Patents by Inventor Bronwyn POWER
Bronwyn POWER 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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Publication number: 20240125241Abstract: An airfoil includes a high pressure surface and a low pressure surface that are connected at a leading edge and a trailing edge. The high pressure surface and the low pressure surface extend from a first end to a second end. A camber line extends between the leading edge and the trailing edge and a camber angle is defined as a plurality of camber-angle distributions that extend between the leading edge end and the trailing edge. The plurality of camber-angle distributions include a uniform portion that extends from the leading edge to a forced non-equilibrium boundary layer diffusion (FNBD) feature. The uniform portion includes a non-dimensionalized camber-angle unit that is constant the FNBD feature includes a rapidly increasing camber-angle that is 0.2 non-dimensional camber-angle units higher than the non-dimensionalized camber-angle of the uniform portion.Type: ApplicationFiled: October 5, 2022Publication date: April 18, 2024Inventor: Bronwyn Power
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Publication number: 20240052747Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: ApplicationFiled: August 18, 2023Publication date: February 15, 2024Inventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
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Publication number: 20240052746Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: ApplicationFiled: August 8, 2023Publication date: February 15, 2024Inventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
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Patent number: 11231044Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4 < ? 0 1 ? [ ? 0 x ? ? ? ? dx ] ? dx ? 0 1 ? ? ? ? dx ? 0.5 where x is chord location, ? ? = ? i - ? ? i - ? e , ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.Type: GrantFiled: October 31, 2018Date of Patent: January 25, 2022Assignee: Rolls-Royce CorporationInventor: Bronwyn Power
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Patent number: 11060527Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about ?5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.Type: GrantFiled: October 28, 2016Date of Patent: July 13, 2021Assignee: Rolls-Royce CorporationInventors: Bronwyn Power, Jonathan M. Rivers
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Patent number: 10935041Abstract: In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.Type: GrantFiled: June 29, 2016Date of Patent: March 2, 2021Assignee: Rolls-Royce CorporationInventor: Bronwyn Power
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Patent number: 10605257Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about ?5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.Type: GrantFiled: October 28, 2016Date of Patent: March 31, 2020Assignee: Rolls-Royce CorporationInventors: Bronwyn Power, Jonathan M. Rivers
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Patent number: 10539024Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: GrantFiled: July 7, 2017Date of Patent: January 21, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Roy D. Fulayter, Daniel K. Vetters, Bronwyn Power
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Patent number: 10309236Abstract: A gas turbine engine strut has a forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body has a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.Type: GrantFiled: December 31, 2013Date of Patent: June 4, 2019Assignee: Rolls-Royce CorporationInventor: Bronwyn Power
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Patent number: 10294862Abstract: A turbine engine casing flow-path segment that is locally diffusing, followed by a flow-path segment contracting in the vicinity of a fan blade. This contraction accelerates the fluid flow axially forward of the fan blade leading edge at the tip and converges with the linear flow-path aft of the fan blade leading edge but forward of the fan blade trailing edge. More diffused fluid flow results in increased flow capacity of the fan, and increased fan efficiency.Type: GrantFiled: November 23, 2015Date of Patent: May 21, 2019Assignee: ROLLS-ROYCE CORPORATIONInventors: Roy David Fulayter, Aaron Joseph King, Bronwyn Power, Greg Hebert
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Publication number: 20190072103Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4 < ? 0 1 ? [ ? 0 x ? ? ? ? dx ] ? dx ? 0 1 ? ? ? ? dx ? 0.5 where x is chord location, ? ? = ? i - ? ? i - ? e , ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.Type: ApplicationFiled: October 31, 2018Publication date: March 7, 2019Inventor: Bronwyn Power
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Patent number: 10145383Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as ? ? = ? i - ? ? i - ? e where ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.Type: GrantFiled: February 19, 2016Date of Patent: December 4, 2018Assignee: Rolls-Royce CorporationInventor: Bronwyn Power
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Publication number: 20180231016Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about ?5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.Type: ApplicationFiled: October 28, 2016Publication date: August 16, 2018Inventors: Bronwyn Power, Jonathan M. Rivers
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Publication number: 20180119705Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about ?5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.Type: ApplicationFiled: October 28, 2016Publication date: May 3, 2018Inventors: Bronwyn Power, Jonathan M. Rivers
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Publication number: 20180003189Abstract: In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.Type: ApplicationFiled: June 29, 2016Publication date: January 4, 2018Applicant: Rolls-Royce CorporationInventor: Bronwyn Power
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Publication number: 20170306762Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: ApplicationFiled: July 7, 2017Publication date: October 26, 2017Inventors: Roy D. Fulayter, Daniel K. Vetters, Bronwyn Power
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Patent number: 9739158Abstract: An airfoil member is disclosed having an attachment feature such as a fir tree or dovetail design that includes a curved profile formed from a combination of curves. In one embodiment, the curved profile can be a compound curve formed by a forward curve and a rearward curve that are joined at a point of common tangency. In another embodiment, the curved profile can include curves that do not meet at a common tangency. A cut out can be formed in the curved profile. In some forms, the cut out is formed on a pressure face of the attachment feature.Type: GrantFiled: December 5, 2013Date of Patent: August 22, 2017Assignee: Rolls-Royce CorporationInventors: Jonathan M. Rivers, Bronwyn Powers
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Patent number: 9708914Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: GrantFiled: December 6, 2013Date of Patent: July 18, 2017Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.Inventors: Roy D Fulayter, Daniel K Vetters, Bronwyn Power
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Publication number: 20170145917Abstract: A turbine engine casing flow-path segment that is locally diffusing, followed by a flow-path segment contracting in the vicinity of a fan blade. This contraction accelerates the fluid flow axially forward of the fan blade leading edge at the tip and converges with the linear flow-path aft of the fan blade leading edge but forward of the fan blade trailing edge. More diffused fluid flow results in increased flow capacity of the fan, and increased fan efficiency.Type: ApplicationFiled: November 23, 2015Publication date: May 25, 2017Applicant: Rolls-Royce CorporationInventors: Roy David Fulayter, Aaron Joseph King, Bronwyn Power, Greg Hebert
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Patent number: 9568009Abstract: A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.Type: GrantFiled: November 27, 2013Date of Patent: February 14, 2017Assignee: Rolls-Royce CorporationInventors: Bronwyn Power, Roy D. Fulayter, Jonathan M. Rivers