Patents by Inventor Paul Morrell
Paul Morrell 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: 11845542Abstract: An aircraft wing having a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes an actuation assembly for rotating the wing tip device about the hinge. The upper cover of the wing tip device includes an offset region extending inboard of the hinge axis, such that when the wing tip device is rotated to the ground configuration, the offset region extends into a space previously-occupied by the actuation assembly, but is outside the space occupied by the actuation assembly in the ground configuration.Type: GrantFiled: May 21, 2020Date of Patent: December 19, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Jack Horwood, Paul Morrell, Matt Harding
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Patent number: 11772776Abstract: An aircraft wing including a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes a hinged panel at the boundary between the wing tip device and the fixed wing. In the flight configuration the panel is closed such that the panel is substantially flush with the upper surface of the wing, and the hinged panel is located in the path of a moveable element (for example part of an actuation mechanism, such as a curved rack). In the ground configuration the panel is hinged open to a position outside the path of the moveable element such that clashing of the moveable element with the stationary structure at the tip of the fixed wing is avoided.Type: GrantFiled: May 14, 2020Date of Patent: October 3, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Jack Horwood, Paul Morrell, Matt Harding
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Patent number: 11708145Abstract: A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.Type: GrantFiled: October 6, 2021Date of Patent: July 25, 2023Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS (S.A.S.)Inventors: Russell Older, Paul Morrell, Ryan Holland, Oliver Marks, Pierre-Antoine Combes, Guillaume De Almeida
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Patent number: 11613342Abstract: An aircraft wing having a fixed wing and a wing tip device at the tip of the fixed wing is disclosed. The wing tip device being movable relative to the fixed wing between flight and ground configurations, the aircraft wing having a locking mechanism including a locking bore and a locking pin, the locking mechanism being configurable between a locked configuration, in which the locking pin is received in the locking bore, to lock the wing tip device in one of the flight or ground configurations, and an unlocked configuration in which the locking pin is withdrawn from the locking bore such that the wing tip device is moveable relative to the fixed wing, and wherein the locking pin is configured such that it has a replaceable tip.Type: GrantFiled: March 27, 2020Date of Patent: March 28, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Paul Morrell, Matt Harding
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Publication number: 20220227473Abstract: A pin joint assembly is disclosed having a first lug and a second lug, a pin extending through the first and second lugs, a U-shaped bushing between the first lug and the pin, wherein the U-shaped bushing includes a first end flange and a second end flange that extend radially outwards and retain the U-shaped bushing to the first lug, and wherein the U-shaped bushing includes a bearing surface between the first and second end flanges on which the first lug is slidable.Type: ApplicationFiled: January 13, 2022Publication date: July 21, 2022Inventor: Paul MORRELL
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Publication number: 20220194549Abstract: A pin joint assembly including: a first end lug and a second end lug; a pin hole extending through the first and second end lugs; a first retaining feature and a second retaining feature arrangeable at opposing ends of the pin hole; a headless pin including a pin body for inserting through the pin hole to rotatably couple the first and second end lugs, such that the pin body is retained between the first and second retaining features; a first bushing for positioning between the headless pin and the first end lug, and a second bushing for positioning between the headless pin and the second end lug; wherein the headless pin is isolated from the first and second retaining features.Type: ApplicationFiled: October 21, 2021Publication date: June 23, 2022Inventors: Jack HORWOOD, Matt HARDING, Paul MORRELL
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Publication number: 20220177117Abstract: A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.Type: ApplicationFiled: October 4, 2021Publication date: June 9, 2022Inventors: Russell OLDER, Paul MORRELL, Ryan HOLLAND, Oliver MARKS, Pierre-Antoine COMBES, Guillaume DE ALMEIDA
