CN105756866B - Vortex generating means - Google Patents

Abstract

The invention provides a vortex generating device, which is used to draw the high-energy fluid outside the boundary layer into the bottom layer of the boundary layer by generating a flow direction vortex, thereby inhibiting the flow separation on the surface of the blade. The upper surface of the blade is 20% to 25% away from the leading edge of the blade, and there is a base arranged on the upper surface of the blade and a plurality of vortex generating units arranged on the base; the interlocking part is arranged inside the blade; the induction part , is arranged at the position where the lower surface of the blade is 5-10% away from the leading edge of the blade; the elastic part is arranged between the induction part and the blade.

Description

Vortex generator

technical field

The invention relates to a device for suppressing flow separation on the blade surface, in particular to a vortex generating device.

Background technique

When the fluid flows through the blade, it is generally an attached flow at a small angle of attack. At this time, the lift coefficient is larger and the resistance is smaller. When the angle of attack increases to a certain extent, the flow separation is more likely to occur on the upper surface of the trailing edge of the blade, that is, A stall occurs, resulting in a decrease in lift and an increase in drag. The angle of attack is the angle between the incoming flow and the airfoil chord line of the blade. Large-scale wind turbine blades require strong structural strength from the middle to the root. Generally, large-thickness blades are used. Thick blades are more likely to stall when the angle of attack increases. Aircraft and other blades are also prone to stall when taking off or encountering unstable airflow, resulting in reduced lift and accidents. Therefore, suppressing blade flow separation has become a hot issue in blade aerodynamics research.

The vortex generator is a passive flow control device arranged on the upper surface of the blade near the leading edge, which can effectively inhibit the flow separation on the blade surface. The purpose of suppressing flow separation is achieved by generating flow direction vortices to draw the high-energy fluid outside the boundary layer into the bottom layer of the boundary layer. The vortex generator suppresses flow separation at high blade angles of attack, but at small angles of attack it becomes an unnecessary device that not only reduces the lift coefficient but also creates additional drag.

The early vortex generators consisted of a row of small spoilers, which were fixedly installed on blades such as aircraft wings. However, as a passive flow control technology, the disadvantage was that it could not work well according to different actual conditions. It is easy to be affected by the change of the flow state when adjusting the situation, and it is easy to cause additional resistance or pay other costs in the non-design state.

Compared with solid vortex generators, jet-type vortex generators can artificially change various jet parameters, and thus have better adaptability to different flow states, and can close the jet when it is not needed without affecting flow has any adverse effects. However, the biggest defect of the jet vortex generator is that it needs to provide an air source with sufficient power to generate the jet, and secondly, the blockage of the jet orifice by dust and foreign matter particles will cause a decrease in work efficiency or even failure.

The plasma vortex generator is attached to the upper surface of the blade near the leading edge of the plasma actuator, which can excite the wall jet to interact with the incoming flow to generate a vortex to suppress flow separation. However, it has high requirements on the reliability of electronic components, and when the system has a power failure, the eddy current generator will fail.

Retractable vortex generators that actuate themselves to extend and retract by employing a phase change correlation mechanism. The disadvantage is that it still needs to be driven by related electrical devices, and the shape of the blade changes when the generator is extended and retracted, which affects the aerodynamic performance of the blade.

Contents of the invention

The present invention is made to solve the above problems, and an object of the present invention is to provide a vortex generating device for entraining high-energy fluid outside the boundary layer into the bottom layer of the boundary layer by generating a flow direction vortex.

As an embodiment, the present invention provides a vortex generating device, which is characterized in that it includes: a vortex generating part, which is arranged on the upper surface of the blade at a position 20% to 25% from the leading edge of the blade, and is used to generate a flow direction The vortex draws the high-energy fluid outside the surface boundary layer of the blade into the bottom layer of the surface boundary layer of the blade, including: a base arranged on the upper surface of the blade and a plurality of vortex generating units arranged on the base; Inside, one end is fixedly connected with the base, which is used to drive the movement of the vortex generating part; the sensing part is set at the position where the lower surface of the blade is 5-10% away from the leading edge of the blade, and is used to sense the pressure concentration near the leading edge of the blade after stalling The aerodynamic pressure in the area, the center of the sensing part is fixedly connected to the other end of the linkage part, the side of the sensing part close to the leading edge of the blade is fixedly connected to the blade, and the elastic part is arranged between the sensing part and the blade for When receiving the pressure from the sensing part, a restoring force is provided to the sensing part, one end of the elastic part is fixed on the blade, and the other end of the elastic part is fixedly connected to the side of the sensing part away from the leading edge of the blade.

