• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    RETRACTABLE VORTEX GENERATOR TO REDUCE LOSS SPEED. The present invention relates to a device and methods for improving the low speed performance of an airfoil assembly. At least one vortex generator is coupled to the airfoil assembly, and the vortex generator is extended through the airfoil assembly by tilting an articulated leading edge coupled to the airfoil assembly to increase lift. The vortex generator is retracted within the airfoil assembly to decrease drag.
    公开号:BR102012016563B1
    申请号:R102012016563-5
    申请日:2012-07-04
    公开日:2021-01-12
    发明作者:Bruce R. Fox；Stephen J. Fox
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    [0001] [001] The modalities of the present description generally refer to the flow along dynamic surfaces of fluids. More particularly, the modalities of the present description refer to the retractable vortex generators to enhance the dynamic characteristics of the flow fluids along dynamic surfaces of the fluids. Background
    [0002] [002] Flow separation generally occurs when a boundary layer moves towards an anterior edge of a support surface and far enough from an adverse pressure gradient in which a velocity of the boundary layer in relation to the supporting surface falls almost to zero. The flow of fluids can become separated from the support surface and form swirls and vortices instead. In aerodynamics, flow separation can often result in increased drag and reduced lift. Flow separation generally worsens speed performance by causing the boundary layer to separate at high angles of attack. The worsened low speed performance, in turn, increases a "loss speed" of the airfoil and potentially causes non-optimal flight conditions when the airfoil is operating at low speeds associated with takeoff and landing. summary
    [0003] [003] A device and methods for improving the low speed performance of an airfoil assembly are described. At least one vortex generator is coupled to a support surface, and the vortex generator is extended across the support surface to increase lift. The vortex generator is retracted within the support surface to decrease drag.
    [0004] [004] A simple articulated inclined front edge device is combined with retractable vortex generators and is coupled to a support surface, such as a wing. In the cruise configuration, the wing has smooth top and bottom drag surfaces. In the low speed setting, an anterior wing edge tilts and the vortex generators extend in an air flow. The sloping front edge increases curvature and the extended vortex generators energize the airflow over an upper surface similar to a complex slotted system. This action increases low speed performance at high angles of attack. In this way, heavy complex front edge high support devices that are expensive, maintenance-intensive and suffer from performance-reducing surface discontinuities are replaced by a simpler, lighter and smoother front edge device.
    [0005] [005] In one embodiment, a method improves the low speed performance of an airfoil assembly. At least one vortex generator is coupled to an airfoil assembly, and the vortex generator is extended through the airfoil assembly by tilting an articulated front edge coupled to the airfoil assembly to increase lift. The vortex generator is retracted within the support surface to decrease drag. In another embodiment, a retractable vortex generating device comprises a hinged front edge device coupled to a support surface, and at least one vortex generator coupled to a support surface. The vortex generator is operable to extend across the support surface to increase lift when the hinged leading edge is tilted, and to retract into the support surface to decrease drag when the hinged leading edge is raised.
    [0006] [006] In yet another embodiment, a method for operating an airfoil assembly provides improved low speed performance. The method causes a fluid to flow along the airfoil assembly, and tilts a hinged front edge device to a first surface of the airfoil assembly, from a nominal position to a deflected position. The method further exposes a plurality of retractable vortex generators at a distance in addition to a dynamic surface of the support surface assembly fluids in response to the inclination of the front edge device. The method additionally causes a vortex to be generated within the fluid, and to vary a magnitude of an inclined position of the anterior edge device.
    [0007] [007] This summary is provided to introduce a selection of concepts in a simplified way that will be further described below in the detailed description. This summary is not intended to identify key resources or essential resources of the subject matter claimed, nor is it intended to be used as an aid in determining the scope of the subject matter claimed. Brief Description of Drawings
    [0008] [008] A more complete understanding of the modalities of the present description can be derived referring to the detailed description and the claims when considered together with the figures below, in which the similar numerical references refer to similar elements throughout all figures. The figures are provided to facilitate the understanding of the description without limiting the amplitude, scope, scale or applicability of the description. The drawings are not necessarily to scale.
    [0009] [009] Figure 1 is an illustration of a flowchart of an exemplary aircraft production and service methodology.
    [0010] [0010] Figure 2 is an illustration of an example block diagram of an aircraft.
    [0011] [0011] Figure 3 is an illustration of a perspective view of a support surface assembly showing an inclination of the front edge that exposes the retractable vortex generators (RVGs), according to a description modality.
    [0012] [0012] Figure 4 is an illustration of a side cross-sectional view of a portion of a support surface assembly showing an anterior edge slope that exposes a single RVG, according to one embodiment of the description.
    [0013] [0013] Figure 5 is an illustration of a perspective view of an airfoil assembly showing the smooth upper and lower front edge support surfaces in a cruise configuration with RVGs hidden under a tilted hinged front edge, according to a description mode.
    [0014] [0014] Figure 6 is an illustration of a perspective view of a support surface assembly showing an initial front edge slope at an angle of about 5 degrees that exposes the RVGs, according to one embodiment of the description.
    [0015] [0015] Figure 7 is an illustration of a perspective view of an airfoil assembly showing a mid-level anterior edge slope at an angle of about 15 degrees that extends the RVGs out of the grooves in a liner of an aerodynamic surface of the airfoil assembly, according to a description mode.
