A vortex generator applied to high-load compressor cascade flow control

Abstract

The application discloses a vortex generator applied to high-load compressor cascade flow control and relates to the field of vortex generators, which comprises a blade, a slot is formed in the upper end position of the blade, a vortex plate is arranged in the slot, a flow regulation mechanism is arranged on the outer side wall of the vortex plate and close to one end position, a limiting mechanism is arranged on the both side walls of the vortex plate and at the bottom position, the flow regulation mechanism comprises a flow guide plate, a pin shaft is arranged through the outer side wall of the flow guide plate and close to the edge position, an arc-shaped slot is formed on the outer side wall of the vortex plate and at one side position of the flow guide plate, an arc-shaped sliding rod is arranged between the both inner side walls of the arc-shaped slot, and a sliding plate is arranged on the arc-shaped sliding rod and in the arc-shaped slot; by changing the inclination angle of the flow guide plate, the airflow flowing through the surface of the blade can be adjusted, the high-load compressor cascade flow control can be realized, and the stability between the vortex plate and the blade is improved.

Description

Technical Field

[0001] This invention relates to the field of vortex generators, and more particularly to a vortex generator for use in high-load compressor blade flow control. Background Technology

[0002] A vortex generator is a small winglet mounted vertically on the blade surface at a certain installation angle. It generates a strong wingtip vortex in the oncoming airflow. This high-energy wingtip vortex mixes with the low-energy boundary layer flow downstream, transferring energy to the boundary layer. This allows the boundary layer flow field in the adverse pressure gradient to gain additional energy and continue to adhere to the airframe surface without separation. As a result, the separation of the blade suction surface is reduced. This is the basic working principle of a blade vortex generator.

[0003] A common type of vortex generator used in high-load compressor blades is not convenient for controlling the airflow passing through the blades. Summary of the Invention

[0004] The purpose of this invention is to address the deficiencies in the prior art by proposing a vortex generator for high-load compressor blade flow control.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A vortex generator for high-load compressor blade flow control includes blades, a slot is provided at the upper end of the blades, a vortex plate is provided inside the slot, a flow straightening mechanism is provided on the outer wall of the vortex plate near one end, and a limiting mechanism is provided on both side walls of the vortex plate at the bottom.

[0007] As a further embodiment of the present invention: the rectifier mechanism includes a flow guide plate, and a pin is provided through the outer wall of the flow guide plate near the edge.

[0008] As a further embodiment of the present invention: an arc-shaped groove is provided on the outer wall of the vortex plate and at one side of the guide plate; an arc-shaped sliding rod is provided between the two inner walls of the arc-shaped groove; a sliding plate is provided on the arc-shaped sliding rod and inside the arc-shaped groove; and several sets of rectifying grooves are provided on the outer wall of the blade and near one side.

[0009] As a further embodiment of the present invention: the included angle of the vortex plate is 80°, the upper surface of the vortex plate is inclined, the sliding plate is slidably disposed inside the arc-shaped groove along the arc-shaped sliding rod, and one end of the sliding plate is fixedly connected to the side wall of the diversion plate.

[0010] As a further embodiment of the present invention: one end of the flow guide plate slides along the arc groove on the surface of the vortex plate through a pin and a sliding plate in cooperation with an arc-shaped sliding rod; one end of the pin passes through the vortex plate and is disposed inside the flow guide plate; and several sets of the flow straightening grooves are equally spaced on the surface of the blade.

[0011] As a further embodiment of the present invention: the limiting mechanism includes a threaded rod, and grooves are provided on both sides of the vortex plate near the bottom, with a threaded rod penetrating through the bottom end of the groove.

[0012] As a further embodiment of the present invention: a positioning nut is provided on the screw and located inside the groove, a fixing nut is provided at the bottom of the threaded rod and located above the screw, and a sealing plate is provided between the two inner sidewalls of the groove and near the edge.

