point b is positioned at 73.2% of the chord length of the blade on the suction surface of the blade; the intersection points of the other two edges of the vortex generator and the bottom surface are respectively c1And c2(ii) a Intersection point c1And point of intersection c2Are all positioned at 75.9 percent of the chord length of the blade on the surface of the suction surface of the subsonic vortex blowing type blade.
The length between the vertex a of the vortex generator 4 and the intersection point b is 1mm, and the intersection point c1And c2The length between the two is 1.6mm, and the intersection point b and the intersection point c1The length between the point of intersection b and the point of intersection c2The lengths between the two parts are equal and are all 2 mm.
When the subsonic velocity vortex blowing type blade is installed on the grid plate, the grid distance is 35.71mm, the installation angle is 26.5 degrees, and the Mach number of the designed inlet of the blade grid is 0.6.
Claims (9)
1. The upper surface of the air blowing type compressor blade is a suction surface, and the lower surface of the air blowing type compressor blade is a pressure surface; it is characterized in that a spanwise blowing cavity is arranged between the suction surface and the pressure surface of the blowing type compressor blade; comprises an air blowing cavity, an air blowing hole and a vortex generator; a row of air blowing holes are distributed on the suction surface of the air blowing type compressor blade along the unfolding direction, and each air blowing hole is communicated with the air blowing cavity; a row of vortex generators are arranged on the rear edge of the suction surface of the blade along the unfolding direction, and the vortex generators are in one-to-one correspondence with the air blowing holes; the leading edge of each vortex generator is in the same direction with the leading edge of the blade.
2. The subsonic vortex blowing compressor blade of claim 1, wherein said blowing compressor blade has a chord length of 65 mm; the center of each air blowing hole orifice is positioned at the position of 58.7 percent of the chord length of the blade on the suction surface; the center distance between every two adjacent air blowing holes is 10 mm; the intersection point of the front edge of the vortex generator and the suction surface is located at 73.2% of the chord length of the subsonic velocity vortex air blowing type blade suction surface.
3. The subsonic vortex blowing compressor blade of claim 1, wherein said blowing compressor blade chord length is 65mm, span length is 100mm, inlet geometry angle is 25.5 °, outlet geometry angle is-20.5 °; a curvature mutation point 5 is formed at the intersection of the suction surface of the blade of the air blowing type compressor and the hole of the air blowing cavity; the curvature break point is located 56.6% of the blade chord length above the suction surface.
4. The subsonic velocity vortex blowing type compressor blade according to claim 1, characterized in that said blowing cavity penetrates said subsonic velocity vortex blowing type blade in the spanwise direction of the blade, so that the starting point of the blowing cavity is located at 0% of the spanwise direction and the end point is located at 100% of the spanwise direction; the molded surface of the inner upper surface of the air blowing cavity is the same as the molded surface of the suction surface of the blade, and the molded surface of the inner lower surface of the air blowing cavity is the same as the molded surface of the pressure surface of the blade; the front edge of the air blowing cavity is located at the position, in the chord length direction, of 21.5% of the chord length of the subsonic speed vortex air blowing type blade, and the tail edge of the air blowing cavity is located at the position, in the chord length direction, of 69% of the chord length of the subsonic speed vortex air blowing type blade.
5. The subsonic vortex blowing type compressor blade according to claim 4, characterized in that the arc radius of the leading edge of the blowing cavity is 1mm, and the arc radius of the trailing edge of the blowing cavity is 0.6 mm; the thickness between the blowing cavity and the suction surface and the pressure surface of the blade is 1 mm.
6. The subsonic velocity vortex air blowing type compressor blade as claimed in claim 1, wherein the aperture of each air blowing hole is 1mm, and the holes are uniformly distributed along the spanwise direction of the air blowing type compressor blade; the central line of the air blowing hole is a straight line, and the included angle between the central line of the air blowing hole and the chord length direction is 3.8 degrees; the centers of the orifices of the blowing holes on the suction surface are all positioned at 58.7 percent of the chord length of the blade on the suction surface; the center distance between the orifices of the adjacent air blowing holes is 10 mm.
7. The subsonic vortex blowing compressor blade of claim 1, wherein said vortex generator is block-shaped, having a triangular pyramid shape including a bottom surface and three triangular side surfaces; wherein the bottom surface is a mounting surface of the vortex generator; one edge in the triangular pyramid is the leading edge of the vortex generator; the vortex-generator leading edge is perpendicular to the bottom surface of the vortex generator.
8. The subsonic vortex blowing compressor blade as claimed in claim 7, wherein the intersection point of the vortex generator leading edge with the bottom surface is b, which is located at 73.2% of the blade chord length of the suction surface; the intersection points of the other two edges of the vortex generator and the bottom surface are respectively c1And c2(ii) a Intersection point c1And point of intersection c2Are all positioned at 75.9 percent of the chord length of the blade on the surface of the suction surface of the subsonic vortex blowing type blade.
9. The subsonic vortex blowing compressor blade as claimed in claim 7, wherein the length between the vertex a of the vortex generator and the intersection point b, where c is the intersection point, is 1mm1And c2The length between the two is 1.6mm, and the intersection point b and the intersection point c1The length between the point of intersection b and the point of intersection c2The lengths between the two parts are equal and are all 2 mm.
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| WO2023015931A1 (en) * | 2021-08-07 | 2023-02-16 | 广东美的暖通设备有限公司 | Axial flow wind wheel, air conditioner outdoor unit, and air conditioner |
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