Patents by Inventor Dieter Freno
Dieter Freno 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: 11959399Abstract: Blade root receptacle for receiving a blade root of a rotor blade of a turbomachine. The blade root receptacle, for radially bearing in a form-fitting manner on the blade root, has a supporting flank which, in terms of a rotation axis, at least in proportions faces radially inward, wherein the supporting flank is provided with a convexity which, when viewed in an axially perpendicular section, at least in portions has a convex shape and, also when viewed in an axially parallel section, at least in portions has a convex shape.Type: GrantFiled: August 9, 2022Date of Patent: April 16, 2024Assignee: MTU AERO ENGINES AGInventors: Kilian Bayer, David Koch, Susanne Poesl, Markus Zeis, Andreas Hieber, Jens Truebenbach, Dieter Freno, Hermann Nachtigall, Miriam Rimke
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Patent number: 11905852Abstract: An intermediate element is for a blade/rotor disk connection in a rotor of a fluid flow machine. The intermediate element is adapted to a shape of a blade root of a blade and to a blade root slot in a rotor disk for receiving the blade root such that, when arranged between the blade root and rotor disk, the intermediate element prevents contact between the blade root and rotor disk. The intermediate element has, on an outer surface that faces the rotor disk, at least one protrusion to reduce an air flow parallel to an axis of rotation of the rotor between the rotor disk and the intermediate element; and on an inner surface that faces the blade root, a recess that corresponds to the at least one protrusion.Type: GrantFiled: July 14, 2020Date of Patent: February 20, 2024Assignee: MTU AERO ENGINES AGInventors: Martin Pernleitner, Klaus Wittig, Manfred Dopfer, Dieter Freno, Tino Hummel
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Patent number: 11753950Abstract: A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.Type: GrantFiled: May 18, 2020Date of Patent: September 12, 2023Assignee: MTU AERO ENGINES AGInventors: Martin Pernleitner, Dieter Freno, Klaus Wittig, Christian Eichler, Lutz Friedrich, Johannes Linhard
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Publication number: 20230194384Abstract: The present invention relates to a method for testing a component, in particular an aircraft engine, comprising the steps of: determining (S40) a value of a first toleranced parameter (A1; A2) of the component; determining (S50) a value of a second toleranced parameter (E1; ...; E4) of the component; and classifying (S70) the component in a predefined quality class if this value pair lies outside of a predefined tolerance range, the upper and/or lower limit (G) of which for the second parameter depends on the first parameter, in particular linearly, in at least one first permissible value range (Ta1,1) of the first parameter.Type: ApplicationFiled: May 18, 2020Publication date: June 22, 2023Inventors: Christian EICHLER, Dieter FRENO, Andreas HIEBER, Philipp FARAH, Salome GASSMAnn
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Publication number: 20230128349Abstract: The invention relates to a rotor for a turbomachine, having at least one blade and having at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.Type: ApplicationFiled: December 7, 2020Publication date: April 27, 2023Applicant: MTU Aero Engines AGInventors: Martin Pernleitner, Dieter Freno, Manfred Dopfer, Tino Hummel, Klaus Wittig
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Publication number: 20230046019Abstract: Blade root receptacle for receiving a blade root of a rotor blade of a turbomachine. The blade root receptacle, for radially bearing in a form-fitting manner on the blade root, has a supporting flank which, in terms of a rotation axis, at least in proportions faces radially inward, wherein the supporting flank is provided with a convexity which, when viewed in an axially perpendicular section, at least in portions has a convex shape and, also when viewed in an axially parallel section, at least in portions has a convex shape.Type: ApplicationFiled: August 9, 2022Publication date: February 16, 2023Inventors: Kilian BAYER, David KOCH, Susanne POESL, Markus ZEIS, Andreas HIEBER, Jens TRUEBENBACH, Dieter FRENO, Hermann NACHTIGALL, Miriam RIMKE