[0013] As a further embodiment of the present invention: one end of the screw passes through the vortex plate and is disposed inside the blade; the upper end of the threaded rod is fixedly connected to the top side wall of the groove; the fixing nut is movably disposed inside the groove through the threaded rod; the bottom of the vortex plate is inserted into the slot; and the vortex plate is fixedly disposed on the blade through the slot and the limiting mechanism.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0015] 1. When the compressor blades rotate with the compressor under high load, airflow flows over the blade surface. As the airflow passes over the blades, a pressure difference arises between the pressure and suction sides due to the different flow velocities. When the blade angle of attack increases or the leading edge and surface of the blade are damaged, airflow separation occurs on the blade surface, leading to increased blade noise and decreased aerodynamic efficiency. Vortex plates and straighteners are used to effectively prevent or mitigate airflow separation on the blade surface, thus maintaining or increasing the compressor's stable operating margin. Strong wingtip vortices are generated in the oncoming airflow. These high-energy wingtip vortices mix with the downstream low-energy boundary layer flow, transferring energy to the boundary layer. This allows the boundary layer flow field in the adverse pressure gradient to gain additional energy and continue to adhere to the compressor surface without separation, thus maintaining or increasing the pressure difference. To ensure stable operation of the compressor, the bottom end of the vortex plate is inserted into the slot and positioned by a limiting mechanism, thus securing the vortex plate firmly on the blade. The pin is rotated counterclockwise to loosen the connection between the vortex plate and the guide plate. The guide plate is then rotated around the pin, causing the other end of the guide plate to move along the arc-shaped groove on the surface of the vortex plate via a sliding plate and an arc-shaped sliding rod. The arc-shaped sliding rod and sliding plate allow for positioning of the guide plate without affecting its rotation, ensuring the guide plate is tightly against the vortex plate surface. After adjusting the angle of the guide plate, the pin is rotated clockwise to tighten the connection between the guide plate and the guide plate, thus fixing the guide plate to one side of the vortex plate. By changing the tilt angle of the guide plate, the airflow direction across the blade surface can be adjusted, thereby enabling flow control of the high-load compressor blade cascade.

[0016] 2. After inserting the bottom of the vortex plate into the slot, insert the bottom end of the screw through the vortex plate and place it inside the blade. Then rotate the positioning nut to the top of the screw and make it close to the inner wall of the groove. At this time, the positioning nut can fix the vortex plate. Then rotate the fixing nut to move it down along the threaded rod until the bottom end of the fixing nut is close to the upper end of the positioning nut. At this time, the fixing nut is positioned by the threaded rod, which further improves the stability between the vortex plate and the blade. Attached Figure Description

[0017] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used together with the embodiments of the invention to explain the invention and do not constitute a limitation thereof.

[0018] Figure 1 This is a schematic diagram of the overall structure of a vortex generator for high-load compressor blade flow control proposed in this invention;

[0019] Figure 2 This is a schematic diagram of the vortex plate and guide plate of a vortex generator for high-load compressor blade flow control proposed in this invention;

[0020] Figure 3This is a top view of a vortex generator for high-load compressor blade flow control proposed in this invention;

[0021] Figure 4 This is a front view of a vortex generator for high-load compressor blade flow control proposed in this invention;

[0022] Figure 5 This is a schematic diagram of the guide plate and groove of a vortex generator for high-load compressor blade flow control proposed in this invention;

[0023] Figure 6 This is a partial structural diagram of the guide plate in a vortex generator for high-load compressor blade flow control proposed in this invention.

[0024] In the diagram: 1. Blade; 2. Vortex plate; 3. Drain plate; 4. Pin; 6. Arc groove; 7. Arc slide bar; 8. Sliding plate; 9. Rectifying groove; 10. Rectifying mechanism; 11. Slot; 12. Limiting mechanism; 13. Groove; 14. Threaded rod; 15. Screw; 16. Positioning nut; 17. Fixing nut; 18. Sealing plate. Detailed Implementation

[0025] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0026] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0027] Example 1

[0028] Please see Figures 1-6 The present invention provides a technical solution: a vortex generator for high-load compressor blade flow control, including blades 1, a slot 11 is provided at the upper end of the blades 1, a vortex plate 2 is provided inside the slot 11, a rectifier mechanism 10 is provided on the outer wall of the vortex plate 2 near one end, and a limiting mechanism 12 is provided on both sides of the vortex plate 2 at the bottom.

[0029] Please see Figure 2 and 3 The rectifier mechanism 10 includes a flow guide plate 3, and a pin 4 is provided through the outer wall of the flow guide plate 3 near the edge.

[0030] An arc-shaped groove 6 is provided on the outer wall of the vortex plate 2 and on one side of the guide plate 3. An arc-shaped sliding rod 7 is provided between the two inner walls of the arc-shaped groove 6. A sliding plate 8 is provided on the arc-shaped sliding rod 7 and inside the arc-shaped groove 6. Several sets of rectifier grooves 9 are provided on the outer wall of the blade 1 and near one side.

[0031] The included angle of the vortex plate 2 is 80°, the upper surface of the vortex plate 2 is inclined, the sliding plate 8 is slidably disposed inside the arc-shaped groove 6 along the arc-shaped sliding rod 7, and one end of the sliding plate 8 is fixedly connected to the side wall of the diversion plate 3.

[0032] One end of the guide plate 3 slides along the arc groove 6 on the surface of the vortex plate 2 via a pin 4 and a sliding plate 8. One end of the pin 4 passes through the vortex plate 2 and is set inside the guide plate 3. Several sets of straightening grooves 9 are equidistantly opened on the surface of the blade 1.

