CN111622963A - Gas compressor based on impact type rotor-rotary stamping stator - Google Patents

Abstract

A compressor based on an impact rotor-rotating stamping stator, the hub is located in the casing. The impingement rotor blade row is composed of a plurality of impingement rotor blades on the side surface of the hub. Each partition is located at one end of the air outlet of the casing. An airflow compression block is fixed between each of the two baffles that are overlapped and staggered end to end. The stator in the present invention uses the inner surface of the hub and the casing as its aerodynamic surface, and divides the airflow through the partition plate. A row of impingement rotors and a row of rotating stamping stators constitute the first stage of the ultra-high pressure ratio compressor based on impingement rotors and rotating stamping stators. The invention takes advantage of the adaptability of the rotary stamping stator to the high Mach number of the incoming flow, decelerates and diffuses the high Mach number of the air flow at the outlet of the impact rotor, forms a shock wave system of the supersonic air inlet in the air intake direction, and utilizes multiple channels. The shock wave structure decelerates and expands, which can greatly improve the aerodynamic performance of the stator.

Description

Compressor Based on Impact Rotor-Rotating Stamping Stator

technical field

The invention relates to the field of compressors, in particular to an ultra-high pressure ratio compressor based on an impact rotor and a rotary stamping stator.

Background technique

Axial flow compressor is a kind of machinery that uses high-speed rotating blades to do work on the gas to increase the gas pressure. It is widely used in aero-engines, gas turbines and missiles.

Modern aircraft design requires continuous improvement of the thrust-to-weight ratio of aero-engines. The multi-stage axial compressor occupies about 50% of the space of the aero-engine in the axial length. Therefore, reducing the number of stages of the multi-stage compressor is important for improving the thrust-to-weight ratio of the aero-engine. important meaning. On the premise that the total pressure ratio of the multi-stage axial compressor remains unchanged, reducing the number of compressor stages means that the single-stage pressure ratio (or "stage pressure ratio") of the compressor needs to be greatly increased. Therefore, under the premise of ensuring that the compressor efficiency and stability margin are not reduced, gradually increasing the stage pressure ratio of the compressor is the goal pursued by modern aero-engine designers.

The stage pressure ratio of subsonic axial flow compressors is about 1.3 or less. With the development of modern compressor full three-dimensional aerodynamic design system, the emergence of supertransonic compressors makes high pressure ratio axial flow compressors possible. Among them, NASA designed and tested a series of high-pressure ratio transonic unipolar axial flow compressors of Stages35-38 in the last century. The design stage pressure ratio of Stages35 and Stages37 is 2.05, the design stage pressure ratio of Stages36 and Stages38 is 1.82, and the design stage pressure ratio of Stages37 is 1.82. The rotor experimental efficiency is 84.2%. The domestically designed ATS-2 unipolar transonic compressor has a pressure ratio of 2.2 and a stage efficiency of 86.8%. However, with the pursuit of higher thrust-to-weight ratios in aero-engines, the stage pressure ratio of axial flow compressors will be further improved, and the design of axial flow compressors with higher stage pressure ratios poses greater challenges for researchers.

Weise and Kantrowitz designed supersonic compressors in 1943 and 1946, respectively. In order to obtain ultra-high loads, research on impingement compressors has not stopped. Klapproth designed the world's first impingement supersonic compressor. Its characteristics are that the relative velocity of the inlet and outlet airflow of the rotor is supersonic, the turning angle of the airflow in the rotor is large, but the overall increase in static pressure is small, and the work of increasing the static pressure is completed in the stator. In supersonic fluid, due to the weak disturbance in the downstream, it cannot be transmitted to the upstream. The flow-pressure ratio curve of the compressor is constant under this working condition (supersonic) and has nothing to do with the back pressure. The efficiency of the Klapproth compressor is high, up to 89%, but under the condition of 96% of its design speed, its stator loss is very large, so that its efficiency is only 63% to 66% under the condition of high pressure ratio. Supersonic compressors are used as a long-term research project at the Von Kármán Institute of Fluid Mechanics (VKI) in Europe and the Institute for Turbojet Propulsion at the University of Aachen (RWTH Aachen) in Germany.

The rotary ram compressor was first proposed by the American Ramgen Power Systems Company. The structure of the ram rotor used is that a series of small-angle binary supersonic inlets are placed on the edge of the rotor, so that when the supersonic airflow enters the inlet. , the airflow will be continuously compressed, thereby greatly improving the single-stage compression ratio. As a new type of supersonic compressor, it can use shock waves to achieve intermittent and efficient compression of airflow, and has the advantages of compact structure, light weight, and high pressure ratio. Due to the complex flow phenomena such as shock-shock and shock-boundary interference in the internal flow field of the compression process, flow loss and compressor performance degradation will be caused. Reducing losses and improving compressor performance are the current research directions.

In April 2002, after a review of the rotary ram-compression technology by experts from the U.S. Department of Energy, the Department of Defense, the National Aeronautics and Space Administration, and Ramgen Power Systems, after comprehensive consideration of technical issues, time and economic costs, it was unanimously decided to adopt a rotary ramjet gas turbine. To replace conventional compressors, and make it a key development direction in the future.

