IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0208565
(2002-07-30)
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발명자
/ 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
28 인용 특허 :
3 |
초록
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A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade has a convex segment followed by a concave segment, as seen in a plan view. The leading and trailing edges are rounded so as to promote proper fluid sheet
A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade has a convex segment followed by a concave segment, as seen in a plan view. The leading and trailing edges are rounded so as to promote proper fluid sheet formation along the flat surfaces and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.
대표청구항
▼
1. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally
1. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally from said hub, said leading edge of each of said blade structures following a curve modeled along a sine function starting from said hub substantially along a tangent line and having at least one curved segment selected from the group consisting of a concave segment and a convex segment. 2. The propeller configuration according to claim 1, wherein said sine function extends along an interval of more than ½·&pgr; in radians.3. The propeller configuration according to claim 2, wherein said sine function extends along an interval of approximately &pgr; in radians.4. The propeller configuration according to claim 1, wherein said trailing edge of each of said blade structures follows a curve having a concave segment and an adjoining convex segment.5. The propeller configuration according to claim 4, wherein said curve of said trailing edge starts from said hub substantially radially outward, curves along said convex segment, and merges into said concave segment leading to said periphery.6. The propeller configuration according to claim 1, wherein said leading edge and said trailing edge are defined by a tangent function.7. The propeller configuration according to claim 1, wherein a width of said blade structures defined by said leading edge and said trailing edge varies with a distance from said hub, with a relatively narrower segment at said hub merging into a relatively wider segment distally from said hub.8. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally from said hub, said leading edge of each of said blade structures following a curve modeled along a sine function and having at least one curved segment selected from the group consisting of a concave segment and a convex segment, and wherein, relative to a center line of each of said blades, said curve of said leading edge is defined by a function y=a sin x, where −&pgr;/2≦x<&pgr; in radians, a being a real number defining an amplitude of said curve or said leading edge. 9. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally from said hub, said leading edge of each of said blade structures following a curve modeled along a sine function and having at least one curved segment selected from the group consisting of a concave segment and a convex segment, and wherein each of said blade structures is formed with a forward surface extending from said leading edge to said trailing edge, and a rear surface extending from said leading edge to said trailing edge; said forward surface and said rear surface at said leading edge extending substantially parallel to and offset from said forward surface and said rear surface at said trailing edge, and converging smoothly at said trailing and leading edges to form a sharp leading edge and a sharp trailing edge. 10. The propeller configuration according to claim 9, wherein said forward surface and said rear surface are defined by a function y=a cos x, where 0≦x≦&pgr; in radians, x being approximately equal to zero at said leading edge and x being approximately equal to &pgr; at said trailing edge, and a being a real number defining a given thickness of said blade structures.11. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally from said hub, said leading edge of each of said blade structures following a curve starting from said hub substantially along a tangent line and having a concave segment and an adjoining convex segment. 12. The propeller configuration according to claim 11, wherein said curve of said leading edge starts from said hub substantially along a tangent line, curves along said concave segment, and merges into said convex segment leading to said periphery.13. The propeller configuration according to claim 11, wherein said trailing edge of each of said blade structures follows a curve having a concave segment and an adjoining convex segment.14. The propeller configuration according to claim 13, wherein said curve of said trailing edge starts from said hub substantially radially outward, curves along said convex segment, and merges into said concave segment leading to said periphery.15. A propeller configuration, comprising: a rotatable hub defining an axis of rotation; a plurality of blade structures attached to said hub and projecting radially away from said axis of rotation; each of said blade structures having a leading edge, a trailing edge, and a periphery distally from said hub, said leading edge of each of said blade structures following a curve modeled along a sine function and having at least one curved segment selected from the group consisting of a concave segment and a convex segment; and wherein, relative to a center line of each of said blades, said curve of said leading edge is defined by a function y=a sin x, where −&pgr;/2≦x<&pgr; in radians, a being a real number defining an amplitude of said curve of said leading edge. 16. In a fixed-wing aircraft having a fuselage with a longitudinal axis, a wing configuration attached to the fuselage, comprising: a wing structure attached to the fuselage and projecting sideways away from the fuselage; said wing structure having a leading edge defined by a forward traveling direction of the aircraft, a trailing edge, and a free end distally from the fuselage, said leading edge of said wing structure following a curve having a concave segment and an adjoining convex segment, and, relative to a center line of said wing structure, said curve of said leading edge being defined by a function y=a sin x, where −&pgr;/2≦x≦&pgr;/2 in radians, a being a real number defining an amplitude of said curve of said leading edge. 17. The wing configuration according to claim 16, wherein said curve of said leading edge starts from the fuselage substantially colinear with a sidewall of the fuselage, curves along said concave segment, and merges into said convex segment leading to said free end.18. The wing configuration according to claim 16, wherein said trailing edge of said wing structure follows a curve having a concave segment and an adjoining convex segment.19. The wing configuration according to claim 16, wherein said trailing edge follows a curve substantially corresponding with the curve followed by said leading edge.20. In a fixed-wing aircraft having a fuselage with a longitudinal axis, a wing configuration attached to the fuselage, comprising: a wing structure attached to the fuselage and projecting sideways away from the fuselage; said wing structure having a leading edge defined by a forward traveling direction of the aircraft, a trailing edge, and a free end distally from the fuselage, said leading edge and said trailing edge of said wing structure each following a curve having a concave segment and an adjoining convex segment substantially defined by a tangent function. 21. In a fixed-wing aircraft having a fuselage with a longitudinal axis, a wing configuration attached to the fuselage, comprising: a wing structure attached to the fuselage and projecting sideways away from the fuselage; said wing structure having a leading edge defined by a forward traveling direction of the aircraft, a trailing edge, and a free end distally from the fuselage, said leading edge of said wing structure following a curve having a concave segment and an adjoining convex segment, and said trailing edge following a curve substantially corresponding with the curve followed by said leading edge.
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