    [0016] [0016] Figure 8 is an illustration of a perspective view of a support surface assembly showing an inclination of the front edge totally displaced at an angle of about 30 degrees that exposes and fully extends the RVGs, according to a description mode.
    [0017] [0017] Figure 9 is an illustration of an example flowchart showing a process for using RVGs to improve the low speed performance of an airfoil assembly, according to one embodiment of the description.
    [0018] [0018] Figure 10 is an illustration of an exemplary flow chart showing a process for operating an airfoil assembly that provides improved low speed performance, according to one embodiment of the description. Detailed Description
    [0019] [0019] The following detailed description is of an exemplary nature and is not intended to limit the description or the application and uses of the description modalities. Descriptions of specific devices, techniques and applications are provided as examples only. Changes to the examples described in this document will be readily apparent to those skilled in the art, and the general principles defined in this document can be applied to other examples and applications without departing from the spirit and scope of the description. In addition, there is no intention to be linked to any expressed or implied theory presented in the preceding field, background, summary or detailed description below. The present description should have the scope consistent with the claims, and not limited to the examples described and shown in this document.
    [0020] [0020] The description modalities can be described in this document in terms of functional and / or logical block components and different processing steps. It must be assessed that such block components can be realized by any number of hardware, software and / or firmware components configured to perform the specified functions. For the sake of brevity, conventional techniques and components related to aerodynamics, fluid dynamics, structures, control surfaces, fabrication and other functional aspects of systems (and the individual operating components of systems) may not be described in detail in the present document. In addition, those skilled in the art will appreciate that the modalities of the present description can be practiced in conjunction with a variety of structural bodies, and that the modalities described in this document are merely exemplary modalities of the description.
    [0021] [0021] The modalities of the description are described in this document in the context of an application without practical limitation, that is, an anterior wing edge. The description modalities, however, are not limited to such front edge applications, and the techniques described in this document can also be used in other dynamic fluid surface applications. For example, the modalities may be applicable to other aircraft support surfaces, such as a flap or tail, an aircraft control surface, such as an elevator and a wing, an engine support, a blade wind turbine, a hydrodynamic surface that uses liquid (for example, water) instead of air, a sailing boat, an engine propeller, a windmill, and the like.
    [0022] [0022] As will be apparent to the person skilled in the art after reading this description, the following examples and modalities of the description are not limited to operate according to these examples. Other modalities can be used and structural changes can be made without leaving the scope of the exemplary modalities of the present description
    [0023] [0023] Referring more particularly to the drawings, the modalities of the description can be described in the context of an aircraft manufacturing and service method 100 (method 100), as shown in figure 1 and an aircraft 200, as shown in figure 2 During pre-production, example method 100 may include aircraft 200 specification and design 104 and material acquisition 106. During production, component and subassembly manufacturing 108 and system integration 110 of aircraft 200 take place. Subsequently, aircraft 200 can pass through certification and distribution 112 in order to be put into service 114. While in service through a customer, aircraft 200 is scheduled for routine maintenance and service 116 (which may also include modification, reconfiguration , restoration, and so on).
    [0024] [0024] Each of the method 100 processes can be performed or executed by a system integrator, third parties and / or an operator (for example, a customer). For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major system subcontractors; third parties may include without limitation any number of vendors, subcontractors and suppliers; and an operator may be, without limitation, an airline, leasing company, military entity, service organization, and the like.
    [0025] [0025] As shown in figure 2, the aircraft 200 produced by the exemplary method 100 can include an airplane structure 218 with a plurality of systems 220 and an interior 222. Examples of high level systems 220 include one or more of one system propulsion system 224, an electrical system 226, a hydraulic system 228, and an environmental system 230. Any number of other systems can also be included. Although an exemplary airspace is shown, the description modalities can be applied to other industries.
    [0026] [0026] The apparatus and methods incorporated in this document can be used during any one or more of the stages of the production and service method 100. For example, the components or subassemblies that correspond to the production process 108 can be manufactured or produced in a similar to the components or subassemblies produced while aircraft 200 is in service. In addition, one or more apparatus modalities, method modalities, or a combination of them can be used during production stages 108 and 110, for example, by substantially prioritizing assembly or reducing the cost of an aircraft 200. similarly, one or more apparatus modalities, method modalities, or a combination thereof may be used while aircraft 200 is in service, for example, and without limitation, in maintenance and service 116.
    [0027] [0027] The description modalities combine the benefits of a retractable split wing groove with the benefits of a fixed vortex generator while eliminating the main disadvantages of both. In some embodiments, a simple hinged inclined front edge device is provided which increases a curvature of an aerodynamic body, such as one used in low speed configurations, in other embodiments, a front edge device can be used . Retractable vortex generators (RVGs) can be positioned under a rear edge of the front edge device (i.e., split or non-split front edge device). On the cruise flight, the front edge device covers RVGs that provide a smooth, low-drag wing surface. At low speed, the front edge device rotates in its simple articulation, exposing the RVGs, which then extend in a flow of free current air that reduces noise.
    [0028] [0028] In this way, the extended RVGs energize the flow of free current air along an upper surface of the aerodynamic body in a manner similar to a complex slotted groove system. This action increases low speed performance by delaying the separation of the boundary layer at high angles of attack. However, in contrast to the existing complex slotted groove system, the modalities of the description eliminate the rear edge of the overlapping cruising slit and an anterior edge groove in an extended position. Elimination of the rear edge of the cruising groove and an anterior edge slot in an extended position reduces cruise drag and approach noise. Therefore, heavy complex front edge high support devices that are expensive, maintenance-intensive and suffer from performance-reducing surface discontinuities are replaced by a simpler, lighter and smoother front edge device.