[0033] During operation, when the high-load compressor blades rotate with the compressor, airflow flows over the surface of blade 1. As the airflow passes over blade 1, a pressure difference arises between the pressure and suction sides due to the different flow velocities. When the angle of attack of blade 1 continuously increases or the leading edge and surface of blade 1 are damaged, airflow separation will occur on the surface of blade 1, leading to increased noise and decreased aerodynamic efficiency. The vortex plate 2 and the straightener 9 are used to effectively prevent or slow down the airflow separation on the surface of blade 1, thus maintaining or improving the compressor's stable operating margin. A strong wingtip vortex is generated in the oncoming airflow. This high-energy wingtip vortex mixes with the low-energy boundary layer flow downstream, transferring energy to the boundary layer. This allows the boundary layer flow field in the adverse pressure gradient to gain additional energy and continue to adhere to the fuselage surface without separation. The bottom end of the vortex plate 2... Inserted into slot 11 and positioned by limiting mechanism 12, vortex plate 2 is securely mounted on blade 1. Rotate pin 4 counterclockwise to loosen the connection between it and guide plate 3. Rotate guide plate 3 around pin 4. At this time, the other end of guide plate 3 moves along arc groove 6 on the surface of vortex plate 2 through sliding plate 8 and arc sliding rod 7. Arc sliding rod 7 and sliding plate 8 can position guide plate 3 without affecting its rotation, so that guide plate 3 is in close contact with the surface of vortex plate 2. After the angle of guide plate 3 is adjusted, rotate pin 4 clockwise to tighten the connection between it and guide plate, so that guide plate 3 is fixed on one side of vortex plate 3. By changing the tilt angle of guide plate 3, the airflow direction flowing through the surface of blade 1 can be adjusted, thereby controlling the flow of the high-load compressor blade.

[0034] Example 2

[0035] Please see Figures 1-6The present invention provides a technical solution: a vortex generator for high-load compressor blade flow control, including blades 1, a slot 11 is provided at the upper end of the blades 1, a vortex plate 2 is provided inside the slot 11, a rectifier mechanism 10 is provided on the outer wall of the vortex plate 2 near one end, and a limiting mechanism 12 is provided on both sides of the vortex plate 2 at the bottom.

[0036] Please see Figure 4-6 The limiting mechanism 12 includes a threaded rod 14, and grooves 13 are provided on both sides of the vortex plate 2 near the bottom. A threaded rod 15 is provided through the bottom end of the groove 13.

[0037] A positioning nut 16 is provided on the screw 15 and inside the groove 13, a fixing nut 17 is provided at the bottom of the threaded rod 14 and above the screw 15, and a sealing plate 18 is provided between the two inner side walls of the groove 13 and near the edge.

[0038] One end of the screw 15 passes through the vortex plate 2 and is set inside the blade 1. The upper end of the threaded rod 14 is fixedly connected to the top side wall inside the groove 13. The fixing nut 17 is movably set inside the groove 13 through the threaded rod 14. The bottom of the vortex plate 2 is inserted into the slot 11. The vortex plate 2 is fixedly set on the blade 1 through the slot 11 and the limiting mechanism 12.

[0039] Specifically, after inserting the bottom of the vortex plate 2 into the slot 11, the bottom end of the screw 15 passes through the vortex plate 2 and is placed inside the blade 1. Then, the positioning nut 16 is rotated to the top of the screw 15 and is tightly attached to the inner wall of the groove 13. At this time, the positioning nut 16 can fix the vortex plate 2. Then, the fixing nut 17 is rotated to move downward along the threaded rod 14 until the bottom end of the fixing nut 17 is tightly attached to the upper end of the positioning nut 16. At this time, the fixing nut 17 is positioned by the threaded rod 14 to fix the positioning nut 16, which further improves the stability between the vortex plate 2 and the blade 1. The sealing plate 18 is placed between the inner walls of the groove 13 by hot melt adhesive to seal the groove 13 and avoid affecting the flow of air.

