CN113153815A - Supersonic adsorption type compressor blade based on multiple holes - Google Patents
Supersonic adsorption type compressor blade based on multiple holes Download PDFInfo
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- CN113153815A CN113153815A CN202011316109.8A CN202011316109A CN113153815A CN 113153815 A CN113153815 A CN 113153815A CN 202011316109 A CN202011316109 A CN 202011316109A CN 113153815 A CN113153815 A CN 113153815A
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D21/00—Pump involving supersonic speed of pumped fluids
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A suction cavity which is communicated in the blade span direction is arranged between the suction surface and the pressure surface of the supersonic velocity adsorption type compressor blade based on multiple holes. And a plurality of suction holes communicated with the suction cavity are distributed on the suction surface of the blade of the supersonic adsorption type compressor. Each suction hole is a circular hole or a rectangular hole with the same cross-sectional area. The pitch of the blades of the supersonic adsorption type compressor arranged on the grid plate is 30.55mm, and the installation angle is 47 degrees; when numerical simulation is carried out under the design working condition, the inlet airflow angle is 61 degrees, and the design inlet Mach number is 1.5. The invention avoids the reflection of shock waves on the surface of the suction surface and reduces the loss of air flow passing through the shock waves; meanwhile, the shock wave impact point is positioned in the suction hole, so that the mutual interference between the shock wave and the suction surface boundary layer is effectively weakened, the separation phenomenon of the suction surface boundary layer after the shock wave is generated is effectively inhibited, the phenomenon that the channel shock wave Mach number is too large due to the fact that the airflow is continuously accelerated on the suction surface is avoided, and the wave front Mach number and the shock wave loss are reduced.
Description
Technical Field
The invention relates to the field of gas compressors, in particular to a supersonic adsorption type gas compressor blade based on porous control shock wave/wall surface interference.
Background
The development of modern aircraft technology requires further improvements in the thrust-to-weight ratio of aircraft engines, i.e. fewer stages and higher stage loads. Inside the compressor, higher stage loads are usually accompanied by inevitable flow separation, and the flow loss and blockage caused by strong flow separation limit the increase of the stage loads of the compressor, and particularly, the shock waves existing in the cross-over and supersonic compressor make the internal flow of the compressor more complicated. Therefore, it is necessary to control the flow separation inside the compressor.
Since Kerreblank et al of MIT in 1997 originally proposed an adsorption compressor, the adsorption compressor gradually became an important research direction for improving the performance of the compressor. Schuler et al, in 2000 and 2005 published in ASME paper Design, analysis, and simulation of an instrumented Fan Stage (2000-GT-0618) and Experimental Investigation of a Trans rated Compressor (Journal of turbo engineering 2005, 02), respectively, numerically simulated Fan stages under designed and un-designed conditions demonstrated the feasibility of boundary layer suction at the blade surface and end wall, followed by a Transonic adsorption Compressor Test platform designed to study the effect of boundary layer suction, the Compressor achieved a maximum pressure ratio of 1.58 and 90% efficiency at Design point tip tangential speed of 228.6m/s, while the suction flow rate of the rotor and stator suction surfaces was only 0.5% of the inlet flow rate.