    [0029] [0029] Figure 3 is an illustration of a perspective view of a support surface assembly 300 (e.g., a wing) showing an inclined front edge device 302 (front edge device 302) that exposes a plurality of retractable vortex generators (RVGs) 308, according to a description modality. The support surface assembly 300 may comprise the front edge device 302, the RVGs 308, a hinge 310, a first surface 314 (upper surface 314) (support surface 314), a second surface 316 (lower surface 316), and a hinge actuator mechanism 318.
    [0030] [0030] The support surface assembly 300 may comprise, for example, but without limitation, an aerodynamic body, such as, an aircraft wing, a vertical aircraft tail, an aircraft control surface (such as, an aircraft lift, an aircraft wing, and an aircraft rudder, an airfoil), a race car's support surface, a ship's rudder, an airboat, an engine propeller, a windmill, and the like.
    [0031] [0031] The front edge device 302 comprises a front edge 304, a back edge 306 of the front edge 304, and a bottom surface of the front edge 330. The front edge device 302 comprises a simple hinged sloped front edge device which increases a curvature of the airfoil mount 300 in low speed configurations. As mentioned above, in one embodiment, the front edge device 302 comprises a slanted front edge device that increases a curvature of the airfoil assembly 300 in low speed configurations. Front edge 304 is a first edge of front edge device 302 that encounters medium flow, such as free current air flow 312 in the case of aircraft or racing cars, and water in the case of a rudder by ship.
    [0032] [0032] The front edge device 302 is pivotally coupled to the first surface 314 (upper surface 314) through the joint 310. An aerodynamic surface 334 (dynamic fluid surface 334) can be provided to support the front edge device 302 The streamlined surface 334 acts as an extension of the rear edge 306 when the front edge device 302 is tilted, thereby covering a distance 338 between the rear edge 306 and an edge 340. In the embodiment shown in figure 3, RVGs 308 extend out of the slots 322 in a liner and a distance above the dynamic fluid surface 334 of the support surface assembly 300 when the front edge device 302 is tilted. However, in other embodiments, RVGs may extend out of the cracks in a liner and a distance above the other dynamic surfaces of the fluids of the support surface assembly 300. The rear edge 306 and the edge 340 overlap when the anterior edge 302 is in a fully retracted position (figure 5). The front edge device 302 is operable to tilt and lift using the hinge actuator mechanism 318, as explained in more detail in the context of the discussion of figure 4 below.
    [0033] [0033] In the embodiment shown in figure 3, RVGs 308 comprise mobile vortex generators that can be positioned under the rear edge 304 of the front edge device 302. RVGs 308 are coupled by coupling means 320 to the articulation actuator mechanism 318 In cruise flight, the front edge device 302 is positioned in nominal position 342, which thus covers RVGs 308 (figure 5) and provides a smooth, low drag surface (top surface 314) for mounting surface support 300 (eg, wing). At low speed, as shown in figure 3, the front edge device 302 pivots downward on its hinge 310, which exposes RVGs 308 through slits 322 which then extend into the free current air flow 312. In this way, RVGs 308 through slits 322 energize the free current air flow 312 along the upper surface 314 in a manner similar to a complex slotted system. This action increases low speed performance by delaying the separation of the boundary layer at high angles of attack.
    [0034] [0034] RVGs 308 may comprise various aerofoil-type vortex generators, such as, but without limitation, cogiratory, counter-rotatory, biplane, and the like. 308 RVGs can generally be placed on a single line. However, tandem configurations can also be used. In tandem configurations, a second line of RVGs 308 can be used to re-energize the boundary layer if vortexes from one line have lost their effectiveness. Slots 322 should be wide enough 324 to allow RVGs 308 to be projected through it, however, width 324 should not be so large in order to create an excessively large gap (not shown) between RVGs 308 and an edge of slot 326 of slots 322. RVGs 308 may have, for example, but without limitation, a spacing 328 of about 2.54-25.4 cm (1-10 inches), a height 344 of about 0.254-6 , 35 cm (0.1-2.5 inches) and an imaginary line of about 0.254-7.62 cm (0.1-3 inches).
    [0035] [0035] The first surface 314 can be an upper surface and the second surface 316 can be a lower surface if the airfoil assembly 300 is horizontally oriented, such as, when the assembly 300 is an aircraft wing, a lift. an aircraft or a support surface of a racing car. If the support surface assembly 300 is oriented in a vertical manner, however, the first surface 314 and the second surface 316 may comprise a first side surface and a second side surface.
    [0036] [0036] The hinge actuator mechanism 318 can be located in a gap 336 within the support surface assembly 300 and coupled to an interior of the bottom surface 316 of the front edge device 302. The hinge actuator mechanism 318 can be at least partially covered and surrounded by the upper surface 314 and the lower surface 316. The hinge actuator mechanism 318 is operable to bend the front edge device 302, as explained below.
