CN113446261B - Tandem stator blades of a supersonic adsorption compressor - Google Patents

Abstract

A plurality of tandem stator blades are formed by one-to-one correspondence of front row blades and rear row blades of a supersonic adsorption type compressor. A suction cavity is arranged between the suction surface and the pressure surface of the front row of blades, the suction cavity penetrates through the front row of blades along the blade expanding direction so as to weaken the flow separation phenomenon, the flow is controlled, and the serial blades are used for ensuring that smaller flow separation is generated under the condition of increasing the load. And (3) a blade. A suction slot is formed on the suction surface of the front row of blades; the suction seam is a continuous suction seam or an intermittent staggered suction seam. The ultrasonic adsorption type compressor serial stator blade cascade channel provided by the invention has the advantages that the area of the flow separation area is obviously reduced and the flow separation is almost completely eliminated under the coupling effect of the suction technology and the flow control technology of the serial blades after the airflow in the ultrasonic adsorption type compressor serial stator blade cascade channel passes through shock waves.

Description

Tandem stator blades of a supersonic adsorption compressor

technical field

The invention relates to the field of aeroengine compressors, in particular to a supersonic adsorption type tandem stator blade.

Background technique

With the rapid development of modern advanced aerodynamic devices, the demand for high thrust-to-weight ratio engines is increasingly urgent. High thrust-to-weight ratio engines require the compressor to work under the conditions of high pressure ratio, high efficiency and margin, resulting in continuous increase in the load of the compressor. The high pressure ratio causes a strong reverse pressure gradient inside the compressor, thus controlling the blade suction under the strong reverse pressure gradient The flow separation of the surface has become an important factor to be considered in the study of compressor aerodynamics. Therefore, under the condition that the speed of the compressor is limited, the development of a new flow control method has become an important research content of the aerodynamic design of the aeroengine compressor.

Tandem cascades as a passive flow control technology, U.K.Saha, and B.Roy in "Experimental Investigations on Tandem Compressor Cascade Performance at Low Speeds" ("Experimental Thermal and Fluid Science", Issue 3, Volume 14, 1997 Edition) , and E.-G.Feindt said in "Exact Calculation of the Flow of a Staggered Tandem Cascade with Moving Second Blade Row" ("Archive of Applied Mechanics" 2001 No. 9, Volume 71) that string can be used on the aero-engine The form of row cascades, that is, adopting the form of front row blades and rear row blades in series on the same stage of stator blades reduces the phenomenon of flow separation.

Boundary layer suction technology is a kind of active flow control technology. Since 1997, J.L.Kerrebrock and others from MIT have published "Aspired Compressors" in "Proceedings of the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition" Volume 1, 1997 The concept of the adsorption compressor was first proposed in the paper, and the boundary layer suction technology has gradually attracted the attention of researchers. The single-stage adsorption transonic compressor introduced by AliMerchant of MIT in "Design and Analysis of Axial Aspirated Compressor Stages" ("ThesisMassachusetts Institute of Technology" 1999) made the boundary layer suction technology successful. verified.

The domestic research on the boundary layer suction technology mainly focuses on the numerical simulation of the cascade. Chen Fu et al. published "Boundary layer suction on the consistency characteristics of the compressor cascade" in the second issue of "Journal of Engineering Thermophysics" in 2005. "Influence" and Ge Zhengwei and others introduced the research on the numerical simulation of the cascade in the "Numerical Simulation of the Flow Field of the Adsorption Transonic Compressor Cascade" in the "Journal of Aerodynamics" No. 8, 2007. The research shows that the adsorption cascade It has little impact on the quality of the single stage of the compressor, and can effectively improve the thrust-to-weight ratio of the aero-engine. At the same time, it should be pointed out that the suction of the moving blade will cause problems in the strength of the blade, but the above-mentioned problems do not exist in the suction of the stationary blade.

Lan Faxiang et al. conducted experimental research on trans/supersonic adsorption compressor cascades in the "Trans- and Supersonic Adsorption Compressor Plane Cascade Test" ("Journal of Aerodynamics" 2010 No. 5) to explore the suction gap. The influence of location, suction flow rate, and shock wave intensity on the cascade flow field, the results show that the best suction position is located downstream of the channel shock wave, and the greater the shock wave intensity, the more obvious the suction effect.