In the invention and creation of patent number CN105626579A, a stamping and compression rotor is proposed, which is characterized in that a plurality of spiral partitions are evenly distributed on the outer wall of the wheel disc assembly, and the gap between two adjacent partition plates forms a In the intake flow channel, each intake flow channel is provided with an airflow compression section, a throat isolation section and a triangular outlet extension section from the inlet section to the outlet section. After the supersonic airflow enters the intake flow channel, the rotor can compress the seven-six through the multiple oblique shock waves generated by the compression section to obtain a higher pressure ratio. However, in order to make the air flow at the intake air supersonic, continuous high-speed rotation of the rotor is required to achieve this condition, which increases the power consumption of the compressor.

Xiao Xiang, Institute of Engineering Thermophysics, Chinese Academy of Sciences, in the article "Analysis and Research on the Internal Flow of the Stamping Impeller of the Contra-rotating Ram Compressor", proposed a structural scheme of the counter-rotating ram compressor. By using two-stage counter-rotating blades in the compressor, the The total boost ratio is above 10. In practice, the disadvantages of the rotary ram compressor are also obvious: the airflow flow is small, and the axial support of the compressor is required to be high. A series of problems make it unable to be applied well in aero-engines with large flow.

The current common compressor rotor needs to work at a high speed, so its allowable flow rate is generally not too high; and the design of the stator currently has serious flow separation and low overall efficiency.

Associate Professor Cao Zhiyuan from Northwestern Polytechnical University proposed a counter-axial compressor in his dissertation "Research on the Influence of Boundary Layer Suction on the Flow Control and Performance of Axial Compressors" and an invention patent (patent number CN103967812B). The front end of the impact rotor blade used is a pre-compressed blade shape, and the camber is mainly concentrated in the second half, and the camber of each section is above 90°. The design of the rotor improves the working capacity of the rotor while ensuring high efficiency. However, the rotor used in the above-mentioned compressor has little effect of increasing the pressure of the airflow, and lacks a stator that can greatly increase the airflow pressure to improve the efficiency of the compressor.

SUMMARY OF THE INVENTION

In order to overcome the steps in the prior art that the pressure boosting effect on the airflow is small, the compressor efficiency is low, and the stator flow separation is serious, the present invention proposes a compressor based on an impact rotor-rotating stamping stator.

The invention comprises a casing, a wheel hub, an impact rotor blade, a baffle, and an airflow compression block. The hub is located in the casing. A plurality of impingement rotor blades are circumferentially arranged on the side surface of the hub to form an impingement rotor blade row. When arranging, the blade bottom surface of each impingement rotor blade is fixed on the hub, and the leading edge of each impingement rotor blade is located in the direction of the air inlet of the casing. There is a distance of 5 mm between the tip of each of the impingement rotor blades and the inner surface of the casing, and the distance between the adjacent surfaces of two adjacent impingement rotor blades is 59.37 mm.

There are three partitions, which are semi-circular arc-shaped arc slats. The baffles are all located at one end of the air outlet of the casing, and the inner arc surface of each baffle is fixed on the outer circumferential surface of the hub, so that the outer arc surface of each baffle is connected to the casing at its location. The inner circumferential surface is fixed. When arranging each of the partitions, the two ends of each partition are not on the same vertical plane, so that there is an included angle of 27.6° between the space connecting line between the two ends of each partition and the vertical surface; the vertical surface parallel to the end face of the hub. When arranging, the head and tail of the three partitions are overlapped and staggered; the arc length of the overlapping and staggered between the head and tail of each partition is 1/3 of the arc length in the partition.

There is an airflow compressing block between the two overlapping baffles, the airflow compressing block is fixed on the outer circumferential surface of the wheel hub, and the two sides of the airflow compressing block are respectively connected to the adjacent two The side surfaces of the head or tail of the partition are fastened. The rotary stamping stator of the compressor is constituted by the baffle and the airflow compression block. The impingement rotor blade row and the rotary stamping stator are arranged in parallel on the hub in turn.

The impingement rotor blades are arc-shaped plates. The surface of the impingement rotor blade adjacent to the surface of the casing is the top surface of the blade, and the surface matched with the outer surface of the hub is the bottom surface of the blade. The intersection of the leading edge of the impingement rotor blade and the top surface of the blade is called the top leading edge point, and the intersection of the trailing edge and the top surface of the blade is called the top trailing edge point; the intersection of the leading edge of the impingement rotor blade and the bottom surface of the blade is called is the bottom front edge point. The distance between the top leading edge points of two adjacent impingement rotor blades is 59.37 mm.

From the leading edge to the trailing edge of the top surface of the blade, a curve is drawn through the top surface of the blade, and the curve is the mid-arc of the top surface; the mid-arc of the top surface is located at 1/2 of the thickness of the blade. The straight line obtained by connecting the two endpoints of the arc in the top surface is the chord length of the top surface of the impingement rotor blade; the tangent to the arc is made at the two endpoints of the arc in the top surface, respectively, and the leading edge of the top is obtained. Tangent and top trailing edge tangent.

, the convex surface of the impact rotor blade is a suction surface, and the suction surface is composed of 3 segments of circular arc profiles; each of the circular arcs is tangent at the connection. Make note of the connecting line between the boundary point at the relative chord length x=0.5 of the suction surface and the chord length of the top surface, and make the connecting line perpendicular to the chord length of the top surface; the length of the connecting line is y ₁ ; y ₁ It is equal to 1/3 of the chord length of the top surface; the starting point of the first arc segment of the suction surface is the leading edge point, and the end point is the first dividing point, which is located at the relative chord length x _E = 0.21, y _E =0.5y ₁ place. The starting point of the second arc segment of the suction surface is the first dividing point, and the end point is the second dividing point, and the second dividing point is located at the relative chord length x _F =0.6, y _F =1.05y ₁ . The starting point of the third circular arc segment on the suction surface is the second dividing point, and the ending point is the trailing edge point.