In such an embodiment, there may be such a feature: wherein, the lower surface of the blade is provided with a groove at a position corresponding to the sensing part, the sensing part is disposed in the groove, and the sensing part is a pressure baffle.

In the above embodiment, it may also have such a feature: wherein, the size of the groove is consistent with the size of the pressure baffle, and a small groove is provided at the corresponding position of the elastic part, and the small groove just accommodates the compressed elastic department.

In the above embodiment, there may also be such a feature: wherein, the linkage part is any one of a connecting rod and a connecting plate.

In the above embodiment, there may also be such a feature: wherein, the fixed connection is a hinge connection.

As another embodiment, the present invention also provides a vortex generating device, which is characterized in that it includes: a vortex generating part, which is arranged at a position where the upper surface of the blade is 20% to 25% from the leading edge of the blade, for The flow direction vortex is generated to draw the high-energy fluid outside the surface boundary layer of the blade into the bottom layer of the surface boundary layer of the blade, including: a base arranged on the upper surface of the blade and a plurality of vortex generating units arranged on the base; the linkage part is arranged on Inside the blade, one end is fixedly connected with the base, which is used to drive the movement of the vortex generating part, and the elastic sensing part is set at the position of the lower surface of the blade at a distance of 5% to 10% from the leading edge of the blade, and is used to sense the leading edge of the blade after stalling. The center of the elastic sensing part is fixedly connected with the other end of the linkage part, and the side of the elastic sensing part close to the leading edge of the blade is directly connected with the blade.

In such an embodiment, there may be such a feature: wherein, the lower surface of the blade is provided with a groove at a position corresponding to the elastic sensing part, the elastic sensing part is arranged in the groove, and the elastic sensing part is an elastic thin plate.

In such an embodiment, it may also have the feature that the size of the groove is consistent with the size of the elastic sensing part.

In such an embodiment, it may also have the feature that the linkage part is any one of a connecting rod and a connecting plate.

In such an embodiment, it may also have the feature that the fixed connection is a hinged connection.

Function and Effect of Invention

According to the vortex generating device involved in the present invention, since the vortex generating part is arranged on the upper surface of the blade at a position 20% to 25% away from the leading edge of the blade, the flow direction vortex can be generated to entrain the high-energy fluid outside the boundary layer on the surface of the blade. The bottom layer of the surface boundary layer of the blade, the interlocking part is arranged inside the blade, and one end is fixedly connected to the base, which can drive the movement of the vortex generating part, and the sensing part is arranged on the lower surface of the blade at a position 5-10% away from the leading edge of the blade. It can sense the aerodynamic pressure in the pressure concentration area near the leading edge after the blade stalls. The elastic part is arranged between the sensing part and the blade, and can provide a restoring force to the sensing part under the pressure of the sensing part. Therefore, the vortex of the present invention occurs The device can generate an approximate flow direction vortex to draw the high-energy fluid outside the boundary layer into the bottom layer of the boundary layer, thereby inhibiting the flow separation on the surface of the blade.

Description of drawings

Fig. 1 is a schematic structural view of a vortex generating device in Embodiment 1 of the present invention; and

Fig. 2 is a schematic structural view of the vortex generating device in the second embodiment of the present invention.

Detailed ways

In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the following embodiments illustrate the vortex generating device of the present invention in detail with reference to the accompanying drawings.

Embodiment one

FIG. 1 is a schematic structural view of a vortex generating device in Embodiment 1 of the present invention.

As shown in Figure 1, the vortex generating device 10 is arranged near the leading edge of the blade 20 of the aircraft, and the high-energy fluid outside the boundary layer is drawn into the bottom layer of the boundary layer by generating a flow direction vortex, including: a vortex generating part 1, a link part 2, The sensing part 3 and the elastic part 4.