Cao Zhiyuan’s doctoral dissertation “Research on the Effect of Boundary Suction on the Flow Control and Performance of Axial Flow Compressors” designed a compressor with a single-stage pressure ratio exceeding 4.5. Difficult to achieve expansion and diversion.

In the invention with the application number 202011316109.8, a supersonic adsorption compressor blade based on porous is disclosed, and the flow separation phenomenon is reduced by performing porous suction on the supersonic compressor blade.

In the invention with the publication number CN120214029, a combined suction cascade experimental device is disclosed. By slotting grooves in the end wall of the cascade and the suction surface of the blade, the low-energy fluid is drawn out from the end wall and the suction surface respectively, so as to achieve the The purpose of controlling the suction flow of the end wall and the suction surface of the blade.

The technical solutions disclosed in the above-mentioned documents/inventions are all based on the research results of blades under supersonic flow conditions under various flow control technologies. Although the flow conditions have been improved, the flow separation phenomenon is still not well controlled. , using suction to control will cause shock wave/wall interference phenomenon, which will strengthen the shock wave and change the shock wave position. The change of shock wave position will lead to more serious flow separation phenomenon.

Contents of the invention

In order to overcome the deficiencies in the prior art that the use of adsorption blades under the condition of supersonic incoming flow will produce shock wave/wall interference effect, induce shock wave enhancement and position change, and cause greater flow separation phenomenon, the present invention proposes A supersonic adsorption type compressor tandem stator blades.

The present invention includes a plurality of front row blades and a plurality of rear row blades; a plurality of tandem stator blades are composed of each of the front row blades and the rear row blades in one-to-one correspondence. A suction cavity is formed between the suction surface and the pressure surface of the front row of blades, and the suction cavity penetrates the blade along the span direction of the blade. There are suction slots on the suction surface of the front blades; the suction slots are continuous suction slots or intermittent suction slots or intermittent misplaced suction slots. The suction slots are distributed along the span direction of the front row of blades and communicate with the suction cavity. The width of each suction slit is 1.8mm.

The front blades are cascaded with the rear blades through the suction slots on the suction surface and the suction cavity inside the front blades, and are fixed on the hub, and at the same time, the suction surface is opened along the suction surface at the end wall of the hub. The suction slots form the tandem stator blades of the supersonic adsorption compressor of the present invention. A plurality of front row blade end wall suction slots and rear row blade end wall suction slots are added on the hub.

Install the blade root of each tandem stator blade on the outer peripheral surface of the hub of the compressor, install the tip of each tandem stator blade on the inner peripheral surface of the compressor rectifier casing, and make the front of each tandem stator blade The edge faces the incoming flow.

The apex of one end of the leading edge of the suction cavity is 22.4% of the chord length from the leading edge of the blade in the chord direction, and the apex of the leading edge of the rear suction cavity is 73.9% of the chord length from the leading edge of the blade in the chord direction. The profile of the upper surface of the suction cavity is the same as that of the suction surface of the blade; the profile of the lower surface of the suction cavity is the same as that of the pressure surface. Both ends of the suction chamber are arcs with a radius of 0.4 mm. The wall thickness of the suction cavity is 0.5mm.

When the continuous suction slot is used, the suction slot is a continuous rectangular groove, and the center line in the width direction of the suction slot is located at 43% of the chord length of the front blades.

When the intermittent suction slot is used, the suction slot is composed of a plurality of single suction slots arranged along the blade span direction, and the centerline of the width direction of the suction slot is located at 43% of the chord length of the front row of blades. The length of each single suction slit is 18 mm, and the distance between adjacent edges of two suction slits is 2 mm. The single suction slots are arranged from the tip of the blade.

When using intermittent dislocation suction slots, the suction slots are composed of a plurality of single suction slots arranged along the blade span direction, and each single suction slot is arranged alternately in two rows on the suction surface of the front row of blades, so that The center line in the width direction of one row of suction slits is located at 43% of the chord length of the front row of blades, and the center line of the width direction of the other row of suction slits is located at 45% of the chord length of the front row of blades. The length of each of the individual suction slits is 18 mm.

In the same row of leaves:

The intersection point of the arc of the front row of blades and the leading edge of the front row of blades is the leading edge of the tandem blades, and the intersection of the arc of the rear row of blades and the trailing edge of the rear row of blades is the trailing edge of the tandem blades. The connecting line between the leading edge and the trailing edge obtains the total chord length of the tandem blades; the total chord length of the tandem blades is 65mm.

