Patents by Inventor Nina Wolfrum
Nina Wolfrum 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: 11927109Abstract: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.Type: GrantFiled: December 8, 2020Date of Patent: March 12, 2024Assignee: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Tobias Froebel, Nina Wolfrum, Sebastian Mann
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Publication number: 20230026899Abstract: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.Type: ApplicationFiled: December 8, 2020Publication date: January 26, 2023Applicant: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Tobias Froebel, Nina Wolfrum, Sebastian Mann
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Patent number: 10458248Abstract: A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.Type: GrantFiled: November 30, 2016Date of Patent: October 29, 2019Assignee: MTU Aero Engines AGInventors: Nina Wolfrum, Markus Brettschneider, Inga Mahle, Markus Schlemmer, Martin Pernleitner
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Patent number: 10436044Abstract: The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.Type: GrantFiled: December 2, 2016Date of Patent: October 8, 2019Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
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Patent number: 10208765Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element, which is arranged in a flow duct, and a leading edge and a trailing edge, which are joined to each other through a pressure side and a suction side, wherein, a new and novel profile section of the blade or vane element is provided.Type: GrantFiled: January 19, 2016Date of Patent: February 19, 2019Assignee: MTU Aero Engines AGInventors: Tobias Froebel, Sebastian Mann, Nina Wolfrum, Sergio Elorza Gomez
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Publication number: 20170159443Abstract: The invention relates to a blade or vane ring for a gas turbine having a plurality of blades or vanes that are arranged next to one another in the peripheral direction (UR), wherein blades or vanes have a flow segment extending essentially in the radial direction, these blades or vanes having a convex suction side, a concave pressure side, a leading edge and a trailing edge, wherein the suction side and the pressure side are joined together by the leading edge and the trailing edge, wherein the blades or vanes transition into an annular segment of the blade or vane ring radially inside and/or radially outside, wherein annular segment connects a first blade or vane (12) and a second blade or vane, which are adjacent to one another, between the suction side of the first blade or vane and the pressure side of the second blade or vane.Type: ApplicationFiled: December 2, 2016Publication date: June 8, 2017Inventors: Martin Pernleitner, Inga Mahle, Nina Wolfrum, Markus Brettschneider, Markus Schlemmer
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Publication number: 20170159465Abstract: The invention relates to a guide vane cluster (10) for a turbomachine, in particular for a turbojet engine, having at least two vanes (14) that are joined together by way of at least one common platform (12, 16) for the radial delimiting of a flow channel of the turbomachine, wherein each vane (14) has a vane element (17) with a suction side (18) and a pressure side (20) that are joined together by a leading edge (22) and a trailing edge (24), wherein the at least two vanes (14) have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.Type: ApplicationFiled: December 2, 2016Publication date: June 8, 2017Inventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
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Publication number: 20170159444Abstract: A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.Type: ApplicationFiled: November 30, 2016Publication date: June 8, 2017Inventors: Nina Wolfrum, Markus Brettschneider, Inga Mahle, Markus Schlemmer, Martin Pernleitner
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Publication number: 20160215788Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element (1), which is arranged in a flow duct, and a leading edge (LE) and a trailing edge (TE), which are joined to each other through a pressure side and a suction side (PS, SS), wherein, a new and novel profile section of the blade or vane element is provided.Type: ApplicationFiled: January 19, 2016Publication date: July 28, 2016Inventors: Tobias Froebel, Sebastian Mann, Nina Wolfrum, Sergio Elorza Gomez