Wangchaogang et al developed a study on suction surface boundary layer suction for a certain high-load transonic compressor cascade in' suction flow and shock coherence study of adsorption type cascade (gas turbine experiment and study, 2008, 02), explored the coherent action of channel shock and boundary layer suction, and the result shows that suction performed before the position of the blade shock causes deterioration of the aerodynamic performance of the cascade; and suction after the shock wave position can obviously improve the cascade performance. The Lanxiang et al respectively carry out experimental research on a span/supersonic velocity adsorption type compressor blade cascade in a span and supersonic velocity adsorption type compressor plane blade cascade test (the year 05 of the aeronautical dynamics journal), and explore the influence of the position of a suction slit, suction flow, shock wave intensity and the like on a blade cascade flow field. In the numerical research on the influence of the combined suction groove on the performance of the rotor of the transonic compressor (proceedings of university of maritime affairs, 2017, period 01), Luhuawei et al design suction groove schemes with different combinations for a certain rotor case of the transonic compressor, and numerical results show that the case groove suction can effectively weaken the flow loss of a blade channel, the rotor leading edge dislocation normal shock wave is changed into an appendage oblique shock wave under the condition of high suction flow, and the shock wave intensity is reduced. The south friendship, et al, studied the influence of different positions and different suction quantities of the suction surface on the aerodynamic performance and flow field structure of the NASA rotor 37 blade in the "mechanism of suppressing boundary layer separation by suction of the suction surface of the rotor blade of the supersonic compressor" (the journal of the aeronautical dynamics, 2007, number 07), and the results showed that the optimum suction position is located at 80% of the chord length of the suction surface of the blade, and the corresponding optimum suction flow is 0.9% of the inlet flow of the compressor. In the research, the pneumatic performance of the adsorption type compressor is improved by sucking the shock wave rear boundary layer, but flow separation still exists in the compressor under the interference of the shock wave/wall surface.
The invention with the suction surface provided with the suction grooves is disclosed in the invention with the publication number of CN103321960A, and the suction control method of the compressor stator blade with the suction surface provided with the suction grooves is that 3 to 5 rows of suction grooves communicated with the vacuum cavity in the blade body are distributed on the suction surface of the blade body, and low-energy fluid in the boundary layer of the suction surface of the blade is sucked into the vacuum cavity through the suction grooves and is discharged through the suction holes, so that the separation of the boundary layer of the suction surface caused by overlarge blade bending angle is weakened or even eliminated, the load and the efficiency of the compressor are improved, and the actual requirement of suction of the boundary layer of the suction surface under different working conditions is met. However, the blade is a subsonic blade, and compared with a cross/supersonic compressor blade, the blade is low in load and small in diffusion factor.
The conventional cross/supersonic velocity adsorption type compressor blade/blade cascade improves the pneumatic performance of the compressor by sucking and exhausting low-energy fluid after shock through the boundary layer, but the suction surface of the blade still has flow separation after suction. Under the working conditions of high incoming flow Mach number and high load, the shock wave/wall interference effect in the blade grid channel is more serious, larger suction gap and the area of a suction cavity in the blade are needed to meet the requirement of large suction flow required by the high-load supersonic blade grid, and the large suction gap and the large suction cavity provide little challenge to the blade profile design and the structural strength of the supersonic blade.
Disclosure of Invention
In order to overcome the defects in the prior art, weaken the shock wave/wall interference effect under the high-load working condition and increase the structural strength of the blade, the invention provides a supersonic velocity adsorption type compressor blade based on multiple holes.
The inlet geometric angle of the supersonic adsorption type compressor blade is 14 degrees, and the outlet geometric angle is-14 degrees; the blade height is 100mm, and the blade chord length is 65 mm.
A suction cavity is arranged between the suction surface and the pressure surface of the supersonic adsorption type compressor blade and penetrates through the supersonic adsorption type compressor blade along the blade span direction of the blade. The molded surface of the upper surface of the suction cavity is the same as the molded surface of the original blade suction surface of the supersonic adsorption type compressor blade; the molded surface of the lower surface of the suction cavity is the same as the molded surface of the original blade pressure surface of the supersonic speed adsorption type compressor blade; the front edge and the rear edge of the suction cavity are respectively positioned at 22.4 percent and 73.9 percent of the chord length of the supersonic adsorption type compressor blade. And a plurality of suction holes communicated with the suction cavity are distributed on the suction surface of the supersonic adsorption type compressor blade. The suction holes are circular holes or rectangular holes. The included angle between the opening direction of each suction hole and the chord length direction of the blades of the supersonic adsorption type compressor is 47 degrees.
The suction holes are divided into two rows and are distributed along the suction surface of the blades of the supersonic adsorption type compressor in the unfolding direction; and a first row of suction holes are arranged near the front edge of the supersonic adsorption type compressor blade.