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Publication number: 20220177112Abstract: A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.Type: ApplicationFiled: October 6, 2021Publication date: June 9, 2022Inventors: Russell OLDER, Paul MORRELL, Ryan HOLLAND, Oliver MARKS, Pierre-Antoine COMBES, Guillaume DE ALMEIDA
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Patent number: 11319053Abstract: An aircraft having a fixed wing and a wing tip device at the tip thereof is disclosed. The wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A locking mechanism locks the wing tip device in the flight configuration, and includes a plurality of lugs located on each of the fixed wing and wing tip device. Locking pins are inserted through and lock together corresponding lugs when the wing tip device is in the flight configuration. A secondary locking mechanism of a plurality of blocking members prevents the removal of the locking pins from the corresponding lugs, whereby the plurality of blocking members have a common actuator.Type: GrantFiled: April 19, 2019Date of Patent: May 3, 2022Assignee: AIRBUS OPERATIONS LIMITEDInventor: Paul Morrell
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Publication number: 20220024559Abstract: An aircraft wing including a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes a hinged panel at the boundary between the wing tip device and the fixed wing. In the flight configuration the panel is closed such that the panel is substantially flush with the upper surface of the wing, and the hinged panel is located in the path of a moveable element (for example part of an actuation mechanism, such as a curved rack). In the ground configuration the panel is hinged open to a position outside the path of the moveable element such that clashing of the moveable element with the stationary structure at the tip of the fixed wing is avoided.Type: ApplicationFiled: May 14, 2020Publication date: January 27, 2022Inventors: Jack HORWOOD, Paul MORRELL, Matt HARDING
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Publication number: 20220024558Abstract: An aircraft wing having a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes an actuation assembly for rotating the wing tip device about the hinge. The upper cover of the wing tip device includes an offset region extending inboard of the hinge axis, such that when the wing tip device is rotated to the ground configuration, the offset region extends into a space previously-occupied by the actuation assembly, but is outside the space occupied by the actuation assembly in the ground configuration.Type: ApplicationFiled: May 21, 2020Publication date: January 27, 2022Inventors: Jack HORWOOD, Paul MORRELL, Matt HARDING
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Patent number: 10844492Abstract: An arrangement comprising a component (203) adjacent to a ceramic matrix composite in a gas turbine engine is shown. The component comprises a nickel-base superalloy substrate (301) and a cobalt-modified beta-nickel-aluminide coating (302) on the substrate to prevent interdiffusion between the substrate and the ceramic matrix composite. The substrate is coated by depositing a cobalt layer on the substrate, depositing an aluminium layer on the cobalt layer and then forming a cobalt-modified beta nickel aluminide coating.Type: GrantFiled: May 17, 2018Date of Patent: November 24, 2020Assignee: ROLLS-ROYCE PLCInventors: Ngunjoh L. Ndamka, Paul Morrell
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Publication number: 20200307762Abstract: An aircraft wing having a fixed wing and a wing tip device at the tip of the fixed wing is disclosed. The wing tip device being movable relative to the fixed wing between flight and ground configurations, the aircraft wing having a locking mechanism including a locking bore and a locking pin, the locking mechanism being configurable between a locked configuration, in which the locking pin is received in the locking bore, to lock the wing tip device in one of the flight or ground configurations, and an unlocked configuration in which the locking pin is withdrawn from the locking bore such that the wing tip device is moveable relative to the fixed wing, and wherein the locking pin is configured such that it has a replaceable tip.Type: ApplicationFiled: March 27, 2020Publication date: October 1, 2020Inventors: Paul MORRELL, Matt HARDING
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Patent number: 10767495Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a turbine vane arranged around the support strut. The support strut is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support strut.Type: GrantFiled: February 1, 2019Date of Patent: September 8, 2020Assignee: Rolls-Royce plcInventors: Michael J. Whittle, Paul Morrell, Anthony Razzell, Matthew Adams
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Publication number: 20200248569Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a turbine vane arranged around the support strut. The support strut is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support strut.Type: ApplicationFiled: February 1, 2019Publication date: August 6, 2020Inventors: Michael J. Whittle, Paul Morrell, Anthony Razzell, Matthew Adams