The vortex generating part 1 is arranged on the upper surface of the blade 20, and it includes a base not shown in the figure and a plurality of vortex generating units on the base, the base is arranged on the upper surface of the blade 20, and the vortex generating part 1 generates flow to the vortex to move the blade The high-energy fluid outside the surface boundary layer of the blade 20 is drawn into the bottom layer of the surface boundary layer of the blade 20. In this embodiment, the vortex generator 1 is a vortex generator 1, which is arranged at a position 25% away from the leading edge of the blade 20.

The interlocking part 2 is arranged inside the blade 20, one end of which is hinged to the base, and the interlocking part 2 drives the vortex generator 1 to move. In this embodiment, the linkage part 2 is a connecting rod 2 .

The induction part 3 is arranged on the lower surface of the blade 20, and can sense the aerodynamic pressure in the pressure concentration area near the leading edge of the blade 20. The specific position of the induction part 3 depends on the pressure concentration area when the blade stalls. The other end of the connecting rod 2 is connected by a hinge, and the side of the induction part 3 close to the front edge of the blade 20 is connected with the blade 20 by a hinge. In this embodiment, the sensing part 3 is a pressure baffle 3 , which is 10% away from the leading edge of the blade 20 .

The elastic part 4 is arranged between the pressure baffle 3 and the blade 20, and can provide a restoring force to the pressure baffle 3 under the pressure of the pressure baffle 3. One end of the elastic part 4 is fixed on the blade 20, and the other end of the elastic part 4 The side of the pressure baffle 3 away from the leading edge of the blade 20 is hinged. In this embodiment, the elastic part is the spring mechanism 4 .

The groove 5 is arranged on the lower surface of the blade 20 at the corresponding position of the pressure baffle 3, the pressure baffle 3 is arranged in the groove 5, the size of the groove 5 is consistent with the size of the pressure baffle 3, the groove 5 is in the spring A small groove not marked in the figure is also provided at the corresponding position of the mechanism 4, and the small groove can just accommodate the compressed spring mechanism 4.

The action process of embodiment one is as follows:

When the blade is at a large angle of attack, the flow separation of the blade occurs at this time, and the force on the pressure baffle 3 increases, which is greater than the restoring force of the spring mechanism 4. The pneumatic pressure presses the side of the pressure baffle 3 away from the leading edge of the blade 20 to the In the groove, the pressure baffle 3 drives the connecting rod 2, so that the connecting rod 2 moves toward the upper surface of the blade, and the connecting rod 2 drives the base to make the vortex generator 1 protrude from the upper surface of the blade 20, and the vortex generator 1 generates a flow direction The vortices draw energetic fluid outside the boundary layer of the blade 20 into the bottom layer of the boundary layer of the blade 20, thereby inhibiting blade flow separation. When the blade transitions from a large angle of attack state to a small angle of attack state, the pressure baffle 3 returns to the initial position under the restoring force of the spring mechanism 4, the pressure baffle 3 drives the connecting rod 2 to move downward, and the connecting rod 2 drives the base The vortex generator 1 is retracted.

Function and effect of embodiment one

According to the vortex generating device involved in this embodiment, because the vortex generator is arranged at the position where the upper surface of the blade is 25% from the leading edge of the blade, it can generate a flow direction vortex to entrain the high-energy fluid outside the surface boundary layer of the blade into the blade. The bottom layer of the surface boundary layer, the connecting rod is set inside the blade, one end of which is connected to the base, which can drive the vortex generator to move; the pressure baffle is set at the position of the lower surface of the blade 10% from the leading edge of the blade, which can sense the blade For the aerodynamic pressure in the pressure concentration area near the leading edge after the stall, the spring mechanism is arranged between the pressure baffle and the blade, which can provide a restoring force to the pressure baffle under the pressure of the pressure baffle. Therefore, the vortex generating device of this embodiment can generate a flow direction vortex when the blade is in a stall state, and the high-energy fluid outside the boundary layer will be involved in the bottom layer of the boundary layer, thereby inhibiting the flow separation on the surface of the blade; and when the blade is in an attached flow state, the vortex generator can Retracts to allow vanes to maintain optimum flow.

According to the vortex generating device involved in this embodiment, the interlocking part may also be a connecting plate in the present invention.

According to the vortex generating device involved in this embodiment, the vortex generating portion may also be disposed at a position where the upper surface of the blade is 20% to 25% from the leading edge of the blade.

According to the vortex generating device involved in this embodiment, the induction part may also be arranged at a position where the lower surface of the blade is 5-10% away from the leading edge of the blade.