The concave surface of the impingement rotor blade is the pressure surface, and the distance from the boundary point of the pressure surface relative to the chord length x=0.5 to the chord length of the top surface is y ₂ , and y ₂ is equal to 1/4 of the chord length of the top surface; The starting point of the airfoil is the leading edge point, and the end point is the third dividing point, which is located at the relative chord length x _G = 0.2, y _G = 0.5y ₂ ; the starting point of the rear airfoil is the third dividing point , the end point is the trailing edge point. The pressure surface of the front airfoil is made into a concave shape to reduce the Mach number of the wave front and reduce the shock wave loss. This airfoil is called a precompression airfoil, and the precompression degree of the airfoil is the largest at the relative chord length x _G = 0.2; The rear section of the pressure surface consists of three tangent arcs.

The functional relationship between y and x of the pre-compression airfoil in the front section is:

y=-0.0004x ² -0.6128x+0.5y ₂

The starting point of the first arc segment of the pressure surface of the rear arc profile is the third dividing point, and the end point is the fourth dividing point. The fourth dividing point is located at the relative chord length x _H = 0.43, y _H = 0.8y ₂ ; The starting point of the second arc segment of the pressure surface is the fourth dividing point, and the end point is the fifth dividing point, and the fifth dividing point is at = at the relative chord length x _I = 0.8, y _I = 0.85y ₂ ; pressure The starting point of the third circular arc segment of the surface is the fifth dividing point, and the ending point is the trailing edge point.

The suction surface and the pressure surface of the impact rotor blade are connected by an arc at the intersection of the leading edge, and the curvature radius of the arc is 0.1% to 3% of the chord length; the suction surface and the pressure surface of the impact rotor blade are at the trailing edge. The intersections are connected by an arc, and the radius of curvature of the arc is 0.1% to 3% of the chord length;

The connection line between the leading edge points of the impingement rotor blades distributed on the circumference of the hub is the top front edge frontal line; the connection line between the trailing edge points of the impingement rotor blades distributed on the circumference of the hub is called the top The frontal line of the front edge of the face; the acute angle formed by the frontal line of the front edge of the top surface and the tangent of the front edge of the top surface is the entrance angle α of the top surface geometry; the acute angle formed by the frontal line of the front edge of the top surface and the tangent of the rear edge of the top surface is the top surface geometry Exit angle β. The angle obtained by the intersection of the tangent of the front edge of the top and the tangent of the rear edge of the top is the top bend.

The line connecting the leading edge points of the impingement rotor blades distributed on the circumference of the hub is called the bottom leading edge front line. The included angle between the chord length of the bottom surface and the forehead line of the bottom front edge is the blade root installation angle γ; the installation angle γ of the blade root of each impact rotor blade is 65.9°.

There are 3 air compressing blocks. The lower surface of the airflow compression block is an arc surface that fits with the outer surface of the wheel hub, the surfaces on both sides are flat surfaces that are attached to the partition, and the upper surface is arc-shaped and processed into seven sections of slopes with different inclinations. Compress the airflow entering the rotary stamping stator and do work; the upper surface is divided into an ascending section and a descending section, wherein the surface of the ascending section is processed into four sections of inclined planes that connect with each other, and the surface of the descending section is processed into three sections that connect with each other the slope. The ascending section is the air inlet, and the descending section is the air outlet. In this ascending section, the included angle θ ₁ between the first inclined plane at the airflow inlet and the horizontal plane is 63.6°, and the included angle θ ₂ between the second inclined plane and the horizontal plane is one-half of θ ₁ . The included angle θ ₃ between the three-stage inclined plane and the horizontal plane is one-half of θ ₂ , and the included angle θ ₄ between the fourth-stage inclined plane and the horizontal plane is one-half of θ ₃ . The angles between the slopes of each section of the descending section and the horizontal plane are all located below the horizontal plane, so that the slopes of each section are in a downward trend. The included angle θ ₅ =θ ₄ ; the sixth-slope slope is connected to the fifth-slope slope, and the included angle between the sixth-slope slope and the horizontal plane is θ ₆ =2θ ₅ ; the seventh-slope slope is connected to the The six slopes are connected, and the angle between the seventh slope and the horizontal plane is θ ₇ =2θ ₆ .

In order to achieve a higher incoming Mach number, improve the stage pressure ratio, and solve the design difficulties of serious stator flow separation and extremely low overall efficiency of the ram compressor, the invention proposes a high pressure ratio adsorption compressor.

In the present invention, the compressor has an impact rotor and a rotary stamping stator in sequence from the inlet to the outlet. The impact rotor is located in the casing and fixed on the circumferential surface of the hub; behind the impact rotor blade is a rotary stamping stator, which is installed in the same way as the rotor and fixed on the circumferential surface of the rotating shaft. This kind of stator is different from the traditional vane-type stator. Its working mode no longer uses the suction surface and pressure surface of the "blade" as the aerodynamic surface, but uses the inner surface of the hub and the casing as its aerodynamic surface. The plate is only what it needs to divide the airflow. A row of impingement rotors and a row of rotating stamping stators constitute the first stage of the ultra-high pressure ratio compressor based on impingement rotors and rotating stamping stators.