The axial distance between the trailing edge of the front row of blades and the leading edge of the rear row of blades is -3mm, and the circumferential offset between the trailing edge of the front row of blades and the leading edge of the rear row of blades is 4mm.

The included angle between the tangent of the center arc of the front row of blades at the leading edge point of the front row of blades and the tangent of the center arc of the rear row of blades at the trailing edge of the rear row of blades is a total bending angle, and the total bending angle is 13°.

During installation, the leading edge of the front row blades in each of the tandem stator blades is located at 5% of the axial length of the hub. The total installation angle of each of the tandem blades is 37°.

The blade height of the front row of blades is 100 mm, the blade chord length is 45 mm, the inlet geometric angle is 14°, and the outlet geometric angle is -14°. When the blades are installed on the hub, the distance between adjacent front row blades is 30.55mm, the installation angle is 47°, and the inlet airflow angle is 61°.

The convex arc surface of the front blades is the suction surface, and the concave arc surface is the pressure surface. The point of maximum thickness for this leading row of blades is at 42% of the blade chord length. The radius of the suction surface between the maximum thickness position point and the trailing edge of the front row of blades is an arc surface of 150mm; the suction surface between the maximum thickness position point and the leading edge of the front row of blades is a plane; The arc surface and the plane smoothly intersect at the point of the maximum thickness position. The pressure surface of the front row of blades adopts a circular arc surface with a radius of 170mm.

The chord length of the rear blades is 33mm, and the blade height is 100mm; the maximum thickness is located at 50% of the chord length of the rear blades, and the maximum thickness is 14mm; the convex arc surface of the rear blades is the suction surface, and the concave arc surface is the pressure surface; the radius of the suction surface is 87.8mm, and the radius of the pressure surface is 138mm.

The suction slot on the end wall of the front row of blades is located on one side of the suction surface of the front row of blades and extends along the chord direction; the width of the suction slot on the end wall of the front row of blades is 1.8mm; the width of the suction slot on the end wall of the front row of blades The distance from the centerline of the direction to the suction surface of the blade is 3mm; the shape of the suction slot on the end wall of the front row blade is the same as that of the suction surface of the front row blade;

The suction slot of the front blades is divided into a front section and a rear section; the suction slot of the front section is a continuous suction slot, the starting point is located at a distance of 8% to 13% of the chord length from the front edge of the front blade, and the end point is located at a distance of 8% to 13% from the front edge of the front blade. 43% of the chord length of the leading edge of the row of blades; the rear section of the suction slot is composed of multiple discontinuous small suction slots, and the starting point of the rear section of the suction slot is located at 45% of the chord length from the front edge of the front row of blades , the end point is located at 100% of the chord length from the leading edge of the front row of blades; the distance between each adjacent small suction slot in the intermittent suction slot of the rear section is 2% of the chord length of the front row of blades; The length of the small suction slot is 3% of the chord length of the front row of blades.

The suction slots on the end walls of the rear blades are located on one side of the suction surface of the rear blades and extend along the chord direction. The width of the suction slots on the end walls of the rear blades is 1.8mm; the suction slots on the end walls of the rear blades The shape is the same as that of the suction surface of the rear row of blades; the suction slot on the end wall of the rear row of blades is divided into a first suction slot and a second suction slot;

The first suction slot is divided into a front section and a rear section; the front section of the first suction slot is a continuous suction slot, the starting point is located at 3% of the chord length from the leading edge of the rear row of blades, and the end point is located at a distance from the rear row of blades. 78% of the chord length of the leading edge; the rear section of the first suction slot is composed of a plurality of discontinuous small suction slots, and the starting point of the rear section is located at 80% of the chord length from the leading edge of the rear row of blades, and the end point is Located at 100% of the chord length from the leading edge of the rear row of blades; the distance from the centerline in the width direction of the first suction slot to the suction surface of the blade is 6mm;

The second suction slot is also divided into a front section and a rear section; the front section of the first suction slot is a continuous suction slot, the starting point is located at 17% of the chord length from the leading edge of the rear row of blades, and the end point is located at a distance from the rear row of blades. 78% of the chord length of the leading edge; the rear section of the second suction slot is composed of a plurality of discontinuous small suction slots, and the starting point of the rear section is located at 80% of the chord length from the leading edge of the rear row of blades, and the end point is Located at 100% of the chord length from the leading edge of the rear row of blades; the distance from the centerline in the width direction of the second suction slot to the suction surface of the blade is 3mm;

Among the small suction slots in the rear section of the first suction slot and in the small suction slots in the rear section of the second suction slot, the distance between adjacent small suction slots is 2 times the chord length of the rear blades. %; the length of each small suction slot is 3% of the chord length of the rear row of blades.