The center of the first row of suction hole orifices is positioned at 43% chord length of the supersonic adsorption type compressor blade. The centers of the two suction hole orifices in the first row of the two rows of suction holes are located at 3.1125% of the spanwise direction of the supersonic adsorption type compressor blade, and the centers of the two suction hole orifices in the last row of the two rows of suction holes are located at 96.8875% of the spanwise direction of the supersonic adsorption type compressor blade. The center distance d between the orifices of the adjacent suction holes in the same row is 3.025 percent of the spanwise length of the blades of the supersonic adsorption type compressor; the center distance c between the orifices of the adjacent suction holes in the same row is 4.628 percent of the chord length of the supersonic adsorption type compressor blade.
The front edge and the rear edge of the suction cavity are both arc-shaped with the radius of 0.4 mm; the wall thickness of the aspiration lumen is 0.5 mm.
When the suction hole is a circular hole, the radius r of the suction hole is 0.944 mm. When the suction hole is a rectangular hole, the long edge of the suction hole is distributed along the spanwise direction of the supersonic adsorption type compressor blade; the long side b of the rectangular hole is 2mm, and the short side a is 1.4 mm.
The cross-sectional area of the circular suction hole is the same as that of the rectangular suction hole.
The pitch of the blades of the supersonic adsorption type compressor arranged on the grid plate is 30.55mm, and the installation angle is 47 degrees; inlet airflow angle beta when numerical simulation is performed under design conditions1At 61 deg., an inlet mach number of 1.5 was designed.
The blade height of the original blade based on the prior art is 100mm, the chord length of the blade is 65mm, the inlet geometric angle is 14 degrees, and the outlet geometric angle is-14 degrees. When the original blade is arranged on the grid plate, the grid pitch is 30.55mm, the installation angle is 47 degrees, and the inlet airflow angle beta is1Is 61 deg.. Under the design condition, the inlet Mach number of the original blade cascade is 1.5, so that a linear inlet area blade profile and a pre-compression blade profile are adopted in the blade profile design of the original blade. The front section of the suction surface of the blade profile in the linear inlet area is a straight line and is tangent to the circular arc of the rear section of the suction surface, and the turning angle of the airflow at the front section of the blade profile is 0 degree. Different from the blade profile in a linear inlet area, the rotating angle of the front section of the suction surface of the pre-compression blade profile is a negative angle, and the molded line of the front section of the suction surface is tangent to the circular arc of the rear section of the suction surface. The maximum thickness position point 4 of the original blade is positioned at the position of 42 percent of the chord of the blade, the maximum thickness position point of the suction surface is connected with the tail edge of the original blade through an arc, the arc is tangent with the front section of the suction surface, and the circle of the molded line of the rear section of the suction surface of the original bladeThe arc is tangent with the front section molded line of the suction surface of the original blade at the position point of the maximum thickness of the original blade.
The invention increases a suction cavity 2 in the original blade, and increases a circular or rectangular suction hole on the suction surface of the blade to form the supersonic speed adsorption type compressor blade. The suction flow of the two suction holes under the design working condition is 6.1 percent of the mass flow of the blade grid inlet, so that the adhesion layer is ensured to be adhered to the suction surface of the blade of the supersonic velocity adsorption type compressor.
The invention adopts a full three-dimensional pneumatic optimization design method to design the blades. In the design, a porous suction surface boundary layer is adopted for pumping to control flow separation of the blades, the shock wave/wall interference effect is weakened, the structural strength of the blades is increased, and the shock wave front Mach number is reduced by utilizing a pre-compression blade profile. After preliminary design of the blades of the supersonic adsorption type compressor based on the multiple holes is completed, the blades of the supersonic adsorption type compressor are distributed into a blade cascade according to the design working condition, and three-dimensional numerical simulation is carried out on the blade cascade to obtain optimized technical parameters.
