Patents by Inventor Angus Roy Smith
Angus Roy Smith 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: 10240536Abstract: A gas turbine engine is disclosed including a bifurcation fairing located in a bypass duct of the gas turbine engine and traversing the radial extent of the bypass duct. The bifurcation fairing has a delivery conduit inlet leading to a delivery conduit extending inside the bifurcation fairing, the delivery conduit being arranged in use for delivery of bypass air to one or more components of the gas turbine engine. A diverter conduit has a diverter conduit inlet from the delivery conduit upstream of the delivery conduit reaching the one or more components of the gas turbine engine. The diverter conduit has an outlet to a location other than the one or more components of the gas turbine engine.Type: GrantFiled: April 24, 2015Date of Patent: March 26, 2019Assignee: ROLLS-ROYCE plcInventors: Adam MacGregor Bagnall, Peter Beecroft, Richard Geoffrey Stretton, Philip Geoffrey Woodrow, Stephane Michel Marcel Baralon, Angus Roy Smith
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Patent number: 9885285Abstract: A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centerline of the engine.Type: GrantFiled: September 17, 2015Date of Patent: February 6, 2018Assignee: ROLLS-ROYCE plcInventors: Christopher Alan Mosley, Angus Roy Smith, Christopher Thomas John Sheaf, John Richard Wells
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Patent number: 9771873Abstract: A gas turbine engine including an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing includes a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop includes a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine.Type: GrantFiled: May 6, 2015Date of Patent: September 26, 2017Assignee: ROLLS-ROYCE plcInventors: Peter Beecroft, Richard Geoffrey Stretton, Philip Geoffrey Woodrow, Stephane Michel Marcel Baralon, Angus Roy Smith
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Patent number: 9328662Abstract: An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight.Type: GrantFiled: July 1, 2009Date of Patent: May 3, 2016Assignee: ROLLS-ROYCE plcInventors: Angus Roy Smith, Dimitris Arzoglou
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Publication number: 20160108811Abstract: A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centreline of the engine.Type: ApplicationFiled: September 17, 2015Publication date: April 21, 2016Inventors: Christopher Alan MOSLEY, Angus Roy SMITH, Christopher Thomas John SHEAF, John Richard WELLS
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Publication number: 20150330309Abstract: A gas turbine engine is disclosed including a bifurcation fairing located in a bypass duct of the gas turbine engine and traversing the radial extent of the bypass duct. The bifurcation fairing has a delivery conduit inlet leading to a delivery conduit extending inside the bifurcation fairing, the delivery conduit being arranged in use for delivery of bypass air to one or more components of the gas turbine engine. A diverter conduit has a diverter conduit inlet from the delivery conduit upstream of the delivery conduit reaching the one or more components of the gas turbine engine. The diverter conduit has an outlet to a location other than the one or more components of the gas turbine engine.Type: ApplicationFiled: April 24, 2015Publication date: November 19, 2015Inventors: Adam MacGregor BAGNALL, Peter BEECROFT, Richard Geoffrey STRETTON, Philip Geoffrey WOODROW, Stephane Michel Marcel BARALON, Angus Roy SMITH
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Publication number: 20150330236Abstract: A gas turbine engine including an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing includes a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop includes a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine.Type: ApplicationFiled: May 6, 2015Publication date: November 19, 2015Inventors: Peter BEECROFT, Richard Geoffrey STRETTON, Philip Geoffrey WOODROW, Stephane Michel Marcel BARALON, Angus Roy SMITH
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Patent number: 8985507Abstract: A method of designing a nacelle for a gas turbine engine includes defining an initial geometry for the nacelle, pivoting, at each of one or more positions on a highlight and in a plane of a respective longitudinal section, a front portion of a section of an intake lip lying in the respective longitudinal section about the highlight, and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighboring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.Type: GrantFiled: February 7, 2013Date of Patent: March 24, 2015Assignee: Rolls-Royce PLCInventors: Angus Roy Smith, Dimitris Arzoglou
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Patent number: 8418953Abstract: A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.Type: GrantFiled: July 2, 2009Date of Patent: April 16, 2013Assignee: Rolls-Royce PLCInventors: Angus Roy Smith, Dimitris Arzoglou
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Publication number: 20100019102Abstract: An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series/an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight.Type: ApplicationFiled: July 1, 2009Publication date: January 28, 2010Applicant: ROLLS-ROYCE PLCInventors: ANGUS ROY SMITH, Dimitris Arzoglou
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Publication number: 20100019100Abstract: An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight.Type: ApplicationFiled: July 1, 2009Publication date: January 28, 2010Applicant: ROLLS-ROYCE PLCInventors: Angus Roy Smith, Dimitris Arzoglou
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Publication number: 20100019101Abstract: A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.Type: ApplicationFiled: July 2, 2009Publication date: January 28, 2010Applicant: ROLLS-ROYCE PLCInventors: Angus Roy Smith, Dimitris Arzoglou