Patents by Inventor Alan Brocklehurst
Alan Brocklehurst has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 9085359Abstract: An aerofoil has a main portion of aerofoil cross section, an inner spanwise root end where the aerofoil is in use secured to a supporting structure, and at an outermost spanwise end outboard of the main portion, beyond a tip station, a tip region which includes a tip edge. The planform configuration of the tip edge lies on a first Bezier curve constructed from at least four control points, P1, P2, P3 and P4, each lying on the periphery of a polygon which bounds the tip region. Control point P1 is located on a leading edge of the aerofoil. Control point P2 is located on the second side of the polygon. Control point P3 is located on the third side of the polygon, and control point P4 is located at the outermost tip edge point at a trailing edge of the aerofoil.Type: GrantFiled: November 30, 2011Date of Patent: July 21, 2015Assignee: Agustawestland LimitedInventor: Alan Brocklehurst
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Publication number: 20120237354Abstract: An aerofoil has a main portion of aerofoil cross section, an inner spanwise root end where the aerofoil is in use secured to a supporting structure, and at an outermost spanwise end outboard of the main portion, beyond a tip station, a tip region which includes a tip edge. The planform configuration of the tip edge lies on a first Bezier curve constructed from at least four control points, P1, P2, P3 and P4, each lying on the periphery of a polygon which bounds the tip region. Control point P1 is located on a leading edge of the aerofoil. Control point P2 is located on the second side of the polygon. Control point P3 is located on the third side of the polygon, and control point P4 is located at the outermost tip edge point at a trailing edge of the aerofoil.Type: ApplicationFiled: November 30, 2011Publication date: September 20, 2012Inventor: Alan BROCKLEHURST
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Patent number: 8210818Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end.Type: GrantFiled: May 20, 2009Date of Patent: July 3, 2012Assignee: Agusta S.p.A.Inventors: Alan Brocklehurst, Alessandro Scandroglio
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Patent number: 8056851Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge.Type: GrantFiled: May 20, 2009Date of Patent: November 15, 2011Assignee: Agusta S.p.A.Inventors: Alan Brocklehurst, Alessandro Scandroglio
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Publication number: 20100092299Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end.Type: ApplicationFiled: May 20, 2009Publication date: April 15, 2010Applicant: Agusta S.p.A.Inventors: Alan Brocklehurst, Alessandro Scandroglio
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Publication number: 20100092294Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge.Type: ApplicationFiled: May 20, 2009Publication date: April 15, 2010Applicant: Agusta S.p.A.Inventors: Alan Brocklehurst, Alessandro Scandroglio
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Patent number: 5992793Abstract: An aerofoil comprises a leading edge and a trailing edge which define a mean chord length, and the aerofoil having an inner or root end adapted for attachment to an aircraft, and an outer end which includes a tip which is adapted in use to divide the airflow into two generally equal vortices one being an inner vortex and the other being an outer vortex the inner vortex being arranged to trail from an outer edge of a forward region of the tip and pass over a rear region of the tip.Type: GrantFiled: January 6, 1997Date of Patent: November 30, 1999Assignee: GKN Westland Helicopters LimitedInventors: Frederick John Perry, Robert John Harrison, Alan Brocklehurst
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Patent number: 5927948Abstract: A propeller (10a) comprising a plurality of propeller blades (9a) each having a root end (11a) attached to the central propeller disc or hub (12a), an intermediate portion (13a) extending from the root end (11a) and having a generally aerofoil cross section extending chordwise between a leading edge (14a) and a trailing edge (15a), and the blade (9a) having a tip (19) at an end of the intermediate portion (13a) remote from the root end (11a), the tip (19) having a leading edge portion (20) extending forwardly from a junction (21) with the leading edge (14a) of the intermediate portion (13a) thus to provide a discontinuity or notch (25) in the leading edge (14a) of the blade (9a) at the junction (21).Type: GrantFiled: April 23, 1997Date of Patent: July 27, 1999Assignee: GKn Westland Helicopters LimitedInventors: Frederick John Perry, Alan Brocklehurst, Robert John Harrison
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Patent number: 5750891Abstract: A method and apparatus for determining the airspeed of a rotary wing aircraft having a sustaining rotor with a plurality of radially extending rotor blades for rotation about a substantially vertical axis comprises the steps of measuring an airflow sideslip angle established during rotation of each rotor blade by the vector of a radial flow component due to the relative wind vector and the rotational velocity perpendicular to a blade feathering axis, producing a signal representative of the sideslip angle, comparing the signal in a processor containing information on a known relationship between the sideslip angle and airspeed, providing an output signal representative of the airspeed and wind direction to a display which may display both the airspeed and wind direction.Type: GrantFiled: September 11, 1996Date of Patent: May 12, 1998Assignee: GKN Westland Helicopters LimitedInventor: Alan Brocklehurst
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Patent number: 5492448Abstract: A rotary blade includes a fixed boundary layer control device extending spanwise on a lower surface adjacent the trailing edge to improve the lift/thrust characteristics of the blade especially at positive incidence angles. It was discovered that expected detrimental effects at zero/negative incidence did not materialize and the reasons are identified. Such blades are particularly useful for helicopter sustaining and anti-torque rotors.Type: GrantFiled: March 8, 1994Date of Patent: February 20, 1996Assignee: Westland Helicopters LimitedInventors: Frederick J. Perry, Alan Brocklehurst
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Patent number: 5205715Abstract: Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by a plurality of boundary layer control vanes located adjacent a forwardly swept leading edge portion forming the notch region.Type: GrantFiled: October 10, 1991Date of Patent: April 27, 1993Assignee: Westland Helicopters, Ltd.Inventors: Frederick J. Perry, Nicholas C. G. Isaacs, Alan Brocklehurst
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Patent number: 5199851Abstract: A helicoper rotor blade includes at its outer end a tip vane having a mean chord length greater than fifty percent of a chord length of a blade central portion and a span length greater than fifty percent of the blade chord which in operation generates two approximately equal strength tip vortices to reduce an acoustic impulse and a resulting noise known as blade slap.Type: GrantFiled: October 23, 1991Date of Patent: April 6, 1993Assignee: Westland Helicopters Ltd.Inventors: Frederick J. Perry, Alan Brocklehurst
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Patent number: 5174721Abstract: Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by features of the geometry and aerodynamic characteristics of the notch region itself. In particular it has been found beneficial for a forwardly swept leading edge portion to extend at an angle between 30 degrees and 55 degrees from a reference line parallel to a blade pitch change axis and the leading edge of the aerofoil in the notch region incorporates blade droop.Type: GrantFiled: October 10, 1991Date of Patent: December 29, 1992Assignee: Westland Helicopters LimitedInventor: Alan Brocklehurst