[특허]Apparatus and method for the control of trailing wake flows

The Boeing Company

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Apparatus and method for the control of trailing wake flows

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/00
미국특허분류(USC)	244/199.3; 244/207
출원번호	UP-0332835 (2006-01-13)
등록번호	US-7597289 (2009-10-20)
발명자 / 주소	Shmilovich, Arvin Yadlin, Yoram Clark, Roger Leopold, Donald
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 2 인용 특허 : 35

초록

A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

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We claim: 1. An airfoil vortex dissipating system comprising: an airfoil having a leading edge, a trailing edge, and an outer end portion; and at least one nozzle positioned at, or proximate to, the outer end portion of the airfoil, wherein a characteristic of the at least one nozzle cyclically changes during operation to discharge a jet air stream in a plurality of different discharge directions, wherein the characteristic changes at a cyclic frequency sufficient to substantially dissipate a vortex generated by the airfoil. 2. The system of claim 1 wherein the characteristic of the at least one nozzle is a discharge direction of the jet air stream that cyclically changes between at least a first discharge direction and a second discharge direction. 3. The system of claim 2 wherein when the discharge direction is generally centrally located between the first discharge direction and the second discharge direction, the discharge direction has a substantial alignment component generally perpendicular to a forward to rear chord axis of the airfoil and generally parallel to an alignment reference plane of the airfoil, wherein the alignment reference plane is coincident with the forward to rear chord axis and a spanwise axis. 4. The system of claim 2 wherein when the discharge direction is in a generally central discharge direction between the first discharge direction and the second discharge direction, the discharge direction has a substantial alignment component slanting downwardly and outwardly from an alignment reference plane of the airfoil, wherein the alignment reference plane is coincident with a forward to rear chord axis and a spanwise axis. 5. The system of claim 2 wherein the characteristic changes at a cyclic frequency sufficiently high that substantial dissipation of the vortex is accomplished by alleviating the intensity of the vortex. 6. The system of claim 5 wherein the cyclic frequency is greater than two Hertz. 7. The system of claim 5 wherein the cyclic frequency is at least as great as about five Hertz. 8. The system of claim 1 wherein the characteristic changes to move the discharge direction of the jet air stream rotatably between at least a first discharge direction and a second discharge direction through an angle of at least 30 degrees. 9. The system of claim 1 wherein the characteristic changes to move the discharge direction of the jet air stream rotatably between at least a first discharge direction and a second discharge direction through an angle of at least 60 degrees. 10. The system of claim 2 wherein the characteristic changes at a cyclic frequency sufficiently low that substantial dissipation of the vortex is accomplished at least in part by accelerating an instability which leads to vortex dissipation. 11. The system of claim 10 wherein the cyclic frequency is at least as low as about two Hertz. 12. The system of claim 10 wherein the cyclic frequency is at least as low as approximately one Hertz. 13. The system of claim 1 wherein the jet air stream comprises at least two air stream portions which are moved cyclically out of phase with one another. 14. The system of claim 13 wherein the air stream portions move in a scissors pattern. 15. The system of claim 1 wherein the cyclic frequency is constant. 16. The system of claim 1 wherein the cyclic frequency is 1 Hz. 17. The system of claim 1 wherein the characteristic changes in a continuous manner. 18. The system of claim 1 wherein the nozzle comprises an exit orifice with an elliptical shape. 19. The system of claim 1 wherein the nozzle comprises an exit orifice with a circular shape. 20. The system of claim 1 wherein the at least one nozzle comprises a convergent nozzle shape. 21. The system of claim 1 wherein the at least one nozzle comprises a convergent-divergent nozzle shape. 22. The system of claim 1 wherein the nozzle is configured to discharge the jet air stream at a speed that is a function of at least one of aircraft weight, chordwise length of the at least one nozzle, number of nozzle orifices, and orifice diameter. 23. The system of claim 1 wherein a discharge diameter of the at least one nozzle is selected to be a function of aircraft weight, jet air stream velocity, length of the at least one nozzle, and number of nozzle orifices. 24. The system of claim 1 wherein the jet air stream is discharged at a speed of at least Mach 0.3. 25. The system of claim 1 wherein the jet air stream is discharged at a speed of between Mach 0.3 to Mach 0.9. 26. A method of dissipating a vortex which is generated by an airfoil on a fixed wing aircraft, the airfoil having a leading edge, a trailing edge, and an outer end portion, the method comprising: at least partially dissipating the vortex generated by the airfoil by cyclically changing a characteristic of a jet air stream between a first state and a second state in a time-dependent manner, with the characteristic changing in a continuous manner between temporally adjacent states, the jet air stream being directed from at least one nozzle located at least proximate to the outer end portion of the airfoil. 