    [0037] [0037] Figure 4 is an illustration of a side cross-sectional view of a portion of a support surface assembly 400 showing the forward edge slope that exposes a single retractable vortex generator (RVG) 308, according to one embodiment description. The support surface assembly 400 comprises the front edge device 302, the RVG 308, the hinge 310, the upper surface 314, the lower surface 316, the actuator mechanism of the hinge 318, the coupling means 320 and the dynamic surface of the fluids 334. The modality shown in figure 4 may have functions, materials and structures that are similar to the modalities shown in figure 3. Therefore, the common features, functions and elements may not be redundantly described here.
    [0038] [0038] The articulation actuator mechanism 318 is coupled to the front edge device 302 and is operable to arch the front edge device 302 in an upward (elevated) or downward (inclined) direction (if the support surface assembly 300- 400 is horizontally oriented) or in a side-to-side direction (if the support surface mount 300-400 is vertically oriented). The hinge actuator mechanism 318 causes the front edge device 302 to be extended from a nominal position 402 (342 in figure 3) to an inclined position 404 (deflected position 404). The front edge device 302 pivotably pivots around the hinge 310 from the nominal position 402 to the inclined position 404 to expose the RVG 308. In the embodiment shown in figure 4, a rotation angle α of the front edge device 302 it can vary, for example, but without limitation, 0-30 degrees, and the like. Any actuation mechanism known in the art suitable for extending / retracting the front edge device 302 can be used.
    [0039] [0039] The RVG 308 is substantially covered, when the front edge device 302 is in the nominal position 402 in relation to the support surface 314, and the RVG 308 is exposed to a variable distance in a boundary layer and capable of generating vortexes in the boundary layer on a portion of the support surface 314 during flight when the RVG 308 is in the deflected position 404 relative to the support surface 314.
    [0040] [0040] The joint that couples the front edge device 302 to the support surface assembly 400 provides the front edge hinged 302. Therefore, in this document, the terms front edge device 302 and hinged front edge 302 can be used interchangeably . Also, the hinged front edge 302 provides an exposed RVG 308 and a covered RVG 308 (figure 5) when the hinged front edge 302 is tilted and elevated, respectively. Therefore, in this document, the terms RVG 308, RVG 308 exposed and RVG 308 covered can be used interchangeably.
    [0041] [0041] In practice, in a low speed flight condition, the hinged front edge 302 rotates at its hinge 310, which exposes the RVG 308 to provide the exposed RVG 308 which then extends to the current air flow free 312, and in a cruising flight condition, the hinged leading edge 302 covers the RVG 308 to provide the covered RVG 308 that provides a smooth low drag airfoil mounting surface 400.
    [0042] [0042] Figures 5 to 8 are sequential illustrations of the perspective views of the support surface assembly 500/600/700/800 showing the front edge device 302 of the support surface assembly 300/400 in various positions, from according to a description mode. The modalities shown in figures 5 to 8 can have functions, materials and structures that are similar to the modalities shown in figures 3-4. Therefore, common features, functions and elements may not be redundantly described here.
    [0043] [0043] In practice, RVGs 308 extend through the support surface assembly 300 to increase lift when the front edge device 302 is tilted, and RVGs 308 retract within the support surface assembly 300 to decrease drag, when the hinged front edge 302 is raised.
    [0044] [0044] Figure 5 is an illustration of a perspective view of the support surface assembly 500 (for example, wing) showing the smooth top surface 314 and the bottom surface 316 in the cruise configuration with RVGs 308 hidden under a angled hinged leading edge, such as the leading edge device 302, according to a description mode.
    [0045] [0045] Figure 6 is an illustration of a perspective view of a support surface assembly 600 showing the front edge device 302 tilted at an initial angle of rotation α of about 5 degrees that exposes the RVGs 308 through the slots 322, according to a description mode.
    [0046] [0046] Figure 7 is an illustration of a perspective view of a support surface assembly 700 showing the front edge device 302 tilted at an intermediate level angle of rotation α of about 15 degrees that extends the RVGs 308 out of the slits 322 in the liner of the aerodynamic surface 334, according to a description mode.
    [0047] [0047] Figure 8 is an illustration of a perspective view of a support surface assembly 800 showing the front edge device 302 tilted at a fully extended angle of rotation α of about 30 degrees that exposes and fully extends the RVGs 308 out of the slits 322, according to a description mode.
    [0048] [0048] As explained above, figures 5 to 8 show the exemplary deflection / inclination of the front edge device 302 at various angles of rotation α in a range of about 0-30 degrees. However, other angles of rotation α can also be used to expose the RVGs 308. The front edge device 302 can be tilted by exposing the RVGs 308 to facilitate access to maintenance in an interior of the 300/400 support surface assembly. / 500/600/700/800, such as, but without limitation, an interior of a wing, and the like, according to a description mode. In this way, complexity is reduced compared to existing solutions, such as removable bottom panels.
    [0049] [0049] Figure 9 is an illustration of an example flowchart showing a 900 process to improve the low speed performance of the 300/400/500/600/700/800 airfoil assembly using RVGs 308, from according to a description mode. The various tasks performed in connection with the 900 process can be performed mechanically, by software, hardware, firmware, or a combination of them. For illustrative purposes, the following description of process 900 can refer to the elements mentioned above in connection with figures 3 to 9. In practical embodiments, portions of process 900 can be realized by the front edge device 302, RVGs 308, a hinge 310, first surface 314, second surface 316, hinge actuator mechanism 318, dynamic fluid surface 334, etc. The 900 process can have functions, materials and structures that are similar to the modalities shown in figures 3 to 8. Therefore, the common features, functions and elements may not be redundantly described here.
