Patents by Inventor Paul Hadley
Paul Hadley 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: 9365283Abstract: A foldable seal comprising an elastomeric seal substrate and at least one molded-in stiffener plate embedded within the seal substrate. Also, a method of manufacturing the seal.Type: GrantFiled: November 7, 2011Date of Patent: June 14, 2016Assignee: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Colin John West, David Alistair Sutton, Paul Hadley
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Publication number: 20160144493Abstract: A bush assembly comprising a component having a bore, a bush fitted in the bore and having a flange that extends radially outwardly over a surface of the component surrounding the bore, and a seal assembly for sealing the interface between the flange and the surface of the component, wherein the seal assembly includes a seal member and a layer of sealant between the seal member and the interface between the flange and the surface of the component. Also a method for sealing a bush, a kit of parts for forming a bush assembly, and a clamping tool for forming a bush assembly.Type: ApplicationFiled: February 1, 2016Publication date: May 26, 2016Inventors: James WILSON, Alan QUAYLE, Paul HADLEY, John Colin WEST, Simon CARRICK, John MONTEITH, Peter MASON
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Patent number: 9308982Abstract: The present invention relates to a joint between a laminar composite cover (12) and a second cover (15) (which may or may not be also formed from a composite material). The invention also relates to a method of manufacturing such a joint and a method of manufacturing a composite cover suitable for use in such a joint. The laminar composite cover (12) comprises a stack of layers, substantially all of the layers being shaped to form a joggle, each joggle comprising a first portion, a second portion where the layer extends substantially parallel with the first portion, and a ramp (33) between the first and second portions where the layer extends at an angle to the first and second portions, the number of layers being substantially the same on both sides of the ramp. The second cover (15) partially overlaps with the composite cover, and a clamp or fastener (31) holds the covers together where they overlap.Type: GrantFiled: March 12, 2009Date of Patent: April 12, 2016Assignee: Airbus Operations LimitedInventors: Paul Hadley, John Flood, Alan Quayle
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Publication number: 20160096615Abstract: A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.Type: ApplicationFiled: December 15, 2015Publication date: April 7, 2016Inventors: James WILSON, Alan QUAYLE, Paul HADLEY
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Patent number: 9303693Abstract: A bush assembly comprising a component having a bore, a bush fitted in the bore and having a flange that extends radially outwardly over a surface of the component surrounding the bore, and a seal assembly for sealing the interface between the flange and the surface of the component, wherein the seal assembly includes a seal member and a layer of sealant between the seal member and the interface between the flange and the surface of the component. Also a method for sealing a bush, a kit of parts for forming a bush assembly, and a clamping tool for forming a bush assembly.Type: GrantFiled: April 25, 2013Date of Patent: April 5, 2016Assignee: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Alan Quayle, Paul Hadley, John Colin West, Simon Carrick, John Monteith, Peter Mason
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Patent number: 9242718Abstract: A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.Type: GrantFiled: November 7, 2011Date of Patent: January 26, 2016Assignee: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Alan Quayle, Paul Hadley
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Patent number: 9102393Abstract: A wing assembly for an aircraft is disclosed having a spar, a wing cover, and a rib. The spar has a web portion and a flange portion joined by a radius corner, wherein a gap is formed at an interface between the spar, the wing cover and the rib. The assembly further includes a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap.Type: GrantFiled: March 18, 2013Date of Patent: August 11, 2015Assignee: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Paul Hadley, Alan Quayle
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Patent number: 9061755Abstract: An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted upon a slat deployment mechanism for moving the slat between a retracted position and an extended position with respect to the fixed leading edge, the fixed leading edge having an aperture to accommodate the slat deployment mechanism, and a closing plate mounted off the slat deployment mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted. The closing plate can include a first portion and a second portion, and a hinge connecting the first and the second portions. The closing plate can include a plurality of integrally formed spacer elements for positioning the closing plate with respect to the slat deployment mechanism. Also, a method of removing an access panel in an aircraft wing assembly.Type: GrantFiled: December 14, 2012Date of Patent: June 23, 2015Assignee: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Paul Hadley, John Gleave
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Patent number: 9038951Abstract: A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies.Type: GrantFiled: March 31, 2010Date of Patent: May 26, 2015Assignee: Airbus Operations LimitedInventors: Steven Coulter, Paul Hadley, Geraint Hopkins