The impact rotor 3 includes 27 blades, which are evenly distributed on the hub along the circumferential direction, the installation angle of the rotor blade root is 65.9°, the chord length of different blade heights is about 120mm, and the inlet geometric angle is 40.18 °, the outlet geometry angle is 12.71°. In order to adapt to the airflow direction, the rotor blades adopt streamlined blades with large bending angles, and the turning angle of the rotor blades from the air inlet to the air outlet is greater than 90° from the blade root to the blade tip. On the premise that the total bending angle is greater than 90°, the chord length of the blade is widened, so that the turning angle of each blade is smaller, so that the entire channel is streamlined, making it difficult to block the airflow and reducing flow loss. The impulsive force of the impingement rotor mainly comes from the impact force of the airflow on the blades, and the rotor rotates to pressurize the airflow. When there is no passage, the airflow velocity is still supersonic. At this time, the inlet Mach number is about 1.2, which is different from the conventional compressor, and because the angle between the inlet airflow and the axial direction of the rear stator is large, the inlet airflow angles of different blade spans are all 60. Around °, curved blades are used to control the secondary flow of airflow at the blade wall at the end face of the blade.

The rotary stamping stator is fixed on the side surface of the wheel hub with three partitions whose arc length is half of the circumference of the top surface of the wheel hub and spans the side surface. Viewed from the axial direction, the overlapping portion of every two baffles is 1/3 of its arc length. On the rim of the overlapping part of the two partitions, there are several stepped air flow channels similar to the binary supersonic intake channel placed at a small angle. The partition is used as the wall surface of the intake channel. Shizuo's air intake. The steps in the first half of the passage show an upward trend, and the angle between the inclined surface and the wheel rim gradually decreases; the second half is a downward trend, and the angle between the inclined surface and the wheel rim also gradually decreases. Its working principle is that in the first half, the airflow is compressed in the stepped channel, so that the airflow velocity continues to rise, reaching Mach number 1 at the top; in the second half, the airflow velocity reaches supersonic speed at this time, due to the continuous expansion of the cross-section of the intake duct. , the airflow velocity continues to increase. In the channel, an intake channel similar to a Rafael nozzle will be formed, which is used to compress the airflow and increase the energy of the airflow.

In order to ensure high efficiency and improve the supercharging ratio of the rotor at the same time, the rotor of the axial flow compressor of the present invention adopts a large bending angle impact rotor; The ratio can be as high as 5.7, while the conventional transonic rotor is only about 2.0; the impact design makes the airflow in the rotor less diffused, that is, the diffuser load is low, so although the rotor has a large turning angle, it can still maintain a high level. efficiency, its efficiency can reach 87%.

Taking advantage of the adaptability of the rotating ram-type stator to the high Mach number of the incoming flow, it decelerates and diffuses the high-flow Mach number at the outlet of the impinging rotor; this type of stator places the airflow similar to the type of the intake port in the intake direction. In the compression section, a shock wave system similar to the supersonic inlet port is formed in turn, and the multi-channel shock wave structure is used for deceleration and diffusion, which can greatly improve the aerodynamic performance of the stator compared with the conventional vane stator. It is proved that the total pressure loss of the airflow after passing through the shock wave system is much smaller than the total pressure loss of only one normal shock wave, which means that when the total turning angle of the airflow is the same, the oblique flow through The more shock waves, the smaller the total pressure loss of the airflow.

Description of drawings

1 is a three-dimensional view of the present invention viewed from the direction of intake air;

Fig. 2 is the three-dimensional view of the present invention observed from the air outlet direction;

3 is an axial two-dimensional cross-sectional view of the present invention;

Figure 4 is a three-dimensional view of the assembly of the impact rotor-rotating stamping stator

Figure 5 is a side view of the impact rotor-rotating stamping stator;

Fig. 6 is the assembly drawing of the impact rotor-rotating stamping stator viewed from the air intake direction;

Fig. 7 is the assembly drawing of the impact rotor-rotating stamping stator viewed from the air outlet direction;

8 is a three-dimensional view of an impingement rotor blade;

9 is a top view of an impingement rotor blade;

Figure 10 is a cross-sectional view of the top of an impingement rotor blade;

Figure 11 is a cross-sectional view of the bottom of an impingement rotor blade;

12 is a schematic diagram of the geometric inlet angle and geometric outlet angle of the top surface of the impingement rotor blade;

Figure 13 is a schematic view of the mounting angle of the impingement rotor blade.

Figure 14 is a three-dimensional view of an airflow compression block;

Figure 15 is a cross-sectional view of an airflow compression block;

Figure 16 is a sectional view of a rotary stamping stator airflow channel;

FIG. 17 is a schematic diagram of a shock wave formed by a rotating punching stator airflow channel.