The tandem stator blades of the compressor in the present invention are divided into front row stator blades and rear row stator blades, which are referred to as front row blades and rear row blades for short. In order to reduce the flow separation phenomenon as much as possible, the flow control is carried out through the tandem blades to ensure that under the condition of increased load, a small flow separation occurs. The front row of blades takes most of the load, and the rear row of blades is responsible for turning the airflow.

The front row of blades bears most of the load, and since the curvature of the blade profile and its derivative will directly affect the performance of the blade, the specific theoretical analysis of the blade profile design of the blade is as follows: the growth of the boundary layer along the side of the suction surface determines the type The curvature distribution change of the line on the suction side from the leading edge to the trailing edge, deduce the coordinates of each point on the suction side side from the curvature distribution change, and then determine the area distribution of the cross section, and calculate the curvature distribution of the profile line on the pressure side side by comprehensive constraints , similarly, deduce the coordinates of each point on the side of the pressure surface. In order to close the suction side and the pressure side of the profile line, the leading edge of the pressure side is smoothly connected with the leading edge of the suction side, and the trailing edge of the pressure side is smoothly connected with the trailing edge of the suction side to obtain a complete two-dimensional section of the front blade leaf type.

Compared with prior art, the beneficial effect that the present invention obtains is:

The invention adopts a full three-dimensional aerodynamic optimization design method to design blades. In the design, suction at the boundary layer of the suction surface is used to control the flow separation of the blades, weaken the shock wave/wall interference effect, increase the structural strength of the blades, and use the pre-compression blade shape to reduce the Mach number of the shock wave front. After the preliminary design of the tandem stator blades of the supersonic adsorption compressor is completed, the tandem stator blades of the supersonic adsorption compressor are arranged into a cascade according to the design conditions, and a three-dimensional numerical simulation is performed on the cascade.

The use of suction slots to control the flow separation under the condition of supersonic incoming flow will cause shock wave/wall interference phenomenon, but the suction will further strengthen the shock wave and change the position of the shock wave, while the change of the shock wave position induces a stronger flow separation.

In the present invention, through the discontinuous suction slots arranged on the end walls of the front blades, the shock wave hits the discontinuous suction slots at the shock wave impact point 7, thereby generating expansion waves, which intersect with the shock waves, and then Weaken or cancel each other, so that the shock wave/wall interference phenomenon caused by the suction is weakened or disappeared, and the effect of the suction under the condition of supersonic incoming flow is fully reflected, and the flow separation phenomenon is controlled. The sucked low-energy fluid converges to the low-energy fluid converging place 8 to collect.

Because the present invention uses tandem blades, there will be low-energy fluid in the wake and end wall area of the front blades, while the suction slots on the end walls of the rear blades adopt a double-slit structure, and the first suction slot is aimed at the wake and the end wall of the front blades. The low-energy fluid in the end wall area is used for suction, and the second suction slot is for the low-energy fluid of the rear blades. At the same time, in order to control the suction flow, an intermittent suction slot is used at the position of 78% of the length of the suction slot. , to avoid traffic loss.

At the same time, the adoption of adsorption tandem stator blades can reduce the weight of the stator blades and eliminate the phenomenon of flow separation.

In the cascade channel of the tandem blades without suction, the air flow passes through the bow shock wave 6 to generate flow separation, and the flow separation area is very large, causing serious losses.

In the cascade passage of the tandem stator blades of the supersonic adsorption compressor proposed by the present invention, after the air flow passes through the shock wave, the area of the flow separation area is significantly reduced under the action of the coupling of the suction and the flow control technology of the tandem blades, Flow separation is almost completely eliminated.

Description of drawings

Fig. 1 is the front view of the supersonic adsorption compressor tandem blade front row blades with various forms of suction slots; wherein: Fig. 1a is a continuous rectangular suction slot, Fig. 1b is an intermittent rectangular suction slot, Fig. 1c is a rectangular suction slit distributed in a staggered manner.