Compared with the prior art, the invention has the following beneficial effects:
FIG. 8 is a Mach number cloud of an original blade cascade at 50% of a spanwise cross section of a blade under a design condition, and FIG. 9 is a Mach number cloud of a supersonic absorption type compressor blade with a rectangular suction hole at 50% of the spanwise cross section of the blade under the design condition. As can be seen from the figure, in the original blade cascade channel, after the airflow passes through the bow shock wave 5, a flow separation area 6 is generated, and the area of the flow separation area is large, so that serious loss is caused; compared with the original blade, in the blade grid channel of the supersonic speed adsorption type compressor blade corresponding to the invention, the area of the flow separation area is sharply reduced under the action of porous suction after the airflow is subjected to shock, and the flow separation is almost eliminated. When the suction flow is 6.1% of the inlet mass flow, the supersonic velocity adsorption type compressor blade is effectively controlled by the post-shock wave flow separation. The static pressure ratio of the inlet and the outlet of the blade cascade of the supersonic adsorption type compressor with the rectangular suction hole reaches 3.15, and the diffusion factor D reaches 0.907. The control principle is as follows:
in the invention, the center of the first row of suction hole orifices is positioned at the position of 43 percent of the chord length of the blade, namely positioned at the downstream of the shock wave impact point 7 of the suction surface of the blade of the supersonic adsorption type compressor. The suction flow of the two suction holes under the design working condition is 6.1 percent of the mass flow of the blade grid inlet, so that the downstream boundary layer of the shock wave impact point is ensured to be attached to the suction surface of the blade of the supersonic velocity adsorption type compressor. The design principle is as follows: the porous boundary layer sucks and pumps low-energy fluid at the downstream of the shock wave impact point, and the thickness of the boundary layer 8 is reduced, so that the separation is not easy to occur; on the other hand, as shown in fig. 10, the suction of the porous boundary layer can cause the shock point of the suction surface shock wave to slightly move downstream, and the shock point is just positioned in the suction hole under the design working condition, so that the reflection of the shock wave on the surface of the suction surface is avoided, and the loss of the air flow passing through the shock wave is reduced; meanwhile, a boundary layer 8 is arranged between a main flow region 9 of the air flow and a suction surface of the blade of the supersonic adsorption type compressor, the boundary layer 8 is arranged between the main flow region 9 of the air flow and the suction surface of the blade of the supersonic adsorption type compressor, and a shock wave impact point is positioned in a suction hole, so that the mutual interference between a shock wave and the boundary layer 8 of the suction surface is effectively weakened, and the separation phenomenon of the boundary layer after the shock wave is effectively inhibited.
Because the Mach number of the designed inlet of the supersonic speed adsorption type compressor blade is as high as 1.5, a linear inlet area blade profile and a pre-compression blade profile are adopted in the blade profile design. The front section of the suction surface of the blade profile in the linear inlet area is a straight line, so that the turning angle of the airflow at the front section of the blade profile is 0 degree, and the phenomenon that the Mach number of the channel shock wave is too large due to continuous acceleration of the airflow on the suction surface is avoided. And the rotating angle of the front section of the suction surface of the pre-compression blade profile is a negative angle, and the supersonic air flow is compressed and decelerated by the front section of the suction surface of the blade of the supersonic adsorption type compressor, so that the wave front Mach number and the shock wave loss are reduced. The maximum thickness position point 4 of the supersonic speed adsorption type compressor blade is located at 42% of the blade chord position, the design principle is that a shock wave structure shown in figure 11 exists in a blade cascade channel of an original blade flowing down at supersonic speed, the shock wave structure is divided into bow shock waves and channel shock waves 10, under the design working condition, the maximum thickness position point of the original blade is arranged at the upstream of an impact point of a bow shock wave suction surface, under the condition that the sufficient throat area of the original blade cascade channel is ensured, the channel shock waves and the bow shock waves are enabled to be intersected at one point on the blade suction surface, and the boundary layer of the original blade suction surface is prevented from bearing two shock wave impact points. Subsequently, a porous suction is provided downstream of the shock point, and the advantages of the porous suction are exploited to the greatest extent, so that the length of the subsonic section downstream of the shock point, i.e. the pressure recovery zone 11, is maximized.