Figure 18 is a schematic diagram of the airfoil demarcation point of an impingement rotor blade

In the figure: 1. Case; 2. Hub; 3. Impact rotor blade; 4. Baffle plate; 5. Airflow compression block; 6. Top surface of blade; 7. Bottom surface of blade; .Top chord length; 10. Top front edge tangent; 11. Top rear edge tangent; 12. Top surface corner; 13. Bottom surface mid-arc; 14. Bottom surface chord; 15. Bottom front edge tangent; 16. 17. Bottom edge tangent; 18. Rising slope; 19. Descending slope; 20. Top front edge forehead line; 21. Front edge; 22. Trailing edge; Front margin frontal line; A. Top trailing margin point; B. Top leading margin point; C. Bottom trailing margin point; D. Bottom leading margin point; E. First demarcation point; F. Second demarcation point; G. Third dividing point; H. Fourth dividing point; I. Fifth dividing point; α. Geometric inlet angle; β. Geometric outlet angle; γ. Installation angle.

Detailed ways

This embodiment is a compressor based on an impact rotor-rotating stamping stator, including a casing 1 , a hub 2 , an impact rotor blade 3 , a baffle 4 , and an airflow compression block 5 . The hub 2 is located in the casing 1 . A plurality of impingement rotor blades 3 are circumferentially arranged on the side surface of the hub 2 to form an impingement rotor blade row. When arranging, the blade bottom surface 7 of each impingement rotor blade is fixed on the hub, and the leading edge of each impingement rotor blade is located in the direction of the air inlet of the casing 1 . There is a distance of 5 mm between the top end of each impact rotor blade 3 and the inner surface of the casing 1, and the distance between the adjacent surfaces of two adjacent impact rotor blades is 59.37 mm.

There are three partitions 4, which are semi-circular arc-shaped arc-shaped slats. The baffles are located at one end of the air outlet of the casing 1, and the inner arc surface of each baffle is fixed on the outer circumferential surface of the hub, so that the outer arc surface of each baffle is in line with the machine at its location. The inner circumferential surface of the box is fixed. When arranging each of the partitions 4, the two ends of each partition 4 are not on the same vertical plane, so that the space connecting line between the two ends of each partition and the vertical surface have an included angle of 27.6°; the The vertical plane is parallel to the end face of the hub 2 . When arranging, the head and tail of the three partitions 4 are overlapped and staggered; In this embodiment, the inner arc length of the partition plate is 725mm, and the arc length of the overlapping and staggered two adjacent partition plates is 242mm.

There is an airflow compressing block 5 between the two baffles that are overlapped and staggered at each end. The airflow compressing block 5 is fixed on the outer circumferential surface of the hub 2, and the two sides of the airflow compressing block 5 are respectively aligned with the opposite sides. The side surfaces of the head or tail of the two adjacent partitions are fixedly connected. The baffle and the airflow compression block 5 constitute the rotary stamping stator of the compressor. The impingement rotor blade row and the rotary stamping stator are sequentially arranged on the hub 2 in parallel.

The impact rotor blade 3 is an arc-shaped plate. The surface of the impingement rotor blade 3 adjacent to the casing surface is the blade top surface 6 , and the surface matching with the outer surface of the hub 2 is the blade bottom surface 7 . The intersection of the leading edge of the impingement rotor blade 3 and the blade top surface 6 is called the top leading edge point B, and the intersection point of the trailing edge and the blade top surface 6 is called the top trailing edge point A; the leading edge of the impingement rotor blade 3 The point of intersection with the blade bottom surface 7 is called the bottom leading edge point C. The distance between the top leading edge points B of two adjacent impingement rotor blades is 59.37 mm.

From the leading edge of the top surface to the trailing edge, a curve is drawn through the top surface 6 of the blade, and this curve is the middle arc line 8 of the top surface; the middle arc line of the top surface is located at 1/2 of the thickness of the blade. The straight line obtained by connecting the two end points of the arc line 8 in the top surface is the top surface chord length 9 of the impingement rotor blade 3; The top leading edge tangent 10 and the top trailing edge tangent 11 are obtained.

The connection line between the leading edge points C of the impingement rotor blades 3 distributed on the circumference of the hub 2 is the top front front edge line 20; the line between the trailing edge points A of the impingement rotor blades 3 distributed on the circumference of the hub 2 The connection line between them is called the forehead line 23 of the rear edge of the top surface; the acute angle formed by the forehead line 20 of the front edge of the top surface and the tangent line 10 of the front edge of the top surface is the geometric inlet angle α of the top surface; The acute angle formed by the edge tangent line 11 is the geometric exit angle β of the top surface. The angle obtained by the intersection of the top front edge tangent 10 and the top rear edge tangent 11 is the top curved angle 12 .

In this embodiment, the top chord 9 of the impingement rotor blade has a length of 120.48mm, the bottom chord 14 has a length of 115.39mm, and the distance between the blade top 6 and the blade bottom 7 is 54.18mm.

The distance from each point that constitutes the boundary of the top surface of the impingement rotor blade to the top chord 9 is recorded as y, and the projection of each point on the top chord to the leading edge point B is recorded as the percentage of the top chord as relative. Chord length x. The relative chord lengths of each demarcation point are recorded as x _E , x _F , x _G , x _H , x _I ; the distances from each demarcation point to the top chord length 9 are denoted as y _E , y _F , y _G , y _H , y _I.

The convex surface of the impingement rotor blade is the suction surface, which adopts a circular arc profile, and has a total of 3 arcs; each of the arcs is tangent at the connection. Make note of the connection line between the boundary point at the relative chord length x=0.5 of the suction surface and the chord length 9 of the top surface, and make the connection line perpendicular to the chord length of the top surface; the length of the connection line is y ₁ ; y ₁ is equal to 1/3 of the chord length of the top surface; the starting point of the first arc segment of the suction surface is the leading edge point B, and the end point is the first dividing point E, which is located at the relative chord length x _E = 0.21, where y _E = 0.5y ₁ . The starting point of the second arc segment of the suction surface is the dividing point E, and the end point is the second dividing point F, and the second dividing point F is located at the relative chord length x _F =0.6, y _F =1.05y ₁ . The starting point of the third arc segment of the suction surface is the second dividing point F, and the ending point is the trailing edge point A.