Figure 2 is a top view of the tandem blades of the supersonic adsorption compressor with suction slots;

Fig. 3 is a schematic diagram of the shock wave structure in the tandem blade cascade channel of the supersonic adsorption compressor;

Fig. 4 is a schematic diagram of the end wall suction slots of the front blades and the rear blades of the tandem blades of the supersonic adsorption compressor;

Fig. 5 is a three-dimensional view of a group of supersonic adsorption compressor tandem blades with suction slots of the present invention;

Fig. 6 is a three-dimensional view of the tandem blades of the supersonic adsorption compressor with suction slots of the present invention.

Fig. 7 is the Mach number nephogram of the tandem blades without suction under design conditions;

Fig. 8 is a Mach number nephogram of the tandem blades of the present invention under design working conditions.

In the figure: 1. Front row of blades; 2. Rear row of blades; 3. Suction slot; 4. Suction chamber; 5. Hub; 6. Bow shock wave; 7. Shock wave impact point; ; 9. Rectifier casing; 10. Front row blade end wall suction slot; 11. Rear row blade end wall suction slot; 12. First suction slot; 13. Second suction slot.

Detailed ways

This embodiment is a tandem stator blade of a supersonic adsorption compressor, including a plurality of front row blades 1 and a plurality of rear row blades 2 . A plurality of tandem stator blades are composed of the front row of blades and the rear row of blades in one-to-one correspondence. Install the blade root of each tandem stator blade on the outer circumferential surface of the hub 5 of the compressor, install the tip of each tandem stator blade on the inner circumferential surface of the compressor rectifier casing 9, and make each tandem stator blade The leading edge faces the incoming flow.

The front blades are cascaded with the rear blades through the suction slots on the suction surface and the suction cavity inside the front blades, and are fixed on the hub, and at the same time, the suction surface is opened along the suction surface at the end wall of the hub. The suction slots form the tandem stator blades of the supersonic adsorption compressor of the present invention.

In the same row of leaves:

The intersection point of the arc of the front row of blades and the leading edge of the front row of blades is the leading edge of the tandem blades, and the intersection of the arc of the rear row of blades and the trailing edge of the rear row of blades is the trailing edge of the tandem blades. The connecting line between the leading edge and the trailing edge obtains the total chord length of the tandem blades; the total chord length of the tandem blades is 65mm.

The axial distance between the trailing edge of the front row of blades and the leading edge of the rear row of blades is -3mm, and the circumferential offset between the trailing edge of the front row of blades and the leading edge of the rear row of blades is 4mm.

The included angle between the tangent of the center arc of the front row of blades at the leading edge point of the front row of blades and the tangent of the center arc of the rear row of blades at the trailing edge of the rear row of blades is a total bending angle, and the total bending angle is 13°.

During installation, the leading edge of the front row blades in each of the tandem stator blades is located at 5% of the axial length of the hub. The total installation angle of each of the tandem blades is 37°.

The front row of blades has a blade height of 100 mm, a blade chord length of 45 mm, an inlet geometric angle of 14°, and an outlet geometric angle of -14°. When the blades are installed on the hub, the distance between adjacent front row blades is 30.55mm, the installation angle is 47°, and the inlet airflow angle is 61°.

The convex arc surface of the front blades is the suction surface, and the concave arc surface is the pressure surface. The point of maximum thickness for this leading row of blades is at 42% of the blade chord length. The radius of the suction surface between the maximum thickness position point and the trailing edge of the front row of blades is an arc surface of 150mm; the suction surface between the maximum thickness position point and the leading edge of the front row of blades is a plane; The arc surface and the plane smoothly intersect at the point of the maximum thickness position. The pressure surface of the front row of blades adopts a circular arc surface with a radius of 170mm.

A suction cavity 4 is opened between the suction surface and the pressure surface of the front row of blades, and the suction cavity penetrates the blade along the span direction of the blade. Both ends of the suction cavity are arc-shaped, and the radius of the arc is 0.4mm. The apex of one end of the leading edge of the suction chamber is 22.4% of the chord length from the leading edge of the blade in the chord direction, and the chord length of one end of the rear leading edge of the suction chamber is 73.9% of the chord length from the leading edge of the blade in the chord direction. The profile of the upper surface of the suction cavity is the same as that of the suction surface of the blade; the profile of the lower surface of the suction cavity is the same as that of the pressure surface. The wall thickness of the suction cavity is 0.5mm.