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Publication number: 20230003137Abstract: A rotor blade system includes a blade root, a blade neck adjoining the blade root, an airfoil adjoining the blade neck, a radially outer partition wall, an axially forward partition wall and an axially rearward partition wall, connected to the radially outer partition wall such that the partition walls surround the blade neck on three sides, the partition walls projecting beyond the blade neck in the circumferential direction, and further including a blade root protection plate designed to be arranged on the blade root. It is provided that the blade root protection plate have at least one sealing portion that extends in the axial direction from the forward partition wall to the rearward partition wall and whose radially outer side is disposed opposite the radially outer partition wall when the blade root protection plate is arranged on the blade root.Type: ApplicationFiled: August 5, 2020Publication date: January 5, 2023Inventors: Martin PERNLEITNER, Dieter FRENO, Manfred DOPFER
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Publication number: 20220268164Abstract: An intermediate element is for a blade/rotor disk connection in a rotor of a fluid flow machine. The intermediate element is adapted to a shape of a blade root of a blade and to a blade root slot in a rotor disk for receiving the blade root such that, when arranged between the blade root and rotor disk, the intermediate element prevents contact between the blade root and rotor disk. The intermediate element has, on an outer surface that faces the rotor disk, at least one protrusion to reduce an air flow parallel to an axis of rotation of the rotor between the rotor disk and the intermediate element; and on an inner surface that faces the blade root, a recess that corresponds to the at least one protrusion.Type: ApplicationFiled: July 14, 2020Publication date: August 25, 2022Inventors: Martin Pernleitner, Klaus Wittig, Manfred Dopfer, Dieter Freno, Tino Hummel
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Publication number: 20220251959Abstract: A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.Type: ApplicationFiled: May 18, 2020Publication date: August 11, 2022Inventors: Martin PERNLEITNER, Dieter FRENO, Klaus WITTIG, Christian EICHLER, Lutz FRIEDRICH, Johannes LINHARD
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Patent number: 11255196Abstract: A cooling system for cooling a turbine blade with a cooling fluid via an internal flow passage formed in the turbine blade extending from an inlet to an outlet edge having a first passage section defining a first flow direction, a second passage section defining a second flow direction, a wall between the first and second passage section and a diverter, between the first and the second passage section. The wall in a region of the diverter forms a pier head which extends into the region of the first passage section and thereby reduces the flow cross section of the flow passage.Type: GrantFiled: August 9, 2019Date of Patent: February 22, 2022Assignees: MTU AERO ENGINES, MAN Energy Solutions SEInventors: Dieter Freno, Thorsten Pöhler, Martin Pernleitner, Paul Storm, Electra Stavropoulou, Dirk Frank
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Publication number: 20200049015Abstract: A cooling system for cooling a turbine blade with a cooling fluid via an internal flow passage formed in the turbine blade extending from an inlet to an outlet edge having a first passage section defining a first flow direction, a second passage section defining a second flow direction, a wall between the first and second passage section and a diverter, between the first and the second passage section. The wall in a region of the diverter forms a pier head which extends into the region of the first passage section and thereby reduces the flow cross section of the flow passage.Type: ApplicationFiled: August 9, 2019Publication date: February 13, 2020Inventors: Dieter FRENO, Thorsten PÖHLER, Martin PERNLEITNER, Paul STORM, Electra STAVROPOULOU, Dirk FRANK
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Patent number: 8870542Abstract: A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.Type: GrantFiled: February 2, 2010Date of Patent: October 28, 2014Assignee: MTU Aero Engines GmbHInventors: Manfred Feldmann, Markus Uecker, Benedikt Heidenreich, Dieter Freno
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Publication number: 20110293408Abstract: A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.Type: ApplicationFiled: February 2, 2010Publication date: December 1, 2011Applicant: MTU Aero Engines GmbHInventors: Manfred Feldmann, Markus Uecker, Benedikt Heidenreich, Dieter Freno