In this embodiment, the radius of curvature of the first arc segment is infinite, that is, the first arc segment of the suction surface is a straight line, the radius of curvature of the second arc segment of the suction surface is 408.9 mm, and the third arc segment of the suction surface is 408.9 mm. The radius of curvature of the arc segment is 140mm.

The concave surface of the impingement rotor blade is the pressure surface, and the distance from the boundary point of the pressure surface relative to the chord length x=0.5 to the top surface chord length 9 is y ₂ , and y ₂ is equal to 1/4 of the top surface chord length; The starting point of the airfoil is the leading edge point B, and the end point is the third dividing point G, which is located at the relative chord length x _G = 0.2, y _G = 0.5y ₂ ; the starting point of the rear airfoil is the The third demarcation point G, the end point is the trailing edge point A. The pressure surface of the front airfoil is made into a concave shape to reduce the Mach number of the wave front and reduce the shock wave loss. This airfoil is called a precompression airfoil, and the precompression degree of the airfoil is the largest at the relative chord length x _G = 0.2; The rear section of the pressure surface adopts a circular arc surface, which is composed of three tangent arcs.

The functional relationship between y and x of the pre-compression airfoil in the front section is:

y=-0.0004x ² -0.6128x+0.5y ₂

The starting point of the first arc segment of the pressure surface of the rear arc profile is the dividing point G, and the end point is the fourth dividing point H; the fourth dividing point H is located at the relative chord length x _H = 0.43, y _H = 0.8y ₂ The starting point of the second arc segment of the pressure surface is the fourth boundary point H, and the end point is the fifth boundary point I, the fifth boundary point I is at = located at the relative chord length x _I = 0.8, y _I = 0.85y ₂ The starting point of the third arc segment on the pressure surface is the boundary point I, and the end point is the trailing edge point A.

In this embodiment, the radius of curvature of the first arc segment of the pressure surface is 356.4 mm, the radius of curvature of the second arc segment of the pressure surface is 204.5 mm, and the radius of curvature of the third arc segment of the pressure surface is 140 mm.

The suction surface and the pressure surface of the impact rotor blade are connected by an arc at the intersection of the leading edge, and the curvature radius of the arc is 0.1% to 3% of the chord length; the suction surface and the pressure surface of the impact rotor blade are at the trailing edge. The intersections are connected by an arc, and the radius of curvature of the arc is 0.1% to 3% of the chord length;

The line connecting the leading edge points B of the impingement rotor blades 3 distributed on the circumference of the hub 2 is called the bottom leading edge front line 24 . The included angle between the bottom surface chord 14 and the bottom front edge frontal line 24 is the blade root installation angle γ; the installation angle γ of the blade root of each impact rotor blade 3 is 65.9°. In this embodiment, the length of the top chord 9 is 120.48 mm, and the length of the bottom chord 14 is 115.39 mm. The geometric inlet angle α is 42°, and the geometric outlet angle β is 63°.

In order to adapt to the airflow direction, the impingement rotor blade 3 adopts a streamlined blade with a large bending angle, that is, the bending angle is greater than 90°. In this embodiment, the top surface bending angle 12 of the impingement rotor blade 3 is 94.5°, and the bottom surface bending angle 17 is 100.6°. The impingement rotor blades 3 use wide chord blades. The wide chord blade makes the entire airflow channel between the two adjacent blades streamlined, making the airflow less likely to be blocked when flowing, and reducing flow loss at the same time.

There are 3 air compressing blocks 5 in block shape. The lower surface of the airflow compressing block 5 is an arc surface that fits with the outer surface of the hub 2 , the surfaces on both sides are flat surfaces that fit the partition plate 4 , and the upper surface is arc-shaped and processed into seven sections with different inclinations The inclined plane of the slanting surface compresses the airflow entering the rotary stamping stator; the upper surface is divided into an ascending section 21 and a descending section 22, wherein the surface of the ascending section is processed into four mutually connected slopes, and the surface of the descending section is processed into three connected slopes. The ascending section is the air inlet, and the descending section is the air outlet. In this ascending section, the included angle θ ₁ between the first inclined plane at the airflow inlet and the horizontal plane is 63.6°, and the included angle θ ₂ between the second inclined plane and the horizontal plane is one-half of θ ₁ . The included angle θ ₃ between the three-stage inclined plane and the horizontal plane is one-half of θ ₂ , and the included angle θ ₄ between the fourth-stage inclined plane and the horizontal plane is one-half of θ ₃ . The angles between the slopes of each section of the descending section and the horizontal plane are all located below the horizontal plane, so that the slopes of each section are in a downward trend. The included angle θ ₅ =θ ₄ ; the sixth-slope slope is connected to the fifth-slope slope, and the included angle between the sixth-slope slope and the horizontal plane is θ ₆ =2θ ₅ ; the seventh-slope slope is connected to the The six slopes are connected, and the angle between the seventh slope and the horizontal plane is θ ₇ =2θ ₆ . In this embodiment, θ ₁ =63.6°, θ ₂ =36.75°, θ ₃ =18.36°, θ ₄ =9.18°, θ ₅ =−9.18°, θ ₆ =−18.36°, and θ ₇ =−36.72°.

