| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS | EP00944573.5 | 2000-02-25 | EP1156962B1 | 2004-06-02 | MCCORMICK, Duane, C.; GYSLING, Daniel, L. |
| 182 | DESIGN OF VISCOELASTIC COATINGS TO REDUCE TURBULENT FRICTION DRAG | EP01927412.5 | 2001-03-20 | EP1272387A1 | 2003-01-08 | MAY, Carol, L.; VOROPAYEV, Gennadiy A. |
| A method is provided to select appropriate material properties for turbulent friction drag reduction, given a specific body (1), configuration and freestream velocity (2). The method is based on a mathematical description of the balance of energy at the interface between the viscoelastic surface and the moving fluid, and permits determination of the interaction of turbulent boundary layer fluctuations with a viscoelastic layer by solving two subtasks -- i.e., a hydrodynamic problem and an elasticity problem, which are coupled by absorption and compliancy coefficients. Displacement, velocity, and energy transfer boundary conditions on a viscoelastic surface are determined, and a Reynolds stress type turbulence model is modified to account for redistribution of turbulent energy in the near-wall of the boundary layer. The invention permits drag reduction by a coating with specified density, thickness, and complex shear modulus to be predicted for a given body geometry and freestream velocity. For practical applications, viscoelastic coatings may be combined with additional structure, including underlying wedges to minimize edge effects for coatings of finite length, and surface riblets, for stabilization of longitudinal vortices. | ||||||
| 183 | VORRICHTUNG ZUR BRECHUNG VON STRÖMUNGSWIRBELN AN EINER TURBULENT UMSTRÖMTEN FLÄCHE | EP95931133.3 | 1995-09-13 | EP0870116B1 | 2002-10-09 | FREMEREY, Johan, K.; POLACHOWSKI, Stephan; REIFF, Heinrich |
| In order to break whirls at a surface submerged by a tangential turbulent flow (9), a wall (11) extends parallel to the surface, at a certain distance (12) therefrom, and is provided with periodically arranged structural elements. The distance (12) between the wall and the submerged surface determines the maximum still admissible whirl size and the size and spacing of the structural elements correspond to the length of the distance between the wall and the submerged surface. | ||||||
| 184 | PASSIVELY DRIVEN ACOUSTIC JET CONTROLLING BOUNDARY LAYERS | EP00925864.1 | 2000-02-25 | EP1156961A1 | 2001-11-28 | MCCORMICK, Duane, C.; LORD, Wesley, K. |
| Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage. | ||||||
| 185 | Rumpfnase zur Steuerung von Fluggeräten | EP99115190.3 | 1999-08-16 | EP0980823A3 | 2001-08-22 | Hakenesch, Peter, Dr. |
Steuerungseinrichtung für Fluggeräte mit einem Rumpfnasensegment (3) und zumindest einem Strake (5, 6), wobei das Rumpfnasensegment (3) rotatorisch gegenüber dem Flugzeugrumpf (1) verstellbar ist und der zumindest ein Strake (5, 6) an dem Rumpfnasensegment (3) ausklappbar angebracht ist. |
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| 186 | Aircraft airconditioning energy recovery device | EP99500060.1 | 1999-04-15 | EP0974515A3 | 2000-04-26 | Munoz Saiz, Manuel |
The aircraft air conditioning energy recovery device exploits the high level energy in relation to the exterior, in the air conditioning air flow required for renewal, and involves the placement of the aircraft outflow valve in a duct through which all the air flows said duct being arranged from the pressurized cabin to the inside of the engine inlet diffuser (30), through the pylon (28) and in some cases through the wing (27), with said air-conditioning flow being fed back to the input air flow through multiple openings on the inside wall of the inlet diffuser (30). Said openings or grooves run at a slight angle to the direction of flow to avoid turbulence.The air conditioning input may be introduced through hollow radial guide vanes (33) attached at the front end to the vanes (33) of the first stage of the low-pressure compressor (35) and to the hollow vanes (36), open at the back, in the first stage or stages of the low-pressure compressor stator where the pressure is lower than that of the cabin air. |
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| 187 | Rumpfnase zur Steuerung von Fluggeräten | EP99115190.3 | 1999-08-16 | EP0980823A2 | 2000-02-23 | Hakenesch, Peter, Dr. |
Steuerungseinrichtung für Fluggeräte mit einem Rumpfnasensegment (3) und zumindest einem Strake (5, 6), wobei das Rumpfnasensegment (3) rotatorisch gegenüber dem Flugzeugrumpf (1) verstellbar ist und der zumindest ein Strake (5, 6) an dem Rumpfnasensegment (3) ausklappbar angebracht ist. |