There are suction slots 3 on the suction surface of the front blades; the suction slots are continuous suction slots or intermittent suction slots or intermittent misplaced suction slots. Said distribution along the span direction of the front row of blades. The width of each suction slit is 1.8mm, and it is connected with the suction cavity.

When the continuous suction slot is used, the suction slot is a continuous rectangular groove, and the center line in the width direction of the suction slot is located at 43% of the chord length of the front blades.

When the intermittent suction slot is used, the suction slot is composed of a plurality of single suction slots arranged along the blade span direction, and the centerline of the width direction of the suction slot is located at 43% of the chord length of the front row of blades. The length of each single suction slit is 18 mm, and the distance between adjacent edges of two suction slits is 2 mm. The single suction slots are arranged from the tip of the blade. In this embodiment, the blade height is 100 mm, and there are 5 single suction slots along the spanwise direction of the front row of blades.

When using intermittent dislocation suction slots, the suction slots are composed of a plurality of single suction slots arranged along the blade span direction, and each single suction slot is arranged alternately in two rows on the suction surface of the front row of blades, so that The center line in the width direction of one row of suction slits is located at 43% of the chord length of the front row of blades, and the center line of the width direction of the other row of suction slits is located at 45% of the chord length of the front row of blades. The length of each of the individual suction slits is 18 mm. In this embodiment, the distance between adjacent edges of two suction slots in the same column is 22 mm.

The chord length of the rear blades is 33 mm, and the blade height is 100 mm. The maximum thickness is located at 50% of the chord length of the rear row of blades, and the maximum thickness is 14mm. The convex arc surface of the rear blade is the suction surface, and the concave arc surface is the pressure surface. The suction side has a radius of 87.8mm and the pressure side has a radius of 138mm.

The hub 5 is obtained by improving the prior art. The improvement is that a plurality of front row blade end wall suction slots 10 and rear row blade end wall suction slots 11 are added or subtracted from the hub.

The suction slot on the end wall of the front row of blades is located on one side of the suction surface of the front row of blades and extends along the chord direction; the suction slot of the front row of blades is divided into a front section and a rear section, and the front section of the suction slot is a continuous suction slot , the starting point is located at 8% to 13% of the chord length from the front edge of the front blade, and the end point is located at 43% of the chord length from the front edge of the front blade; the rear suction slot is composed of a plurality of discontinuous small suction slots, And make the starting point of the rear segment suction slot be located at the chord length of 45% from the leading edge of the front row of blades, and the end point be located at the chord length of 100% from the leading edge of the front row of blades; The distance between the small suction slits is 2% of the chord length of the front row of blades; the length of each of the small suction slits is 3% of the chord length of the front row of blades.

The width of the suction slit on the end wall of the front row of blades is 1.8 mm; the distance from the centerline of the suction slit in the width direction of the end wall of the front row of blades to the suction surface of the blade is 3 mm. The shape of the suction slot on the end wall of the front row of blades is the same as the profile of the suction surface of the front row of blades. In this embodiment, the position of the suction slot on the end wall of the front row of blades is 9% to 100% of the chord length of the front row of blades.

The suction slots on the end walls of the rear blades are located on one side of the suction surface of the rear blades and extend along the chord direction. The width of the suction slots on the end walls of the rear blades is 1.8mm; the suction slots on the end walls of the rear blades The shape is the same as that of the suction surface of the rear blades. The suction slit 11 on the end wall of the trailing blade is divided into a first suction slit 12 and a second suction slit 13 . The first suction slot is divided into two sections, the suction slot in the front section is a continuous suction slot, the starting point is located at 3% of the chord length from the front edge of the rear row of blades, and the end point is located at 78% of the chord length from the front edge of the rear row of blades . The rear suction slot of the first suction slot is made up of a plurality of discontinuous small suction slots, and the starting point of the rear suction slot is located at the chord length of 80% from the leading edge of the rear row of blades, and the end point is located at 100% of the chord length from the front edge of the rear row of blades; the distance between each adjacent small suction slot in the intermittent suction slot of the rear row is 2% of the chord length of the rear row of blades; each of the small suction slots The length of the seam is 3% of the chord length of the rear row of blades. The distance from the center line in the width direction of the first suction slot to the suction surface of the blade is 6mm.