According to the vortex generating device involved in this embodiment, the device can also be applied to equipment such as wind power generators and ocean current generators.

Embodiment two

In the second embodiment, the same symbols are assigned to the same structures as in the first embodiment.

Fig. 2 is a schematic structural view of the vortex generating device in the second embodiment of the present invention.

As shown in Figure 2, the vortex generating device 30 is arranged near the leading edge of the blade 20 of the aircraft, and the high-energy fluid outside the boundary layer is involved in the bottom layer of the boundary layer by generating a flow direction vortex, including: a vortex generating part 1, a link part 2 and Elastic sensing part 3.

The vortex generating part 1 is arranged on the upper surface of the blade 20, and it includes a base not shown in the figure and a plurality of vortex generating units on the base, the base is arranged on the surface of the blade 20, and the vortex generating part 1 generates flow to the vortex to move the blade 20. The high-energy fluid outside the surface boundary layer is drawn into the bottom layer of the surface boundary layer of the blade 20. In this embodiment, the vortex generator 1 is a vortex generator 1, which is arranged at a position 25% away from the leading edge of the blade 20.

The interlocking part 2 is arranged inside the blade 20, one end of which is connected to the base, and the interlocking part 2 drives the vortex generator 1 to move. In this embodiment, the linkage part 2 is a connecting rod 2 .

The elastic sensing part 6 is arranged on the lower surface of the blade 20, and can sense the aerodynamic pressure of the pressure concentration area near the leading edge of the blade 20. The specific position of the elastic sensing part 3 depends on the pressure concentration area when the blade stalls. The elastic sensing part 6 The center is connected with the other end of the connecting rod 2 by a hinge, and the side of the induction elastic part 6 close to the front edge of the blade 20 is directly connected with the blade 20 . In this embodiment, the elastic sensing part 6 is an elastic thin plate 6 . It is located 10% from the leading edge of the blade.

The groove 5 is arranged on the lower surface of the blade 20 at the corresponding position of the elastic thin plate 6 , the elastic thin plate 6 is arranged in the groove 5 , and the size of the groove 5 is consistent with the size of the elastic thin plate 6 .

The action process of embodiment two is as follows:

When the blade is at a large angle of attack, the flow separation of the blade occurs at this time, the force on the elastic thin plate 6 increases, and the pneumatic pressure presses the side of the elastic thin plate 6 away from the leading edge of the blade 20 into the groove, and the elastic thin plate 6 drives the connecting rod 2 , so that the connecting rod 2 moves toward the upper surface of the blade, and the connecting rod 2 drives the base so that the vortex generator 1 protrudes from the upper surface of the blade 20, and the vortex generator 1 generates a flow direction vortex to roll the high-energy fluid outside the boundary layer of the blade 20 Into the bottom layer of the boundary layer of the blade 20, thereby inhibiting the blade flow separation. When the blade transitions from a state with a large angle of attack to a state with a small angle of attack, the elastic thin plate 6 returns to the initial position under the action of its own restoring force, and the elastic thin plate 6 drives the connecting rod 2 to move downward, and the connecting rod 2 drives the base to make the vortex generator 1 retract.

Function and effect of embodiment two

According to the vortex generating device involved in this embodiment, because the vortex generator is arranged at the position where the upper surface of the blade is 25% from the leading edge of the blade, it can generate a flow direction vortex to entrain the high-energy fluid outside the surface boundary layer of the blade into the blade. The bottom layer of the surface boundary layer, the connecting rod is set inside the blade, one end of which is connected to the base, which can drive the movement of the vortex generator; the elastic thin plate is set at the position of the lower surface of the blade 10% from the leading edge of the blade, which can sense the stall of the blade The aerodynamic pressure in the area of pressure concentration near the trailing leading edge. Therefore, the vortex generating device of this embodiment can generate a flow direction vortex when the blade is in a stall state, and the high-energy fluid outside the boundary layer can be drawn into the bottom layer of the boundary layer, thereby inhibiting the flow separation on the surface of the blade; and when the blade is in an attached state, the vortex generator Ability to retract allowing the vanes to maintain optimum flow.

According to the vortex generating device involved in this embodiment, the interlocking part may also be a connecting plate in the present invention.