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Patent number: 9027890Abstract: An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted for movement between a retracted position and an extended position with respect to the fixed leading edge, and a translating cable device for electrically connecting the slat to the wing and having a strut coupled at one end to the slat, the fixed leading edge having an aperture to accommodate the strut, and a seal assembly for sealing between the strut and the aperture.Type: GrantFiled: December 14, 2012Date of Patent: May 12, 2015Assignee: Airbus Operations LimitedInventors: James Wilson, Paul Hadley, Alexandru Teodoru
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Publication number: 20150086143Abstract: A bush assembly comprising a component having a bore, a bush fitted in the bore and having a flange that extends radially outwardly over a surface of the component surrounding the bore, and a seal assembly for sealing the interface between the flange and the surface of the component, wherein the seal assembly includes a seal member and a layer of sealant between the seal member and the interface between the flange and the surface of the component. Also a method for sealing a bush, a kit of parts for forming a bush assembly, and a clamping tool for forming a bush assembly.Type: ApplicationFiled: April 25, 2013Publication date: March 26, 2015Inventors: James Wilson, Alan Quayle, Paul Hadley, John Colin West, Simon Carrick, John Monteith, Peter Mason
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Publication number: 20150030380Abstract: A structural assembly comprising a first component having a ramped surface, and a fastener assembly for fastening the first component to a second component, the fastener assembly including a receptacle strip of resiliently deformable material attached to the ramped surface of the first component so as to assume the contour of the ramped surface, and a plurality of fastener receptacles attached to the receptacle strip for receiving respective fasteners. Also, a method of fastening a first component to a second component using the fastener assembly.Type: ApplicationFiled: January 11, 2013Publication date: January 29, 2015Applicant: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Paul Hadley, John Gleave
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Patent number: 8632311Abstract: A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.Type: GrantFiled: August 21, 2006Date of Patent: January 21, 2014Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
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Publication number: 20140002947Abstract: An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either: at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; or at least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.Type: ApplicationFiled: March 9, 2012Publication date: January 2, 2014Applicant: Airbus Operations LimitedInventors: Alan Quayle, James Wilson, Jon Mcalinden, Paul Hadley
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Publication number: 20130305415Abstract: Provided are methods for the production of a stress tolerant plant or precursor thereof. The methods comprise (i) subjecting one or more parental plants to one or more stress conditions selected from unfavourable conditions relating to relative humidity, water availability, periodic drought, nutrients, sunlight, wind, temperature, pH, exogenous chemicals, chemical toxins such as salt, herbivory, prophylactic chemicals, fertilizers, pathogen attack such as bacterial, fungal, or virus infection and pest infestation; and (ii) generating offspring from said one or more parental plants.Type: ApplicationFiled: June 14, 2011Publication date: November 14, 2013Applicant: Aberystwyth UniversityInventors: Michael James Wilkinson, Carlos Marcelino Rodriguez Lopez, Penelope Tricker, Paul Hadley
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Publication number: 20130228983Abstract: A foldable seal comprising an elastomeric seal substrate and at least one moulded-in stiffener plate embedded within the seal substrate. Also, a method of manufacturing the seal.Type: ApplicationFiled: November 7, 2011Publication date: September 5, 2013Inventors: James Wilson, Colin John West, David Alistair Sutton, Paul Hadley
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Publication number: 20130214096Abstract: A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.Type: ApplicationFiled: November 7, 2011Publication date: August 22, 2013Applicant: AIRBUS OPERATIONS LIMITEDInventors: James Wilson, Alan Quayle, Paul Hadley
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Patent number: 8512003Abstract: A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.Type: GrantFiled: August 21, 2006Date of Patent: August 20, 2013Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
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Patent number: 8500396Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.Type: GrantFiled: August 21, 2006Date of Patent: August 6, 2013Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
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Patent number: 8425183Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.Type: GrantFiled: November 20, 2006Date of Patent: April 23, 2013Assignee: General Electric CompanyInventors: Ching-Pang Lee, Kevin Samuel Klasing, Paul Hadley Vitt, Brian David Keith