27. The method of claim 26 wherein changing a characteristic comprises changing a discharge direction of the jet air stream between at least a first discharge direction and a second discharge direction. 28. The method of claim 27 wherein changing the characteristic of the jet air stream comprises moving at least two air stream portions cyclically out of phase with one another. 29. The method of claim 26 wherein changing the characteristic comprises changing a discharge direction rotatably between at least a first discharge direction and a second discharge direction through an angle of at least 30 degrees. 30. The method of claim 26 wherein changing the characteristic comprises changing a discharge direction rotatably between at least a first discharge direction and a second discharge direction through an angle of at least 60 degrees. 31. The method of claim 26, further comprising discharging the jet air stream from the at least one nozzle in a generally central discharge direction between a first discharge direction and a second discharge direction, the generally central discharge direction having a substantial alignment component generally perpendicular to a chord axis of the airfoil and generally parallel to an alignment reference plane of the airfoil, the alignment reference plane being coincident with a forward to rear chord axis and a spanwise axis. 32. The method of claim 26, further comprising discharging the jet air stream from the at least one nozzle in a generally central discharge direction between a first discharge direction and a second discharge direction, the generally central discharge direction having a substantial alignment component slanting downwardly and outwardly from an alignment reference plane of the airfoil, the alignment reference plane being coincident with a forward to rear chord axis and a spanwise axis. 33. The method of claim 26 wherein changing the characteristic comprises changing a discharge direction at a cyclic frequency sufficiently high that dissipation of the vortex is accomplished at least in part by alleviating the intensity of the vortex. 34. The method of claim 33 wherein the cyclic frequency is greater than two Hertz. 35. The method of claim 33 wherein the cyclic frequency is at least as great as about five Hertz. 36. The method of claim 26 wherein changing the characteristic comprises changing a discharge direction at a cyclic frequency sufficiently low that dissipation of the vortex is accomplished at least in part by accelerating instability which leads to substantial vortex dissipation. 37. The method of claim 36 wherein the cyclic frequency is at least as low as about two Hertz. 38. The method of claim 36 wherein the cyclic frequency is at least as low as approximately one Hertz. 39. The method of claim 26 wherein the characteristic is changed in a continuous manner. 40. An airfoil vortex dissipating system comprising: an airfoil having a leading edge, a trailing edge, and an outer end portion; at least one nozzle located at, or proximate to, the outer end portion of the airfoil, wherein a characteristic of the at least one nozzle cyclically changes during operation to discharge a jet air stream in a plurality of discharge directions, and wherein the characteristic chances at a cyclic frequency sufficient to substantially dissipate a vortex generated by the airfoil; and a pressurized air inlet section positioned to supply pressurized air to the at least one nozzle. 41. The system of claim 40 wherein the characteristic includes a discharge direction and changes between a first discharge direction and a second discharge direction through an angle of at least 30 degrees. 42. The system of claim 40 wherein the characteristic includes a discharge direction and changes between a first discharge direction and a second discharge direction through an angle of at least 60 degrees. 43. The system of claim 40 wherein the characteristic changes at a cyclic frequency sufficiently high that substantial dissipation of the vortex is accomplished at least in part by alleviating the intensity of the vortex. 44. The system of claim 43 wherein the frequency is greater than two Hertz. 45. The system of claim 43 wherein the cyclic frequency is at least as great as about five Hertz. 46. The system of claim 40 wherein the characteristic changes at a cyclic frequency sufficiently low that substantial dissipation of the vortex is accomplished at least in part by accelerating an instability which leads to vortex substantial dissipation. 47. The system of claim 46 wherein the cyclic frequency is at least as low as about two Hertz. 48. The system of claim 46 wherein the cyclic frequency is at least as low as approximately one Hertz. 49. The system of claim 40 wherein the characteristic comprises a discharge direction of the jet air stream and changes between at least a first discharge direction, a second discharge direction, and a third discharge direction. 50. A method of dissipating a vortex which is generated by an airfoil, the airfoil having a leading edge, a trailing edge, and an outer end portion, the method comprising: discharging a jet air stream from at least one nozzle into the vortex; and at least substantially dissipating the vortex by cyclically changing a characteristic of the jet air stream to direct at least a portion of the jet air stream in a plurality of discharge directions.

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Apparatus and method for the control of trailing wake flows

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