According to the vortex generating device involved in this embodiment, the vortex generating portion may also be disposed at a position where the upper surface of the blade is 20% to 25% from the leading edge of the blade.

According to the vortex generating device involved in this embodiment, the induction part may also be arranged at a position where the lower surface of the blade is 5-10% away from the leading edge of the blade.

According to the vortex generating device involved in this embodiment, the device can also be applied to equipment such as wind power generators and ocean current generators.

The above embodiments are only basic descriptions of the concept of the present invention, and do not limit the present invention. Any equivalent transformation made according to the technical solution of the present invention belongs to the protection scope of the present invention.

Claims (10)

1. A vortex generating device, which is arranged near the leading edge of the blade of the aircraft, is used to generate the flow direction vortex to entrain the high-energy fluid outside the surface boundary layer of the blade into the bottom layer of the surface boundary layer of the blade, and has a vortex generating part , set at the position where the upper surface of the blade is 20% to 25% away from the leading edge of the blade, and is used to generate a flow direction vortex to draw the high-energy fluid outside the surface boundary layer of the blade into the surface boundary of the blade The bottom layer includes: a base set on the upper surface of the blade and a plurality of vortex generating units set on the base, characterized in that it includes: The linkage part is arranged inside the blade, one end is fixedly connected with the base, and is used to drive the movement of the vortex generating part; The induction part is arranged at the position where the lower surface of the blade is 5-10% away from the leading edge of the blade, and is used to sense the aerodynamic pressure in the pressure concentration area near the leading edge of the blade after stalling, and the induction part The center is fixedly connected to the other end of the linkage part, and the side of the induction part close to the leading edge of the blade is fixedly connected to the blade, and The elastic part is arranged between the sensing part and the blade, and is used to provide a restoring force to the sensing part under the pressure of the sensing part, one end of the elastic part is fixed on the blade, The other end of the elastic part is fixedly connected to a side of the sensing part away from the leading edge of the blade. 2. The vortex generating device according to claim 1, characterized in that: Wherein, a groove is provided on the lower surface of the blade at a corresponding position of the sensing part, the sensing part is arranged in the groove, and the sensing part is a pressure baffle. 3. The vortex generating device according to claim 2, characterized in that: Wherein, the size of the groove is consistent with the size of the pressure baffle, and the groove is provided with a small groove at a position corresponding to the elastic part, and the small groove just accommodates the compressed elastic part. 4. The vortex generating device according to claim 1, characterized in that: Wherein, the linkage part is any one of a connecting rod and a connecting plate. 5. The vortex generating device according to claim 1, characterized in that: Wherein, the fixed connection is a hinge connection. 6. A vortex generating device, which is arranged near the leading edge of the blade of the aircraft, is used to generate a flow direction vortex to entrain the high-energy fluid outside the surface boundary layer of the blade into the bottom layer of the surface boundary layer of the blade, and has a vortex generating part , set at the position where the upper surface of the blade is 20% to 25% away from the leading edge of the blade, and is used to generate a flow direction vortex to draw the high-energy fluid outside the surface boundary layer of the blade into the surface boundary of the blade The bottom layer includes: a base set on the upper surface of the blade and a plurality of vortex generating units set on the base, characterized in that it includes: a linkage part arranged inside the blade, one end of which is fixedly connected to the base, and is used to drive the vortex generating part to move, and The elastic sensing part is arranged at the position where the lower surface of the blade is 5-10% away from the leading edge of the blade, and is used to sense the aerodynamic pressure in the pressure concentration area near the leading edge of the blade after the stall, and the elastic sensing part The center of the part is fixedly connected with the other end of the linkage part, and the side of the elastic sensing part close to the leading edge of the blade is directly connected with the blade. 7. The vortex generating device according to claim 6, characterized in that: Wherein, a groove is provided on the lower surface of the blade at a position corresponding to the elastic sensing part, the elastic sensing part is arranged in the groove, and the elastic sensing part is an elastic thin plate. 8. The vortex generating device according to claim 7, characterized in that: Wherein, the size of the groove is consistent with the size of the elastic sensing part. 9. The vortex generating device according to claim 6, characterized in that: Wherein, the linkage part is any one of a connecting rod and a connecting plate. 10. The vortex generating device according to claim 6, characterized in that: Wherein, the fixed connection is a hinge connection.