    [0050] [0050] Process 900 can begin by coupling at least one retractable vortex generator, such as the RVG 308 to a support surface assembly, such as the support surface assembly 300 (task 902).
    [0051] [0051] Process 900 can continue through the hinge coupling of a front edge device, such as the front edge device 302 to the support surface assembly 300 to provide the hinged front edge 302 (task 904).
    [0052] [0052] Process 900 may continue to extend the RVG 308 through the support surface assembly 300 to increase support by tilting an articulated front edge, such as the articulated front edge 302 coupled to the support surface assembly 300 (task 906).
    [0053] [0053] Process 900 may continue to retract RVG 308 within the support surface assembly 300 to decrease drag (task 908).
    [0054] [0054] Process 900 can then continue through the RVG 308 exposure by tilting the hinged front edge 302 (task 910) to provide an exposed vortex generator 308. In this way, the exposed vortex generator 308 energizes a flow of air along the upper surface 314 of the airfoil assembly 300, delaying a separation of the airflow boundary layer at a high angle of attack from the airfoil assembly 300. The exposed vortex generator 308 provides a speed of lower loss for support surface mounting 300.
    [0055] [0055] Process 900 can continue coupling the front hinged edge 302 to the RVG 308, so that the front hinged edge 302 extends the RVG 308 through the mounting surface 300 (task 912).
    [0056] [0056] Process 900 can continue coupling the front hinged edge 302 to the RVG 308, so that the elevation of the front hinged edge 302 retracts the RVG 308 within the support surface assembly 300 (task 914).
    [0057] [0057] Process 900 can continue to cover the RVG 308 by raising the articulated anterior edge 302 (task 916). In this way, the covered vortex generator 308 reduces cruising drag.
    [0058] [0058] Figure 10 is an illustration of an exemplary flowchart showing a process for operating an airfoil assembly to provide improved low speed performance, according to a description mode. The various tasks performed in connection with process 1000 can be performed mechanically, by software, hardware, firmware, or a combination of these. For illustrative purposes, the following description of process 1000 can refer to the elements mentioned above in connection with figures 3 to 8. In practical modalities, portions of process 1000 can be realized by the front edge device 302, by RVGs 308, by articulation 310, the first surface 314, the second surface 316, the actuator mechanism of the articulation 318, the dynamic surface of the fluids 334, etc. Process 1000 can have functions, materials and structures that are similar to the modalities shown in figures 3 to 9. Therefore, the common features, functions and elements may not be redundantly described here.
    [0059] [0059] Process 1000 can begin to cause a fluid to flow along a support surface assembly, such as the support surface assembly 300 (task 1002). In this way, process 1000 can cause the airfoil assembly 300 to move through the fluid or cause the fluid to move along the airfoil assembly 300. In a mode in which the airfoil assembly lift 300 comprises an aircraft wing or tail of a race car support surface, the medium is air. In a case where the support surface assembly 300 is a ship's rudder, the medium is water.
    [0060] [0060] Process 1000 may then continue to tilt (deflect) a leading edge device, such as the leading edge device 302 hinged to a surface, such as the first surface 314 of the support surface assembly 300 to from nominal position 402 to deflected / inclined position 404 (task 1004).
    [0061] [0061] Process 1000 may then continue through one or more RVGs, such as RVGs 308 extended or exposed at a distance (not shown) beyond the dynamic surface of fluids 334 of the support surface assembly 300 in response to inclination of the front edge device 302 (task 1006). In one embodiment, RVGs 308 may extend or be exposed a distance (not shown) beyond the first surface 314 of the support surface assembly 300 in response to deflection / inclination.
    [0062] [0062] Process 1000 can then continue through one or more RVGs that cause a vortex to be generated within the fluid (not shown) (task 1008), which is flowing along the support surface assembly 300.
    [0063] [0063] Process 1000 can then continue to vary a magnitude / angle of rotation α from an inclined position of the front edge device 302 (task 1010).
    [0064] [0064] The front edge device 302 in the inclined position increases the curvature and the extended RVGs 308 energize the air flow along the upper surface 314. In this way, the flow separation is delayed increasing the low speed performance of the mounting of support surface 300 by retracting a separation of the boundary layer at high angles of attack. This, in turn, slows down a "loss speed" and in the case of the aircraft, causes optimal flight conditions when operating at low speeds and low altitudes associated, for example, with takeoff and landing.
    [0065] [0065] In this way, several modalities of the description provide a device and methods to reduce the "loss speed" of a support surface assembly by extending the retractable vortex generators through the support surface assembly by tilting a articulated anterior edge coupled to the support surface assembly. In this way, heavy complex front edge high support devices that are expensive, maintenance-intensive and suffer from performance-reducing surface discontinuities are replaced by a simpler, lighter and smoother front edge device.
    [0066] [0066] Although at least one exemplary modality has been presented in the previous detailed description, it must be appreciated that there are a wide number of variations. Also, it should be assessed that the modality or exemplary modalities described in this document are not intended to limit the scope, applicability or configuration of the subject in question in any way. Preferably, the preceding detailed description will provide those skilled in the art with a convenient road map to implement the described modality or modalities. It should be understood that several changes can be made in the function and arrangement of the elements without departing from the scope defined by the claims, which includes known equivalents and equivalents provided at the time of filing this patent application.