The suction flow of 6.1% of the mass flow of the blade grid inlet of the supersonic adsorption type air compressor is met through the suction cavity 2, and the wall thickness of the suction cavity of the supersonic adsorption type air compressor is 0.5mm, namely, the supersonic adsorption type air compressor has enough blade strength on the premise of ensuring sufficient suction flow.
Drawings
FIG. 1 is a schematic view of a circular suction hole structure;
FIG. 2 is a schematic view of a rectangular suction hole structure;
FIG. 3 is a top view of a supersonic absorption compressor blade having a circular suction hole;
FIG. 4 is a top view of a supersonic absorption compressor blade having a rectangular suction hole;
FIG. 5 is a front view of the present invention;
FIG. 6 is a top view of the original blade;
FIG. 7 is a front view of the original blade;
FIG. 8 is a Mach number cloud for a raw blade at 50% of the spanwise cross-section of the blade under design conditions;
FIG. 9 is a Mach number cloud for a 50% spanwise cross-section of the blade of the present invention at design conditions;
FIG. 10 is a schematic view of the suction side flow separation and shock/wall interference effect attenuation of the present invention blade;
FIG. 11 is a schematic view of the shock wave structure within a imperforate supersonic blade cascade channel.
Fig. 12 is a schematic view of channel shockwaves.
In the figure: 1. original leaves; 2. a suction lumen; 3. a suction hole; 4. a point of maximum thickness; 5. bow shock waves; 6. a flow separation zone; 7. shock wave impact points; 8. a surface layer; 9. a main flow zone; 10. channel shock waves; 11. a pressure recovery zone.
Detailed Description
The embodiment is a supersonic velocity adsorption type compressor blade based on multiple holes, the original blade of the supersonic velocity adsorption type compressor blade adopts the prior art, the inlet geometric angle is 14 degrees, and the outlet geometric angle is-14 degrees; the blade height is 100mm, and the blade chord length is 65 mm.
A suction cavity 2 is arranged between the suction surface and the pressure surface of the supersonic adsorption type compressor blade and penetrates through the supersonic adsorption type compressor blade along the blade span direction of the blade. The molded surface of the upper surface of the suction cavity is the same as the molded surface of the original blade suction surface of the supersonic adsorption type compressor blade; the molded surface of the lower surface of the suction cavity is the same as the molded surface of the original blade pressure surface of the supersonic speed adsorption type compressor blade; the front edge and the rear edge of the suction cavity 2 are both arc-shaped with the radius of 0.4 mm; the front edge and the rear edge of the suction cavity are respectively positioned at 22.4 percent and 73.9 percent of the chord length of the supersonic adsorption type compressor blade. The wall thickness of the suction chamber 2 is 0.5 mm.
And a plurality of suction holes 3 communicated with the suction cavity 2 are distributed on the suction surface of the supersonic adsorption type compressor blade. The suction holes are divided into two rows and are distributed along the suction surface of the blades of the supersonic adsorption type compressor in the unfolding direction; a first row of suction holes are arranged close to the front edge of the blade of the supersonic adsorption type compressor; the center of the first row of suction hole orifices is located at 43% chord length of the supersonic adsorption type compressor blade. The centers of the two suction hole orifices in the first row of the two rows of suction holes 3 are located at 3.1125% of the spanwise direction of the supersonic adsorption type compressor blade, and the centers of the two suction hole orifices in the last row are located at 96.8875% of the spanwise direction of the supersonic adsorption type compressor blade. The center distance d between the orifices of the adjacent suction holes in the same row is 3.025 percent of the spanwise length of the blades of the supersonic adsorption type compressor; the center distance c between the orifices of the adjacent suction holes in the same row is 4.628 percent of the chord length of the supersonic adsorption type compressor blade.