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| 188 | Method and arrangement for fluidborne vehicle propulsion and drag reduction | EP98202072.9 | 1998-06-22 | EP0887259A2 | 1998-12-30 | Chapman, John H. |
A body having a propulsion system comprising an inlet (7, 29, 46) and means (6, 28, 43, 45) for drawing fluid through said inlet to be used to propel said body characterised in that said inlet (7, 29, 46) is disposed along a substantial portion of the area of said body where boundary layer separation would otherwise occur at a predetermined speed. |
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| 189 | VORRICHTUNG ZUR BRECHUNG VON STRÖMUNGSWIRBELN AN EINER TURBULENT UMSTRÖMTEN FLÄCHE | EP95931133.0 | 1995-09-13 | EP0870116A1 | 1998-10-14 | FREMEREY, Johan, K.; POLACHOWSKI, Stephan; REIFF, Heinrich |
| In order to break whirls at a surface submerged by a tangential turbulent flow (9), a wall (11) extends parallel to the surface, at a certain distance (12) therefrom, and is provided with periodically arranged structural elements. The distance (12) between the wall and the submerged surface determines the maximum still admissible whirl size and the size and spacing of the structural elements correspond to the length of the distance between the wall and the submerged surface. | ||||||
| 190 | AEROFOIL WITH VARIABLE GEOMETRY EXPANSION SURFACE | EP92916427.0 | 1992-07-28 | EP0596976A1 | 1994-05-18 | ASHILL, Patrick, Ralph; FULKER, John, Leslie Woodcote Lodge Road |
| PCT No. PCT/GB92/01396 Sec. 371 Date May 25, 1994 Sec. 102(e) Date May 25, 1994 PCT Filed Jul. 28, 1992 PCT Pub. No. WO93/02915 PCT Pub. Date Feb. 18, 1993.A wing, or similar article of airfoil section, has a variable geometry surface for the active control of shock strength and transonic wave drag. In one embodiment, the wing has a region of distensible skin (4) aft of the line of maximum section, which extends along the span of the wing in those areas that experience drag. Pressure means (10, 20, 30) within the wing outwardly deflect the distensible region and produce a local bulge in the expansion surface. This bulge induces pre-shock compression and reduces the effect of the shock. The bulge is retracted by the natural elasticity of the skin material (which can be a conventional aluminum alloy) upon removal of the applied pressure. In another embodiment, the wing has a ramp portion (14) which is outwardly deflectable for the same purpose. The invention is applicable to supercritical and natural laminar flow wings. | ||||||
| 191 | VENTURI ENHANCED AIRFOIL | EP88907492 | 1988-06-23 | EP0319574A4 | 1990-09-05 | WILLIS, MARK T. |
| A basic airfoil has its operating performance improved by incorporating one or more apertures in the airfoil adjacent its trailing edge. These apertures (24) extend from the upper surface (18) of the airfoil down through to the lower surface (20) of the airfoil. The entry port (25) and the exit port (26) of these apertures (24) has a greater circumference than that of the throat (27) circumference which is intermediate thereto. This structure forms a venturi having a vertical axis. Spaced below the throat (27) of the aperture (24) are a plurality of air nozzles (30) that communicate with an air plenum chamber (32) within the airfoil. A source of pressurized air (35) is connected to the plenum chamber (32). The venturi enhanced airfoil can be utilized both in a horizontal fixed airfoil or its structure can also be incorporated into the tail rudder (53) of an aircraft or helicopter. The venturi enhanced airfoil can be oriented in any position between the horizontal and vertical axes. | ||||||
| 192 | Gas turbine engine airfoil | EP87630267.0 | 1987-12-14 | EP0273851A2 | 1988-07-06 | Werle, Michael J.; Presz, Walter Michael, Jr.; Paterson, Robert W. |
An airfoil (400) has a plurality of spaced apart, U-shaped troughs (408,410) in either or both its suction or pressure surface (402,404) in the trailing edge region. Each trough (408,410) extends in a direction generally parallel to the bulk fluid flow in its vicinity near the airfoil surface and has an outlet at the trailing edge (406). The troughs (408,410) increase in depth from their inlets toward their outlets, the maximum depth being no more than half the trailing edge thickness. The troughs (408,410) are spaced apart, sized and configured to flow full over their entire length and to cause fluid to flow into the space immediately behind the trailing edge (406), thereby reducing base drag. |
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| 193 | Control of laminar flow in fluids by means of acoustic energy | EP87201608.4 | 1987-08-25 | EP0264144A2 | 1988-04-20 | Mangiarotty, Rudolph A. |