The projected lengths of the inclined plane sections in the ascending section 21 in the circumferential direction of the hub 2 are the same, which are 29.42 mm in this embodiment; the projected lengths of the inclined plane sections in the descending section 22 in the circumferential direction of the hub 2 are the same, in this embodiment Both are 26.33mm.

The working principle of the airflow compression block 5 The airflow is to decelerate and pressurize the incoming flow by a series of shock waves formed by the shape of the airflow compression block 5 after entering the rotating stamping stator. This shape forms an air intake channel similar to a Rafael nozzle in the channel, which is used to compress the airflow and increase the energy of the airflow.

The casing 1 is a casing, the inner surface of which is connected with the partition plate 4. In this embodiment, the circumferential diameter of the end face of the impact rotor side is 462.04 mm, and the circumferential diameter of the end face of the rotary stamping stator side is 458.04 mm.

The rotary stamping stator in this embodiment is different from the traditional vane-type stator. Its action mode no longer uses the suction and pressure surfaces of the “blade” as the aerodynamic surfaces, but the outer circumferential surface of the hub 2 and the casing 1. The inner surface is used as its aerodynamic surface, and the baffle 6 fixed on the surface of the hub 2 is only a device required for dividing the airflow, and the shape of the airflow compression block 5 is used to complete the compression work on the airflow. Each row of impingement rotor blades and rotating ram stators constitute a stage of the compressor, and the ultra-high pressure ratio compressor based on impingement rotor-rotating ram stators is composed of many such stages with hub 2 and casing 1 .

The driving force of the rotor used in the compressor mainly comes from the impact force of the airflow on the impinging rotor blades, which makes the impinging rotor rotate to pressurize the airflow. The working principle is that when the airflow enters the adjacent two impinging rotor blades When the guide vane-to-blade channel is formed between 3 and 3, the airflow velocity is still supersonic. At this time, the inlet Mach number is 1.2, which is different from the conventional gas turbine, and the angle between the outlet airflow and the axial direction of the rotating stamping stator is 60°. Between 70°, curved blades are used to control the secondary flow of airflow at the blade wall at the end face of the blade.

Claims (7)