The second suction slot is also divided into two sections, the suction slot in the front section is a continuous suction slot, the starting point is located at 17% of the chord length from the front edge of the rear row of blades, and the end point is located at 78% of the chord length from the front edge of the rear row of blades strengths.

The rear suction slot of the second suction slot is made up of a plurality of discontinuous small suction slots, and the starting point of the rear suction slot is located at the chord length of 80% of the leading edge of the rear row of blades, and the end point is located at 100% of the chord length from the front edge of the rear row of blades; the distance between each adjacent small suction slot in the intermittent suction slot of the rear row is 2% of the chord length of the rear row of blades; each of the small suction slots The length of the seam is 3% of the chord length of the rear row of blades. The distance from the center line in the width direction of the second suction slit to the suction surface of the blade is 3 mm.

Claims (6)

1. A supersonic adsorption compressor tandem stator blade, comprising a plurality of front row blades and a plurality of rear row blades; a plurality of tandem stator blades are formed by each of the front row blades and rear row blades in one-to-one correspondence; It is characterized in that a suction cavity is opened between the suction surface and the pressure surface of the front row of blades, and the suction cavity penetrates the blade along the blade span direction; there is a suction slot on the suction surface of the front row of blades; The suction slots are continuous suction slots or intermittent suction slots or intermittent misplaced suction slots; the suction slots are distributed along the span direction of the front row of blades and communicate with the suction cavity; each of the suction slots The width is 1.8mm; The front row of blades is cascaded with the rear row of blades by opening suction slots on the suction surface and the suction cavity inside the front row of blades, and is fixed on the hub; multiple front row blade ends are arranged on the hub Wall suction slots and rear blade end wall suction slots; The suction slot on the end wall of the front row of blades is located on one side of the suction surface of the front row of blades and extends along the chord direction; the width of the suction slot on the end wall of the front row of blades is 1.8mm; the width of the suction slot on the end wall of the front row of blades The distance from the centerline of the direction to the blade suction surface is 3mm; the shape of the front row blade end wall suction slit is the same as the profile of the front row blade suction surface; the front row blade suction slit is divided into front section and rear section section; the suction slot in the front section is a continuous suction slot, the starting point is located at 8% to 13% of the chord length from the leading edge of the front row of blades, and the end point is located at 43% of the chord length from the front edge of the front row of blades; The suction slot is composed of a plurality of discontinuous small suction slots, and the starting point of the rear section of the suction slot is located at a chord length of 45% from the leading edge of the front blade, and the end point is located at a chord length of 100% from the front edge of the front blade. Strengths; the distance between each adjacent small suction slot in the rear section of the suction slot is 2% of the chord length of the front row of blades; the length of each of the rear section of the suction slot is the chord length of the front row of blades 3% of Install the blade root of each tandem stator blade on the outer peripheral surface of the hub of the compressor, install the tip of each tandem stator blade on the inner peripheral surface of the compressor rectifier casing, and make the front of each tandem stator blade edge towards incoming flow; In the same tandem stator blade: The intersection point of the middle arc of the front row of blades and the leading edge of the front row of blades is the leading edge of the tandem stator blades, and the intersection of the middle arc of the rear row of blades and the trailing edge of the rear row of blades is the trailing edge of the tandem blades. The connecting line between the leading edge and the trailing edge obtains the total chord length of the tandem blades; the total chord length of the tandem blades is 65mm; The axial distance between the trailing edge of the front row of blades and the leading edge of the rear row of blades is -3mm, and the circumferential offset between the trailing edge of the front row of blades and the leading edge of the rear row of blades is 4mm; The included angle between the tangent of the center arc of the front row of blades at the leading edge point of the front row of blades and the tangent of the center arc of the rear row of blades at the trailing edge of the rear row of blades is the total bending angle, and the total bending angle is 13°; When a continuous suction slot is used, the suction slot is a continuous rectangular groove, and the center line of the suction slot in the width direction is located at 43% of the chord length of the front row of blades; When intermittent suction slots are used, the suction slots are composed of a plurality of single suction slots arranged along the span direction, and the center line of the suction slot width direction is located at 43% of the chord length of the front row of blades; The length of the single suction slit is 18mm, and the distance between the adjacent edges between the two suction slits is 2mm; the single suction slit is arranged from the blade tip; When using intermittent dislocation suction slots, the suction slots are composed of a plurality of single suction