[0040] Working principle: After inserting the bottom of the vortex plate 2 into the slot 11, the bottom end of the screw 15 passes through the vortex plate 2 and is placed inside the blade 1. Then, the positioning nut 16 is rotated to the top of the screw 15 and tightly against the inner wall of the groove 13. At this time, the positioning nut 16 can fix the vortex plate 2. Then, the fixing nut 17 is rotated to move downward along the threaded rod 14 until the bottom end of the fixing nut 17 is tightly against the upper end of the positioning nut 16. At this time, the fixing nut 17 is positioned by the threaded rod 14 to fix the positioning nut 16, further improving the stability between the vortex plate 2 and the blade 1. The sealing plate 18 is placed between the inner walls of the groove 13 with hot melt adhesive to seal the groove 13 and avoid affecting the airflow. The bottom end of the vortex plate 2 is inserted into the slot 11 and is fixed by the limiting mechanism 12. Position the vortex plate 2 and securely place it on the blade 1. Rotate the pin 4 counterclockwise to loosen the connection between it and the guide plate 3. Rotate the guide plate 3 around the pin 4. At this time, the other end of the guide plate 3 moves along the arc groove 6 on the surface of the vortex plate 2 through the sliding plate 8 and the arc-shaped sliding rod 7. The arc-shaped sliding rod 7 and the sliding plate 8 can position the guide plate 3 without affecting its rotation, so that the guide plate 3 is in close contact with the surface of the vortex plate 2. After the angle of the guide plate 3 is adjusted, rotate the pin 4 clockwise to tighten the connection between it and the guide plate, so that the guide plate 3 is fixedly placed on one side of the vortex plate 3. By changing the tilt angle of the guide plate 3, the airflow direction flowing through the surface of the blade 1 can be adjusted, thereby controlling the flow of the high-load compressor blade.

[0041] When the high-load compressor blades rotate with the compressor, the airflow will flow on the surface of blade 1. When the airflow blows over blade 1, a pressure difference will be generated on the pressure side and suction side due to the different flow velocities. When the angle of attack of blade 1 continues to increase or the leading edge and surface of blade 1 are damaged, airflow separation will occur on the surface of blade 1, which will lead to increased noise and decreased aerodynamic efficiency of blade 1. The vortex plate 2 and the straightening slot 9 are used to effectively prevent or slow down the generation of airflow separation on the surface of blade 1, thus maintaining or improving the compressor's stable operating margin. A strong wingtip vortex is generated in the oncoming airflow. After this high-energy wingtip vortex mixes with the low-energy boundary layer flow downstream, it transfers energy to the boundary layer, so that the boundary layer flow field in the adverse pressure gradient can continue to adhere to the surface of the airframe without separation after obtaining additional energy.

[0042] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A vortex generator for application to high-load compressor cascade flow control, comprising a blade (1), characterised in that, The blade (1) has a slot (11) at the upper end, and a vortex plate (2) is provided inside the slot (11). A rectifier mechanism (10) is provided on the outer side wall of the vortex plate (2) near one end. A limiting mechanism (12) is provided on both sides of the vortex plate (2) at the bottom. The rectifier (10) includes a flow guide plate (3), and a pin (4) is provided through the outer wall of the flow guide plate (3) near the edge. An arc-shaped groove (6) is provided on the outer wall of the vortex plate (2) and on one side of the guide plate (3). An arc-shaped sliding rod (7) is provided between the two inner walls of the arc-shaped groove (6). A sliding plate (8) is provided on the arc-shaped sliding rod (7) and inside the arc-shaped groove (6). Several sets of rectifier grooves (9) are provided on the outer wall of the blade (1) and near one side.

2. A vortex generator for use in high-load compressor cascade flow control according to claim 1, characterized in that The included angle of the vortex plate (2) is 80°, the upper surface of the vortex plate (2) is inclined, the sliding plate (8) is slidably disposed inside the arc groove (6) along the arc sliding rod (7), and one end of the sliding plate (8) is fixedly connected to the side wall of the diversion plate (3).

3. A vortex generator for use in high-load compressor cascade flow control according to claim 2, characterized in that One end of the diverting plate (3) is connected to the sliding plate (8) and the arc-shaped sliding rod (7) to slide along the arc-shaped groove (6) on the surface of the vortex plate (2). One end of the pin (4) passes through the vortex plate (2) and is set inside the diverting plate (3). Several sets of the straightening grooves (9) are equally spaced on the surface of the blade (1).

4. A vortex generator for use in high-load compressor cascade flow control according to claim 1, characterized in that, The limiting mechanism (12) includes a threaded rod (14), and grooves (13) are provided on both sides of the vortex plate (2) near the bottom. A threaded rod (15) is provided through the bottom of the groove (13).

5. A vortex generator for use in high-load compressor cascade flow control according to claim 4, characterized in that A positioning nut (16) is provided on the screw (15) and inside the groove (13). A fixing nut (17) is provided at the bottom of the threaded rod (14) and above the screw (15). A sealing plate (18) is provided between the two inner sidewalls of the groove (13) and near the edge.

6. A vortex generator for high-load compressor blade flow control according to claim 5, characterized in that, One end of the screw (15) passes through the vortex plate (2) and is set inside the blade (1). The upper end of the threaded rod (14) is fixed to the top side wall inside the groove (13). The fixing nut (17) is movably set inside the groove (13) through the threaded rod (14). The bottom of the vortex plate (2) is inserted into the slot (11). The vortex plate (2) is fixed on the blade (1) through the slot (11) and the limiting mechanism (12).

Images