CN113153815B - Supersonic adsorption type compressor blade based on multiple holes - Google Patents

Supersonic adsorption type compressor blade based on multiple holes Download PDF

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Publication number
CN113153815B
CN113153815B CN202011316109.8A CN202011316109A CN113153815B CN 113153815 B CN113153815 B CN 113153815B CN 202011316109 A CN202011316109 A CN 202011316109A CN 113153815 B CN113153815 B CN 113153815B
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suction
supersonic
blade
adsorption type
type compressor
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CN113153815A (en
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曹志远
宋澄
高玺
张飞
张翔
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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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
    • 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
    • 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
    • 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
    • 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 supersonic adsorption type compressor blade. Each suction hole is a circular hole or a rectangular hole with the same cross section 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 boundary layer of the suction surface is effectively weakened, the phenomenon of separation of the boundary layer after the shock wave 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

Supersonic adsorption type compressor blade based on multiple holes
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.
Wangchen et al developed the study of suction surface boundary layer suction on a certain high-load transonic compressor cascade in the study of coherence of suction flow and shock wave of an adsorption type cascade (gas turbine experiment and study, 2008, 02), and studied the coherent action of channel shock wave and boundary layer suction, and the result shows that the pneumatic performance of the cascade is deteriorated when suction is performed before the position of the shock wave of the blade; and suction after the shock wave position can obviously improve the cascade performance. Lanxiang et al respectively carried out experimental research on a span/supersonic velocity adsorption type compressor blade cascade in a span/supersonic velocity adsorption type compressor plane blade cascade test (aeronautical dynamics journal, 2010, 05), and explored the influence of a suction slit position, 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 rotor performance of the transonic compressor (proceedings of university of maritime affairs, 2017, stage 01), luhuawei et al design suction groove schemes with different combinations for a certain transonic compressor rotor casing, and numerical results show that the casing 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 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 surface extraction of the supersonic compressor rotor blade" (journal of the aeronautical dynamics, no. 07 in 2007), and the results showed that the optimal suction position is located at 80% chord length of the blade suction surface, and the corresponding optimal suction flow is 0.9% of the compressor inlet flow. 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 creation with the publication number of CN103321960A, the suction control method of the compressor stator blade comprises the steps 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, low-energy fluid in the boundary layer of the suction surface of the blade is sucked into the vacuum cavity by 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 blade/blade cascade of the cross/supersonic velocity adsorption type compressor improves the pneumatic performance of the compressor by sucking and pumping low-energy fluid after shock waves 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 65mm.
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 profile of the upper surface of the suction cavity is the same as the profile of the original blade suction surface of the supersonic adsorption type compressor blade; the profile of the lower surface of the suction cavity is the same as the profile of the original blade pressure surface of the supersonic 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 supersonic velocity adsorption type compressor blade is 47 degrees.
The suction holes are divided into two rows and distributed along the suction surface of the blades of the supersonic adsorption type compressor in the unfolding direction; the first row of suction holes are close to 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 positioned 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 positioned 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 span length of the supersonic adsorption type compressor blade; 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 0.5mm.
When the suction hole is a circular hole, the radius r of the suction hole is 0.944mm. When the suction hole is a rectangular hole, the long edge of the suction hole is distributed along the spanwise direction of the supersonic velocity adsorption type compressor blade; the long side b =2mm and the short side a =1.4mm of the rectangular hole.
The cross-sectional area of the circular suction hole is the same as that of the rectangular suction hole.
The blades of the supersonic adsorption type compressor are arranged on the grid plateThe grid pitch is 30.55mm, and the installation angle is 47 degrees; when numerical simulation is performed under design conditions, the inlet airflow angle beta 1 At 61 deg., the inlet mach number was designed to be 1.5.
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 is 1 Is 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 located at the position of 42% of the blade chord, 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 arc of the molded line of the rear section of the suction surface of the original blade is tangent with the molded line of the front section of the suction surface of the original blade at the maximum thickness position point 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 velocity adsorption type compressor blade of the invention. 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 the 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-compressed 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 blade of the supersonic adsorption type compressor corresponding to the invention, the area of the flow separation area is sharply reduced under the action of porous suction after the airflow passes through the shock wave, 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 cascade 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 wave impact point of the suction surface to slightly move downstream, and the shock wave impact 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 airflow 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 pre-compression blade-type suction surface 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 velocity adsorption type compressor blade is located at 42% of the blade chord length, the design principle is that a shock wave structure shown in figure 11 exists in a cascade channel of an original blade under the supersonic velocity, 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, to maximize the advantages of the porous suction, such that the length of the subsonic section downstream of the shock point, i.e. the pressure recovery zone 11, is maximized.
The invention meets the suction flow of 6.1 percent of the mass flow of the blade grid inlet of the supersonic adsorption type compressor through the suction cavity 2, and the wall thickness of the suction cavity of the supersonic adsorption type compressor is 0.5mm, namely, the supersonic adsorption type compressor has enough blade strength on the premise of ensuring enough 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 rectangular suction holes;
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 plot for a 50% spanwise cross-section of a blade of the present invention at design conditions;
FIG. 10 is a schematic view of the suction side flow separation and shock wave/wall interference attenuation effect 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 diagram 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 adsorption type compressor blade based on multiple holes, the original blade of the supersonic 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 65mm.
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 profile of the upper surface of the suction cavity is the same as the profile 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 0.5mm.
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 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 of the first row in the two rows of suction holes 3 are located at 3.1125% of the spanwise direction of the supersonic absorption compressor blade, and the centers of the two suction hole orifices of the last row are located at 96.8875% of the spanwise direction of the supersonic absorption 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 0.944mm. 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 =2mm and the short side a =1.4mm of the rectangular hole.
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 fully exerted. 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 (6)

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 profile of the lower surface of the suction cavity is the same as the profile of the original blade pressure surface of the supersonic 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; 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;
the suction holes are uniformly distributed in 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 positioned at 43% chord length of the supersonic adsorption type compressor blade; the centers of two suction hole orifices in the first row of two rows of suction holes are positioned at 3.1125% of the spanwise direction of the supersonic adsorption type compressor blade, and the centers of two suction hole orifices in the last row of two suction holes are positioned 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 span length of the supersonic adsorption type compressor blade; the center distance c between the orifices of adjacent suction holes in the same row is 4.628 percent of the chord length of the blades of the supersonic adsorption type compressor;
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 65mm.
2. 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 0.5mm.
3. 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 0.944mm.
4. The multi-hole-based supersonic absorption compressor blade according to 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 absorption compressor blade; the long side b =2mm and the short side a =1.4mm of the rectangular hole.
5. 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.
6. The multi-hole-based supersonic adsorption compressor blade according to claim 1, wherein the supersonic adsorption compressor blade is installed on the grid plate with a grid pitch of 30.55mm and an installation angle of 47 °; when numerical simulation is performed under design conditions, the inlet airflow angle beta 1 At 61 deg., the inlet mach number was designed to be 1.5.
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CN113847277B (en) * 2021-10-17 2023-06-23 西北工业大学 Supersonic porous adsorption type compressor blade with corrugated grooves on suction surface
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