    [0067] [0067] The above description refers to the elements, nodes or resources that are "connected" or "coupled" to each other. As used in this document, except where expressly stated otherwise, "connected" means that an element / node / resource is directly linked (or communicates directly with) to another element / node / resource, and not necessarily mechanically. Likewise, except where expressly stated otherwise, "coupled" means that an element / node / resource is directly or indirectly joined (or communicates directly or indirectly with) another element / node / resource, and not necessarily mechanically. Thus, although figures 3 to 8 show exemplary arrangements of elements, elements, devices, resources or additional intervening components, they may be present in one embodiment of the description.
    [0068] [0068] The terms and phrases used in this document, and variations thereof, except where expressly stated otherwise, must be constructed open in opposition to the limitation. As examples of what has been said previously: the term "that includes" should be read as "that includes, without limitation", or similar; the term "example" is used to provide exemplary instances of the item under discussion, not an exhaustive or limiting list of them; and adjectives such as "conventional", "traditional", "normal", "standard", "known" and similar terms should not be constructed by limiting the item described in a given period of time to an item available from a certain time, but should instead be read covering conventional, traditional, standard or standard technologies that may be available or known now or at any time in the future.
    [0069] [0069] Likewise, a group of items linked to the conjunction "e" should not be read requiring each and all of these items to be present in the grouping, but preferably should be read as "and / or", except where expressly otherwise stated. Similarly, a group of items linked to the conjunction "or" should not be read requiring mutual exclusivity between this group, but should preferably also be read as "and / or", except where expressly stated otherwise. In addition, although the items, elements or components of the description can be described or claimed in the singular, the plural is contemplated within the scope of the same, except where the limitation to the singular is explicitly established.
    [0070] [0070] The presence of enlarged words and phrases, such as, "one or more", "at least", "but, not limited to" or other phrases in some instances should not be read in the sense of the narrower intended case or required in instances where such extended sentences may be absent. The term "about" when referring to a numerical value or range is intended to cover the values that result from the experimental error that can occur when measurements are taken.
    [0071] [0071] As used in this document, except where expressly stated otherwise, "operable" means capable of being used, adjusted or ready for use or service, useful for a specific purpose, and capable of performing a function mentioned or desired described in this document. In relation to systems and devices, the term "operable" means that the system and / or the device is fully functional and calibrated, comprises elements and meets the applicable operability requirements to perform a function mentioned when activated.
    权利要求:
    Claims (20)
    [0001]
    Method for improving the low speed performance of a support surface assembly (300), the method characterized by the fact that it comprises: coupling at least one vortex generator (308) to a support surface assembly (300); extending a front edge device (302) of the support surface assembly (300) from a nominal position (342) to a deflected position (404); extending at least one vortex generator (308), pivotally coupled to the front edge device (302) through at least one slot (322) on a surface of the airfoil assembly (300); retract the at least one vortex generator (308) within the airfoil assembly (300) to decrease drag; retract the at least one vortex generator (308) under the surface in response to the movement of the front edge device (302) to the nominal position (342); and cover the at least one vortex generator (308) with the front edge device (302) in response to the movement of the front edge device (302) to the nominal position (342).
    [0002]
    Method, according to claim 1, characterized by the fact that it also comprises: exposing at least one vortex generator (308) by tilting an articulated front edge (304), where the front edge device (302) is pivotally coupled to the support surface assembly (300) to provide the edge articulated anterior (304).
    [0003]
    Method according to claim 2, characterized by the fact that it also comprises raising the articulated front edge (304) to retract the at least one vortex generator (308) under the support surface assembly (300).
    [0004]
    Method according to claim 1, characterized by the fact that it further comprises covering at least one vortex generator (308) and at least one slot (322) with the articulated front edge (304).
    [0005]
    Method according to claim 2, characterized in that tilting the hinged leading edge (304) increases a curvature of the support surface assembly (300).
    [0006]
    Method according to claim 2, characterized by the fact that tilting the articulated anterior edge (304) rotates the articulated anterior edge (304) in its articulation (310) to expose at least one vortex generator (308).
    [0007]
    Method, according to claim 1, characterized by the fact that the surface comprises an aerodynamic surface (334) coupled to a first surface (314) of the support surface assembly (300), the aerodynamic surface (334) configured to be covered by the front edge device (302) when the edge device front (302) is in the nominal position (342), the aerodynamic surface (334) is further configured to extend between the front edge device (302) and the first surface (314) when the front edge device (302) is in the deflected position (404); extending the at least one vortex generator (308) comprises extending the at least one vortex generator (308) through the at least one slot (322) in the aerodynamic surface (334); and retracting the at least one vortex generator (308) comprises retracting the at least one vortex generator (308) below the aerodynamic surface (334).
    [0008]
    Method according to claim 1, characterized in that the at least one vortex generator (308) is positioned under a rear edge (306) of the front edge device (302) when the front edge device (302) is in nominal position (342).
    [0009]
    Method according to claim 8, characterized by the fact that it still comprises overlapping a surface edge by the rear edge (306) when the front edge device (302) is in the nominal position (342).