1. A compressor based on an impact rotor-rotating stamping stator, characterized in that it comprises a casing, a hub, an impact rotor blade, a baffle, and an airflow compression block; the hub is located in the casing; The impingement rotor blades are circumferentially arranged on the side surface of the hub to form an impingement rotor blade row; when arranging, the blade bottom surface of each impingement rotor blade is fixed on the hub, and each impingement rotor blade is The leading edge is located in the direction of the air inlet of the casing; there is a 5mm distance between the top of each impingement rotor blade and the inner surface of the casing, and the phase between the adjacent two impingement rotor blades is The spacing between adjacent surfaces is 59.37mm; There are three partitions, which are semi-circular arc-shaped arc-shaped slats; the partitions are all located at one end of the air outlet of the casing, and the inner arc surface of each partition is fixed on the outer circumferential surface of the hub , so that the outer arc surface of each partition is fixedly connected with the inner circumferential surface of the casing at its location; when arranging each of the partitions, the two ends of each partition are not on the same vertical plane, so that the two ends of each partition are There is an included angle of 27.6° between the space connecting line and the vertical plane; the vertical plane is parallel to the end face of the hub; the head and tail of the three partitions are overlapped and staggered when arranged; the partitions The arc length of the overlapping and staggered between the head and tail is 1/3 of the arc length in the partition; There is an airflow compressing block between the two overlapping baffles, the airflow compressing block is fixed on the outer circumferential surface of the wheel hub, and the two sides of the airflow compressing block are respectively connected to the adjacent two The side surfaces of the head or tail of the baffle are fixedly connected; the baffle and the airflow compression block constitute the rotary stamping stator of the compressor; the impinging rotor blade row and the rotating stamping stator are arranged in parallel on the hub in turn. 2. The compressor based on an impact rotor-rotating stamping stator according to claim 1, wherein the impact rotor blade is an arc-shaped plate; the surface adjacent to the impact rotor blade and the casing surface is a blade tip The surface that cooperates with the outer surface of the hub is the bottom surface of the blade; the intersection of the leading edge of the impingement rotor blade and the top surface of the blade is called the top leading edge point, and the intersection of the trailing edge and the top surface of the blade is called the top surface trailing edge point; The intersection of the leading edge of the impingement rotor blade and the bottom surface of the blade is called the bottom leading edge point; the distance between the top leading edge points of two adjacent impingement rotor blades is 59.37 mm. 3. The compressor based on the impact rotor-rotating stamping stator as claimed in claim 1, wherein a curve passing through the top surface of the blade is made from the leading edge to the trailing edge of the top surface of the blade, and the curve is the middle arc of the top surface Line; the middle arc line of the top surface is located at 1/2 of the thickness of the blade; the straight line obtained by connecting the two endpoints of the middle arc line of the top surface is the top surface chord of the impingement rotor blade; the arc line in the top surface The tangents of the arc are made at the two endpoints of , respectively, and the tangent to the leading edge of the top and the tangent to the trailing edge of the top are obtained respectively. 4. The compressor based on an impact rotor-rotating stamping stator according to claim 1, wherein the convex surface of the impact rotor blade is a suction surface, and the suction surface is composed of three arc-shaped surfaces; The arcs are tangent at the connection; record the connection between the boundary point at the relative chord length x=0.5 of the suction surface and the chord length of the top surface, and make the connection line perpendicular to the chord length of the top surface; the connection The length of the line is y ₁ ; y ₁ is equal to 1/3 of the chord length of the top surface; the starting point of the first arc segment of the suction surface is the leading edge point, and the end point is the first dividing point, which is located on the opposite side. Chord length x _E = 0.21, y _E = 0.5y ₁ ; the starting point of the second arc segment of the suction surface is the first dividing point, and the end point is the second dividing point, the second dividing point is located at the relative chord length x _F = 0.6, y _F = 1.05y ₁ ; the starting point of the third arc segment on the suction surface is the second dividing point, and the ending point is the trailing edge point; The concave surface of the impingement rotor blade is the pressure surface, and the distance from the boundary point of the pressure surface relative to the chord length x=0.5 to the chord length of the top surface is y ₂ , and y ₂ is equal to 1/4 of the chord length of the top surface; The starting point of the airfoil is the leading edge point, and the end point is the third dividing point, which is located at the relative chord length x _G = 0.2, y _G = 0.5y ₂ ; the starting point of the rear airfoil is the third dividing point , the end point is the trailing edge point; the pressure surface of the front airfoil is made into a concave shape to reduce the _wavefront Mach number and reduce the shock loss. The pre-compression degree of the airfoil is the largest; the rear section of the pressure surface is composed of three tangential arcs; The functional relationship between y and x of the pre-compression airfoil in the front section is: y=-0.0004x ² -0.6128x+0.5y ₂ The starting point of the first arc segment of the pressure surface of the rear arc profile is the third dividing point, and the end point is the fourth dividing point. The fourth dividing point is located at the relative chord length x _H = 0.43, y _H = 0.8y ₂ ; the starting point of the second arc segment of the pressure surface is the fourth dividing point, and the end point is the fifth dividing point, the fifth dividing point is at=located at the relative chord length x ₁ =0.8, y ₁ =0.85y ₂ ; pressure The starting point of the third circular arc segment of the surface is the fifth dividing point, and the ending point is the trailing edge point. 5. The compressor based on an impact rotor-rotating stamping stator according to claim 4, wherein the suction surface and the pressure surface of the impact rotor blade are connected by an arc at the intersection of the leading edge, and the curvature of the arc is The radius is 0.1% to 3% of the chord length; the suction surface and the pressure surface of the impact rotor blade are connected by an arc at the intersection of the trailing edge, and the curvature radius of the arc is 0.1% to 3% of the chord length. 6 . The compressor based on the impact rotor-rotating stamping stator according to claim 1 , wherein the connection line between the leading edge points of the impact rotor blades distributed on the circumference of the hub is the top leading edge forehead line. 7 . ; The connection line between the trailing edge points of the impingement rotor blades distributed on the circumference of the hub is called the top trailing edge line; the acute angle formed by the top leading edge foreline and the top leading edge tangent is the top surface geometric inlet Angle α; the acute angle formed by the forehead line of the rear edge of the top surface and the tangent of the rear edge of the top surface is the geometric exit angle β of the top surface; the angle obtained by the intersection of the tangent line of the front edge of the top surface and the tangent of the rear edge of the top surface is the top surface bending angle; The line connecting the leading edge points of the impingement rotor blades distributed on the circumference of the hub is called the bottom leading edge frontal line; The included angle between the chord length of the bottom surface and the forehead line of the bottom front edge is the blade root installation angle γ; the installation angle γ of the blade root of each impact rotor blade is 65.9°. 7. The compressor based on an impact rotor-rotating stamping stator as claimed in claim 1, wherein the airflow compression block has 3; the lower surface of the airflow compression block is an arc that fits with the outer surface of the wheel hub The upper surface is arc-shaped, and is processed into seven slopes with different inclinations to compress the airflow entering the rotating stamping stator; the upper surface is divided into The ascending section and the descending section, wherein the surface of the ascending section is processed into four mutually connected slopes, and the surface of the descending section is processed into three mutually connected slopes; the ascending section is the airflow inlet, and the descending section is the airflow outlet; In this ascending section, the included angle θ ₁ between the first inclined plane at the airflow inlet and the horizontal plane is 63.6°, and the included angle θ ₂ between the second inclined plane and the horizontal plane is one-half of θ ₁ . The included angle θ ₃ between the three-stage inclined plane and the horizontal plane is one-half of θ ₂ , and the included angle θ ₄ between the fourth-stage inclined plane and the horizontal plane is one-half of θ ₃ ; The angle between the inclined plane and the horizontal plane is all below the horizontal plane, so that each section of the inclined plane is in a downward trend, wherein the angle between the fifth section of the inclined plane and the horizontal plane connected with the fourth section of the inclined plane in the ascending section is θ ₅ = θ ₄ ; the sixth-segment slope connects with the fifth-slope, and the angle between the sixth-slope and the horizontal plane is θ ₆ =2θ ₅ ; the seventh-slope connects with the sixth-slope, and the sixth-slope connects with the sixth-slope, the The included angle θ ₇ =2θ ₆ between the seven-segment inclined plane and the horizontal plane.

Images