Patents by Inventor Wagner Magalhaes
Wagner Magalhaes 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: 11156095Abstract: A turbocharger turbine wheel includes a hub; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, between the minimum axial coordinate position and the maximum axial coordinate position, each of the blades includes a first lean angle at a first axial coordinate position defined with respect to a first radial line, a second lean angle at a second axial coordinate position defined with respect to a second radial line, and a lean angle inflection region at an inflection axial coordinate position that is between the first axial coordinate position and the second axial coordinate position.Type: GrantFiled: July 29, 2019Date of Patent: October 26, 2021Assignee: Garrett Transportation I Inc.Inventors: Ashraf Mohamed, Wagner Magalhaes
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Patent number: 11041405Abstract: A turbocharger turbine assembly can include a turbine housing that includes a longitudinal axis, an exhaust inlet, a shroud portion, and an exhaust outlet; and a turbine wheel that includes a hub that includes a rotational axis aligned with the longitudinal axis of the turbine housing, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, from the minimum axial coordinate position to the maximum axial coordinate position, the shroud edge has a decreasing radial coordinate position.Type: GrantFiled: September 18, 2019Date of Patent: June 22, 2021Assignee: Garrett Transportation I Inc.Inventors: Ashraf Mohamed, Wagner Magalhaes
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Publication number: 20210079809Abstract: A turbocharger turbine assembly can include a turbine housing that includes a longitudinal axis, an exhaust inlet, a shroud portion, and an exhaust outlet; and a turbine wheel that includes a hub that includes a rotational axis aligned with the longitudinal axis of the turbine housing, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, from the minimum axial coordinate position to the maximum axial coordinate position, the shroud edge has a decreasing radial coordinate position.Type: ApplicationFiled: September 18, 2019Publication date: March 18, 2021Inventors: Ashraf Mohamed, Wagner Magalhaes
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Publication number: 20210032993Abstract: A turbocharger turbine wheel includes a hub; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, between the minimum axial coordinate position and the maximum axial coordinate position, each of the blades includes a first lean angle at a first axial coordinate position defined with respect to a first radial line, a second lean angle at a second axial coordinate position defined with respect to a second radial line, and a lean angle inflection region at an inflection axial coordinate position that is between the first axial coordinate position and the second axial coordinate position.Type: ApplicationFiled: July 29, 2019Publication date: February 4, 2021Inventors: Ashraf Mohamed, Wagner Magalhaes
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Patent number: 10443387Abstract: A turbine wheel for a turbocharger is provided. The turbine wheel includes a plurality of blades and a mid-plane is defined between a pressure side and a suction side of adjacent blades. Each of the blades has a leading edge, and is coupled to the wheel hub along a respective blade hub camber line. The wall has a first radii at the leading edge that extends for a first circumferential distance adjacent to the suction side. The first circumferential distance is at least 12% of a circumferential distance that extends between adjacent blades. The wheel hub includes a plurality of scallops defined through the wall. Each of the scallops is asymmetrical about the mid-plane. For each of the scallops, the wall has a second minimum radii defined offset from the mid-plane toward the suction side and a third minimum radii defined offset from the mid-plane toward the pressure side.Type: GrantFiled: May 24, 2017Date of Patent: October 15, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Ashraf Mohamed, William Joseph Smith, Wagner Magalhaes, Derek Cooper
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Publication number: 20180340422Abstract: A turbine wheel for a turbocharger is provided. The turbine wheel includes a plurality of blades and a mid-plane is defined between a pressure side and a suction side of adjacent blades. Each of the blades has a leading edge, and is coupled to the wheel hub along a respective blade hub camber line. The wall has a first radii at the leading edge that extends for a first circumferential distance adjacent to the suction side. The first circumferential distance is at least 12% of a circumferential distance that extends between adjacent blades. The wheel hub includes a plurality of scallops defined through the wall. Each of the scallops is asymmetrical about the mid-plane. For each of the scallops, the wall has a second minimum radii defined offset from the mid-plane toward the suction side and a third minimum radii defined offset from the mid-plane toward the pressure side.Type: ApplicationFiled: May 24, 2017Publication date: November 29, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Ashraf Mohamed, William Joseph Smith, Wagner Magalhaes, Derek Cooper
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Publication number: 20140241866Abstract: A turbocharger turbine wheel includes a hub and a plurality of blades. Both the center of mass of the hub and the center of mass of the plurality of blades are on an axis of rotation. The blades are circumferentially spaced such that they are rotationally asymmetric. Each consecutive pair of blades is characterized by a spacing angle. A line that intersects with and is normal to the axis of rotation defines a plane of symmetry, and the spacing angles are symmetric across the plane of symmetry.Type: ApplicationFiled: February 25, 2013Publication date: August 28, 2014Applicant: Honeywell International Inc.Inventors: William Joseph Smith, Ashraf Mohamed, Wagner Magalhaes
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Publication number: 20060174611Abstract: An exhaust gas cooler comprising an inlet chamber shaped to restrict exhaust gas flow to certain exhaust gas passages provided therein is disclosed. The inlet chamber may comprise a flow deflector which deflects a proportion of exhaust gas into, for example, the upper exhaust gas cooling passages thus restricting flow to lower exhaust gas cooling passages. In one embodiment the flow deflector is rotatably mounted and can also function as a bypass valve. Alternatively apertures provided within plates which can collectively define the inlet chamber may be of a differing size to restrict exhaust gas flow to certain exhaust gas cooling passages. A more balanced flow through the various exhaust gas cooling passages results increasing heat-exchange efficiency of the exhaust gas cooler.Type: ApplicationFiled: February 7, 2005Publication date: August 10, 2006Inventors: Roland Dilley, Richard Beldam, Keith Agee, Wagner Magalhaes