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Publication number: 20190322350Abstract: An aircraft having a fixed wing and a wing tip device at the tip thereof is disclosed. The wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A locking mechanism locks the wing tip device in the flight configuration, and includes a plurality of lugs located on each of the fixed wing and wing tip device. Locking pins are inserted through and lock together corresponding lugs when the wing tip device is in the flight configuration. A secondary locking mechanism of a plurality of blocking members prevents the removal of the locking pins from the corresponding lugs, whereby the plurality of blocking members have a common actuator.Type: ApplicationFiled: April 19, 2019Publication date: October 24, 2019Inventor: Paul MORRELL
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Publication number: 20180334749Abstract: An arrangement comprising a component (203) adjacent to a ceramic matrix composite in a gas turbine engine is shown. The component comprises a nickel-base superalloy substrate (301) and a cobalt-modified beta-nickel-aluminide coating (302) on the substrate to prevent interdiffusion between the substrate and the ceramic matrix composite. The substrate is coated by depositing a cobalt layer on the substrate, depositing an aluminium layer on the cobalt layer and then forming a cobalt-modified beta nickel aluminide coating.Type: ApplicationFiled: May 17, 2018Publication date: November 22, 2018Applicant: ROLLS-ROYCE plcInventors: Ngunjoh L. NDAMKA, Paul MORRELL
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Patent number: 9509651Abstract: Systems and methods for presenting electronic messages are provided. In some implementations, a method includes, at a computing device having one or more processors and memory storing one or more programs for execution by the one or more processors, (A) causing to be concurrently displayed in an E-mail application (i) a first view of a message folder that includes one or more electronic messages and (ii) a user interface control indicating one or more alternate views are available for the message folder, wherein the user interface control persistently indicates the availability of the one or more alternative views and (B) hiding the user interface control, without user intervention, responsive to the occurrence of a predetermined system event.Type: GrantFiled: July 28, 2014Date of Patent: November 29, 2016Assignee: Google Inc.Inventors: Keith Jonathan Coleman, Douglas Alexander Aberdeen, Paul Morrell McDonald, Annie Chen, Andrew Ward Moedinger, Klaus Martin Kretzschmar, Jason Briggs Cornwell, Debra Joy Lauterbach
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Publication number: 20140337757Abstract: Systems and methods for presenting electronic messages are provided. In some implementations, a method includes, at a computing device having one or more processors and memory storing one or more programs for execution by the one or more processors, (A) causing to be concurrently displayed in an E-mail application (i) a first view of a message folder that includes one or more electronic messages and (ii) a user interface control indicating one or more alternate views are available for the message folder, wherein the user interface control persistently indicates the availability of the one or more alternative views and (B) hiding the user interface control, without user intervention, responsive to the occurrence of a predetermined system event.Type: ApplicationFiled: July 28, 2014Publication date: November 13, 2014Inventors: Keith Jonathan Coleman, Douglas Alexander Aberdeen, Paul Morrell McDonald, Annie Chen, Andrew Ward Moedinger, Klaus Martin Kretzschmar, Jason Briggs Cornwell, Debra Joy Lauterbach
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Patent number: 6025078Abstract: A metallic article (10) comprises a bond coating (14,16) on the metallic article (10) and a ceramic thermal barrier coating (18) on the bond coating (14,16). The ceramic thermal barrier (18) coating comprises zirconia stabilized with yttria, calcia, magnesia or india, and erbia to reduce the thermal conductivity of the ceramic thermal barrier coating (18). The ceramic thermal barrier coating (18) is at least 100 microns thick. The erbium atom has an atomic mass greater than the average atomic mass of the zirconium, the yttrium, calcium, magnesium or indium and the oxygen atoms to reduce phonon thermal conductivity of the ceramic thermal barrier coating (18). The ceramic thermal barrier coating (18) comprises 4 to 20 wt % of yttria, 5 to 25 wt % of erbia and the balance is zirconia plus incidental impurities. The erbia absorbs energy in the 0.3 microns to 5 microns waveband to reduce photon thermal conductivity.Type: GrantFiled: August 7, 1997Date of Patent: February 15, 2000Assignee: Rolls-Royce PLCInventors: David S Rickerby, Paul Morrell, Yuriy A Tamarin