    [0010]
    Retractable vortex generating device (308) characterized by the fact that it comprises: a front edge device (302) coupled to a support surface (300), wherein a hinged front edge (304) is attached to the support surface (300); an aerodynamic surface (334) coupled to the support surface (300) and configured to be covered by the front edge device (302) when the front edge device (302) is in a nominal position (342); at least one vortex generating device (308) coupled to the support surface (300), and operable for: extends through at least one slot (322) in the support surface (300) or the aerodynamic surface (334) in response to the front edge device (302) being tilted; if it retracts under the support surface (300) or the aerodynamic surface (334) in response to the front edge device (302) being raised; and retract into the support surface (300) to decrease drag, when the hinged leading edge (304) is raised.
    [0011]
    Retractable vortex generating device (308) according to claim 10, characterized in that the at least one vortex generating device (308) is configured to be disposed under a rear edge (306) of the front edge device ( 302) when the front edge device (302) is in the nominal position (342).
    [0012]
    Retractable vortex generating device (308) according to claim 10, characterized in that the at least one vortex generating device is articulably coupled to one or more of the support surface (300), and the device front edge (302).
    [0013]
    Retractable vortex generating device (308) according to claim 10, characterized in that the front edge device (302) is configured to cover at least one vortex generating device (308).
    [0014]
    Retractable vortex generating device (308) according to claim 10, characterized in that the front edge device (302) is configured to increase the curvature of the support surface (300) when the front edge device (302) ) is positioned in an inclined position (404).
    [0015]
    Retractable vortex generating device (308), according to claim 10, characterized in that the support surface (300) comprises at least the element selected from the group consisting of: an aircraft wing, a surface of aircraft control, an airboat and a ship's helm.
    [0016]
    Retractable vortex generating device (308) according to claim 10, characterized by the fact that the front edge device (302) is pivotally coupled to the support surface (300).
    [0017]
    Retractable vortex generating device (308) according to claim 10, characterized by the fact that the front edge device (302) comprises a non-slit front edge device (302).
    [0018]
    Retractable vortex generating device (308) according to claim 10, characterized in that the front edge device (302) is configured to cover at least one vortex generating device (308) and at least one slot (322) when the front edge device (302) is in the nominal position (342), a rear edge (306) of the front edge device (302) overlapping a surface edge.
    [0019]
    Method for operating an airfoil assembly (300) to provide improved low speed performance, the method characterized by the fact that it comprises: causing a fluid to flow along the support surface assembly (300); tilting a front edge device (302) hingedly coupled to a first surface (314) of the support surface assembly (300) from a nominal position (342) to a deflected position (404); exposing a plurality of retractable vortex generating devices (308) at a distance beyond a dynamic fluid surface and through a plurality of slits (322) in a first surface (314) of the support surface assembly (300) in response at the inclination of the front edge device (302), the retractable vortex generating devices (308) configured to be covered by a rear edge (306) of the front edge device (302) when the front edge device (302) is in the nominal position (342); cause a vortex to be generated within the fluid; and varying a magnitude of an inclined position (404) of the front edge device (302); and retract the vortex generating devices (308) through the slits (322) by moving the front edge device (302) to the nominal position (342).
    [0020]
    Method, according to claim 19, characterized by the fact that the front edge device (302) and at least one vortex generating device (308) are attached in a fixed manner using a pivoting actuator mechanism to raise and lower, respectively, the vortex generating devices (308) above and below the first surface (314), respectively.
    类似技术:
    公开号 | 公开日 | 专利标题
    BR102012016563B1|2021-01-12|method for improving low speed performance of an airfoil assembly, retractable vortex generating device and method for operating an airfoil assembly
    US10583909B2|2020-03-10|Aircraft comprising a foldable aerodynamic structure and a method of manufacturing a foldable aerodynamic structure for an aircraft
    EP2398704B1|2014-04-02|Aircraft wing load alleviation system
    EP2669190B1|2017-05-10|Rotary actuated high lift gapped aileron
    US6264136B1|2001-07-24|High efficiency combination wing aircraft
    US9505485B2|2016-11-29|Vortex generation
    US8128038B2|2012-03-06|High-lift device for an aircraft
    US20110260008A1|2011-10-27|Fluid flow control device for an aerofoil
    JP2009516615A|2009-04-23|Aircraft trailing edge apparatus including apparatus with non-parallel motion trajectories and associated methods
    Lee et al.2019|Numerical investigation of the aerodynamics and wake structures of horizontal axis wind turbines by using nonlinear vortex lattice method
    US11084566B2|2021-08-10|Passively actuated fluid foil
    Chowdhury et al.2020|The lift force produced by an unsteady translating plate with a rotating tip