The suction holes 3 are divided into circular holes or rectangular holes. The included angle between the opening direction of each suction hole and the chord length direction of the blades of the supersonic adsorption type compressor is 47 degrees. When the suction hole is a circular hole, the radius r of the suction hole is 0.944 mm. When the suction hole is a rectangular hole, the long edge of the suction hole is distributed along the spanwise direction of the supersonic adsorption type compressor blade; the long side b of the rectangular hole is 2mm, and the short side a is 1.4 mm.
The cross-sectional area of the circular hole is the same as that of the rectangular hole.
When the supersonic adsorption type compressor blade provided by the invention is arranged on the grid plate, the grid pitch is 30.55mm, the installation angle is 47 degrees, and the advantage of porous suction is favorably brought into full play. When numerical simulation is carried out under the design working condition, the inlet airflow angle is 61 degrees, and the design inlet Mach number is 1.5.
Claims (8)
1. A supersonic adsorption type compressor blade based on multiple holes is characterized in that a suction cavity is arranged between a suction surface and a pressure surface of the supersonic adsorption type compressor blade and penetrates through the supersonic adsorption type compressor blade along the blade span direction of the blade; the molded surface of the upper surface of the suction cavity is the same as the molded surface of the original blade suction surface of the supersonic adsorption type compressor blade; the molded surface of the lower surface of the suction cavity is the same as the molded surface of the original blade pressure surface of the supersonic speed adsorption type compressor blade; the front edge and the rear edge of the suction cavity are respectively positioned at 22.4 percent and 73.9 percent of the chord length of the supersonic speed adsorption type compressor blade; a plurality of suction holes communicated with the suction cavity are distributed on the suction surface of the blade of the supersonic velocity adsorption type compressor; the suction holes are circular holes or rectangular holes; the included angle between the opening direction of each suction hole and the chord length direction of the blades of the supersonic adsorption type compressor is 47 degrees.
2. The multi-hole-based supersonic adsorption type compressor blade according to claim 1, wherein the suction holes are divided into two rows which are arranged along the suction surface of the supersonic adsorption type compressor blade in the spanwise direction; a first row of suction holes are arranged close to the front edge of the blade of the supersonic adsorption type compressor; the center of the first row of suction hole orifices is positioned at 43% chord length of the supersonic adsorption type compressor blade; the centers of the orifices of the two suction holes in the first row of the two rows of suction holes are positioned at 3.1125% in the spanwise direction of the supersonic adsorption type compressor blade, so that the centers of the orifices of the two suction holes in the last row are positioned at 96.8875% in the spanwise direction of the supersonic adsorption type compressor blade; the center distance d between the orifices of the adjacent suction holes in the same row is 3.025 percent of the spanwise length of the blades of the supersonic adsorption type compressor; the center distance c between the orifices of the adjacent suction holes in the same row is 4.628 percent of the chord length of the supersonic adsorption type compressor blade.
3. The porous-based supersonic adsorption type compressor blade according to claim 1, wherein the leading edge and the trailing edge of the suction cavity are both arc-shaped with a radius of 0.4 mm; the wall thickness of the aspiration lumen is 0.5 mm.
4. The multihole-based supersonic absorption compressor blade of claim 1, wherein when the suction holes are circular holes, the radius r of the suction holes is 0.944 mm.
5. The multi-hole-based supersonic adsorption type compressor blade of claim 1, wherein when the suction holes are rectangular holes, the long sides of the suction holes are distributed along the spanwise direction of the supersonic adsorption type compressor blade; the long side b of the rectangular hole is 2mm, and the short side a is 1.4 mm.
6. The multi-hole-based supersonic absorption compressor blade of claim 1, wherein the circular suction holes have a cross-sectional area that is the same as the rectangular suction holes.
7. The multi-bore based supersonic adsorption compressor blade of claim 1, wherein the supersonic adsorption compressor blade has an inlet geometry angle of 14 ° and an outlet geometry angle of-14 °; the blade height is 100mm, and the blade chord length is 65 mm.