Retarding of the point of transition (3) from laminar flow (2) to turbulent flow (4) in aerodynamic boundary layers on the surfaces (1) of aircraft is accomplished by radiating acoustic energy at frequencies greater than twice the critical Tollmein-Schlichting frequency into the boundary layer. The acoustic energy interferes with the formation of Tollmein-Schlichting waves, thereby increasing the incidence of laminar flow and reducing aerodynamic drag. |
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| 194 | Helicopter | EP83303477 | 1983-06-15 | EP0099185A3 | 1985-07-03 | Brocklehurst, Alan; Cook, Christopher Vincent |
To improve the sideways flight characteristics of a helicopter having a main sustaining rotor and a rearwardly extending tail boom carrying an anti-torque rotor adjacent a rear end thereof, prevention means is incorporated to prevent attached airflow around the tail boom. In the described embodiment, the prevention means comprise a longitudinally extending metal strip (23) protruding from an upper surface of the tail boom. |
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| 195 | Orthosonic thrust apparatus and method | US14269088 | 2014-05-03 | US10037752B1 | 2018-07-31 | David A Colasante |
| An acoustically resonating medium has one or more nodes and anti-nodes. Insulating a first side of a resonating medium at a node from ambient air and exposing the opposite second side of the resonating medium at the node to ambient air results in thrust in the direction of the first side. Insulating the second side of a resonating medium at an anti-node from ambient air and exposing the first side of the medium at the anti-node to ambient air also results in thrust in the direction of the first side. | ||||||
| 196 | Multifunctional erosion protection strip | US14646050 | 2013-11-20 | US10035578B2 | 2018-07-31 | Pontus Nordin; Göte Strindberg |
| An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system. | ||||||
| 197 | METHOD FOR MASKING A SOUND SIGNAL GENERATED BY AN ELEMENT OF THE SKIN OF AN AIRCRAFT | US15661328 | 2017-07-27 | US20180033418A1 | 2018-02-01 | Nicolas Molin; Isabelle Boullet |
| A masking method includes: a step of choosing a generating element which is part of the skin of an aircraft, a first step of measuring a fundamental frequency of a sound signal emitted by the generating element, a step of selecting a masking element which is part of the skin, a second step of measuring a fundamental frequency of another sound signal emitted by the masking element, a step of modification of the structure of the masking element in such a way as to shift the fundamental frequency of the sound signal emitted by the masking element to a frequency lower than the fundamental frequency of the sound signal emitted by the generating element. Such a masking method thus makes it possible to mask the sound signal emitted by the generating element by the sound signal emitted by the masking element. | ||||||
| 198 | Methods of Dynamically Controlling Airflow Behind a Carrier Aircraft to Redirect Air Flow During an In-flight Recovery of an Unmanned Aerial Vehicle and an Apparatus Therefor | US15166732 | 2016-05-27 | US20170341735A1 | 2017-11-30 | Roger D. Bernhardt; Alexander D. Lee; Ryan L. Hupp; Abraham N. Gissen; Benjamin A. Rothacker |
| An apparatus is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. | ||||||
| 199 | Optical effects for aerodynamic microstructures | US14705547 | 2015-05-06 | US09751618B2 | 2017-09-05 | Diane C. Rawlings; Timothy Leroy Williams; James C. McGarvey; James M. Kestner; Alan G. Burg |
| Aerodynamic microstructures having sub-microstructure are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure defining an external surface of a vehicle, and a pattern of sub-microstructures superimposed on the microstructure to convey a representation of an image. | ||||||
| 200 | Mitigating shock using plasma | US14936953 | 2015-11-10 | US09725159B2 | 2017-08-08 | Mark Joseph Clemen, Jr.; Donald V. Drouin, Jr.; Alan F. Stewart |
| A method, apparatus, and system for mitigating undesired effects of a vehicle traveling at a speed greater than a critical Mach number for the vehicle. Ultraviolet energy is generated using a plurality of ultraviolet energy sources associated with an interior structure of the vehicle that travels at the speed greater than the critical Mach number for the vehicle. The ultraviolet energy is transported from the plurality of ultraviolet energy sources past an exterior of the vehicle around a selected location of the vehicle. A plasma is created around the selected location to mitigate the undesired effects of the vehicle traveling at the speed greater than the critical Mach number for the vehicle. | ||||||