    Lazos2005|Biologically inspired fixed-wing configuration studies
    CN106467164B|2022-01-14|Mitigating surface discontinuities between a flight control surface and a fuselage of an aircraft
    Traub et al.2019|Experimental Investigation of an Annular Tri-Wing Geometry
    Huber et al.2017|Experimental aerodynamic assessment and evaluation of an agile highly swept aircraft configuration
    Maqsood et al.2013|Parametric studies and performance analysis of a biplane micro air vehicle
    US20180339770A1|2018-11-29|Rotor assemblies and related control systems
    RU2128129C1|1999-03-27|Deflector-vortex generator
    Keller et al.2019|Numerical Investigation of the Aerodynamic Behavior of a Generic Light Aircraft
    US20190375492A1|2019-12-12|Fan-in-wing aerial vehicle and method for controlling posture thereof
    WO2015183347A2|2015-12-03|Flap design for fixed wing aircraft
    BR102013007323B1|2021-10-05|HELICOPTER ROTOR BLADE SYSTEM AND METHOD FOR OPERATING HELICOPTER ROTOR BLADE SYSTEM
    Naik1987|An investigation of the aerodynamic characteristics of planar and non-planar outboard wing planforms
    Elkaim2008|Airfoil section design and configuration analysis of a free-rotating wing-sail for an autonomous marine surface vehicle
    同族专利:
    公开号 | 公开日
    EP2543588B1|2017-08-09|
    US20130009016A1|2013-01-10|
    IL219688A|2018-05-31|
    RU2012127684A|2014-01-10|
    CN102862674B|2015-02-25|
    US8657238B2|2014-02-25|
    RU2600014C2|2016-10-20|
    CA2774821A1|2013-01-05|
    IL219688D0|2012-07-31|
    CA2774821C|2017-03-28|
    CN102862674A|2013-01-09|
    EP2543588A1|2013-01-09|
    BR102012016563A2|2014-05-27|
    ES2646445T3|2017-12-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1070723A|1963-01-16|1967-06-01|Dehavilland Aircraft|Improvements in or relating to aircraft|
    US4039161A|1975-10-16|1977-08-02|Mcdonnell Douglas Corporation|Hidden vortex generators|
    US5054720A|1989-09-18|1991-10-08|Mcdonnell Douglas Corporation|Trapped vortex cavity|
    US5253828A|1992-07-17|1993-10-19|The Board Of Regents Of The University Of Oklahoma|Concealable flap-actuated vortex generator|
    US5598990A|1994-12-15|1997-02-04|University Of Kansas Center For Research Inc.|Supersonic vortex generator|
    CN101213131A|2005-06-30|2008-07-02|贝尔直升机特克斯特龙有限公司|Retractable vortex generator|EP2548800A1|2011-07-22|2013-01-23|LM Wind Power A/S|Method for retrofitting vortex generators on a wind turbine blade|
    US9505485B2|2012-05-08|2016-11-29|Lockheed Martin Corporation|Vortex generation|
    US8708286B2|2012-06-21|2014-04-29|The Boeing Company|Swing tip assembly rotation joint|
    CA2899238A1|2013-01-25|2014-07-31|Peter Ireland|Energy efficiency improvements for turbomachinery|
    US9638176B2|2013-05-10|2017-05-02|The Boeing Company|Vortex generator using shape memory alloys|
    US9145801B2|2013-07-01|2015-09-29|The Boeing Company|Systems and methods for acoustic resonance mitigation|
    US9593670B2|2014-04-30|2017-03-14|General Electric Company|System and methods for reducing wind turbine noise|
    US9868516B2|2014-12-12|2018-01-16|Lockheed Martin Corporation|Adhesive panels of microvane arrays for reducing effects of wingtip vortices|
    US20160232741A1|2015-02-05|2016-08-11|Igt Global Solutions Corporation|Lottery Ticket Vending Device, System and Method|
    DE102015101763A1|2015-02-06|2016-09-01|Airbus Operations Gmbh|Vertical stabilizer for an aircraft|
    DE102015101765A1|2015-02-06|2016-08-11|Airbus Operations Gmbh|Vortex generator arrangement|
    US20160298600A1|2015-04-08|2016-10-13|Frontier Wind, Llc|Load Compensating Devices|
    US10507906B2|2015-04-28|2019-12-17|The Boeing Company|Aerodynamic surface assembly defining a fluidic actuation orifice|
    US10259566B1|2016-06-13|2019-04-16|James Randolph Lawrence|Rolling vortex wing slat system and method of use|
    ES2797681T3|2016-11-25|2020-12-03|Airbus Operations Sl|Lift surface of an aircraft to increase the lift force generated|
    ES2763558T3|2017-01-17|2020-05-29|Airbus Operations Sl|Supporting surface|
    FR3073017B1|2017-10-30|2021-07-30|Safran Aircraft Engines|MEMBRANE WITH ACTUATORS FOR DAWN ATTACK EDGE|
    EP3552959A1|2018-04-13|2019-10-16|Airbus Defence and Space GmbH|Aerodynamics influencing device for an aircraft and aircraft|
    US10889370B2|2018-07-02|2021-01-12|Textron Innovations Inc.|Chord-wise variable vortex generator|
    CN110844050A|2019-11-02|2020-02-28|南京理工大学|Needle-shaped vortex generator in leading edge slat gap|
    KR102217639B1|2019-12-20|2021-02-22|온톨로지|Unmanned aerial vehicle with drag reduction structure|
    CN111891339A|2020-06-22|2020-11-06|成都飞机工业（集团）有限责任公司|Vortex generator and method for delaying stall attack angle of high-aspect-ratio wing|
    法律状态:
    2014-05-27| B03A| Publication of an application: publication of a patent application or of a certificate of addition of invention|
    2014-08-12| B03H| Publication of an application: rectification|Free format text: REFERENTE A RPI 2264 DE 27/05/2014, QUANTO AO ITEM 54. |
    2018-12-11| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-12-17| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-09-01| B06A| Notification to applicant to reply to the report for non-patentability or inadequacy of the application according art. 36 industrial patent law|
    2020-11-24| B09A| Decision: intention to grant|
    2021-01-12| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 04/07/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/176,539|2011-07-05|
    US13/176,539|US8657238B2|2011-07-05|2011-07-05|Retractable vortex generator for reducing stall speed|
    [返回顶部]