8. The multi-hole-based supersonic adsorption type compressor blade according to claim 1, wherein the pitch of the supersonic adsorption type compressor blade mounted on the grid plate is 30.55mm, and the mounting angle is 47 °; under the design conditionAt the time of numerical simulation, the inlet flow angle beta1At 61 deg., an inlet mach number of 1.5 was designed.
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| CN202011316109.8A CN113153815B (en) | 2020-11-22 | 2020-11-22 | Supersonic adsorption type compressor blade based on multiple holes |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113446261A (en) * | 2021-07-24 | 2021-09-28 | 西北工业大学 | Supersonic adsorption type compressor serial stator blade |
| CN113847277A (en) * | 2021-10-17 | 2021-12-28 | 西北工业大学 | Supersonic speed porous adsorption type compressor blade with corrugated groove on suction surface |
| CN115450953A (en) * | 2022-11-01 | 2022-12-09 | 吉林大学 | Bionic steady flow structure for noise reduction of impeller machinery |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5890874A (en) * | 1996-02-02 | 1999-04-06 | Rolls-Royce Plc | Rotors for gas turbine engines |
| CN101050771A (en) * | 2007-05-11 | 2007-10-10 | 北京航空航天大学 | Method for improving air compressor blade load by using pumping and sucking |
| CN101092978A (en) * | 2007-07-30 | 2007-12-26 | 北京航空航天大学 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
| US20100322777A1 (en) * | 2009-06-22 | 2010-12-23 | Rolls-Royce Plc | Compressor blade |
| CN102312860A (en) * | 2011-09-01 | 2012-01-11 | 西北工业大学 | Suction surface sucking stator blade of air compressor |
| CN103133057A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | T-shaped groove structure adsorption type hollow stator blade |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| WO2018216255A1 (en) * | 2017-05-24 | 2018-11-29 | 株式会社Ihi | Blade for fan and compressor |
| CN109162952A (en) * | 2018-09-11 | 2019-01-08 | 西北工业大学 | A kind of adsorption type compressor louver experiment device |
-
2020
- 2020-11-22 CN CN202011316109.8A patent/CN113153815B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5890874A (en) * | 1996-02-02 | 1999-04-06 | Rolls-Royce Plc | Rotors for gas turbine engines |
| CN101050771A (en) * | 2007-05-11 | 2007-10-10 | 北京航空航天大学 | Method for improving air compressor blade load by using pumping and sucking |
| CN101092978A (en) * | 2007-07-30 | 2007-12-26 | 北京航空航天大学 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
| US20100322777A1 (en) * | 2009-06-22 | 2010-12-23 | Rolls-Royce Plc | Compressor blade |
| CN102312860A (en) * | 2011-09-01 | 2012-01-11 | 西北工业大学 | Suction surface sucking stator blade of air compressor |
| CN103133057A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | T-shaped groove structure adsorption type hollow stator blade |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| WO2018216255A1 (en) * | 2017-05-24 | 2018-11-29 | 株式会社Ihi | Blade for fan and compressor |
| CN109162952A (en) * | 2018-09-11 | 2019-01-08 | 西北工业大学 | A kind of adsorption type compressor louver experiment device |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113446261A (en) * | 2021-07-24 | 2021-09-28 | 西北工业大学 | Supersonic adsorption type compressor serial stator blade |
| CN113446261B (en) * | 2021-07-24 | 2023-06-23 | 西北工业大学 | Ultrasonic adsorption type tandem stator blade of gas compressor |
| CN113847277A (en) * | 2021-10-17 | 2021-12-28 | 西北工业大学 | Supersonic speed porous adsorption type compressor blade with corrugated groove on suction surface |
| CN115450953A (en) * | 2022-11-01 | 2022-12-09 | 吉林大学 | Bionic steady flow structure for noise reduction of impeller machinery |
| CN115450953B (en) * | 2022-11-01 | 2024-05-07 | 吉林大学 | Bionic steady flow structure for noise reduction of impeller machinery |
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