slots arranged along the blade span direction, and each single suction slot is arranged alternately in two rows on the suction surface of the front row of blades, so that The center line of the width direction of one row of suction slots is located at 43% of the chord length of the front row of blades, and the center line of the width direction of the other row of suction slots is located at 45% of the chord length of the front row of blades; the length of each single suction slot is 18mm; The suction slots on the end walls of the rear blades are located on one side of the suction surface of the rear blades and extend along the chord direction. The width of the suction slots on the end walls of the rear blades is 1.8mm; the suction slots on the end walls of the rear blades The shape is the same as that of the suction surface of the rear row of blades; the suction slot on the end wall of the rear row of blades is divided into a first suction slot and a second suction slot; The first suction slot is divided into a front section and a rear section; the front section of the first suction slot is a continuous suction slot, the starting point is located at 3% of the chord length from the leading edge of the rear row of blades, and the end point is located at a distance from the rear row of blades. 78% of the chord length of the leading edge; the rear section of the first suction slot is composed of a plurality of discontinuous small suction slots, and the starting point of the rear section is located at 80% of the chord length from the leading edge of the rear row of blades, and the end point is Located at 100% of the chord length from the leading edge of the rear row of blades; the distance from the centerline in the width direction of the first suction slot to the suction surface of the blade is 6mm; The second suction slot is also divided into a front section and a rear section; the front section of the first suction slot is a continuous suction slot, the starting point is located at 17% of the chord length from the leading edge of the rear row of blades, and the end point is located at a distance from the rear row of blades. 78% of the chord length of the leading edge; the rear section of the second suction slot is composed of a plurality of discontinuous small suction slots, and the starting point of the rear section is located at 80% of the chord length from the leading edge of the rear row of blades, and the end point is Located at 100% of the chord length from the leading edge of the rear row of blades; the distance from the centerline in the width direction of the second suction slot to the suction surface of the blade is 3mm; Among the small suction slots in the rear section of the first suction slot and in the small suction slots in the rear section of the second suction slot, the distance between adjacent small suction slots is 2 times the chord length of the rear blades. %; the length of each small suction slot is 3% of the chord length of the rear row of blades. 2. The tandem stator blades of a supersonic adsorption compressor according to claim 1, wherein the suction cavity is located at the vertex at one end of the leading edge and is 22.4% from the chord length of the blade leading edge in the chord direction, and the suction cavity The apex at one end of the trailing edge is 73.9% of the chord length from the leading edge of the blade in the chord direction; the profile of the upper surface of the suction cavity is the same as that of the suction surface of the blade; the profile of the lower surface of the suction cavity is the same as the profile of the blade The profiles of the pressure surfaces are the same; both ends of the suction chamber are arcs with a radius of 0.4mm; the wall thickness of the suction chamber is 0.5mm. 3. The supersonic adsorption compressor tandem stator blades as claimed in claim 1, characterized in that: when installed, the leading edge of the front row blades in each of the tandem stator blades is located at 5% of the axial length of the hub; The total installation angle of each of the tandem stator blades is 37°. 4. supersonic adsorption type compressor tandem stator blades as claimed in claim 1, characterized in that: the blade height of the front blades is 100mm, the blade chord length is 45mm, the inlet geometric angle is 14°, and the outlet geometric angle is -14°; when the blades are installed on the hub, the distance between adjacent front row blades is 30.55mm, the installation angle is 47°, and the inlet airflow angle is 61°. 5. The supersonic adsorption compressor tandem stator blades as claimed in claim 1, characterized in that: the convex arc surface of the front row blades is the suction surface, and the concave arc surface is the pressure surface; the maximum thickness position of the front row blades The point is located at 42% of the chord length of the blade; the radius of the suction surface between the maximum thickness point and the trailing edge of the front row of blades is an arc surface of 150mm; the distance between the maximum thickness point and the front edge of the front row of blades The suction surface between them is a plane; the circular arc surface and the plane intersect smoothly at the point of the maximum thickness; the pressure surface of the front row of blades adopts an arc surface with a radius of 170mm. 6. The supersonic adsorption compressor tandem stator blades as claimed in claim 1, characterized in that: the chord length of the rear blades is 33 mm, and the blade height is 100 mm; the maximum thickness is located at 50% of the chord length of the rear blades The maximum thickness is 14mm; the convex arc surface of the rear blade is the suction surface, and the concave arc surface is the pressure surface; the radius of the suction surface is 87.8mm, and the radius of the pressure surface is 138mm.

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