Patents by Inventor Axel Stettner
Axel Stettner 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).
-
Patent number: 11697995Abstract: The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.Type: GrantFiled: November 18, 2022Date of Patent: July 11, 2023Assignee: MTU Aero Engines AGInventors: Axel Stettner, Ulf Koellmann
-
Publication number: 20230160309Abstract: The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.Type: ApplicationFiled: November 18, 2022Publication date: May 25, 2023Applicant: MTU Aero Engines AGInventors: Axel Stettner, Ulf Koellmann
-
Patent number: 11585223Abstract: A curved contour of the lateral surface of a blade arrangement includes in at least one meridian section on mutually opposite sides of a blade airfoil an intersection point that is closer to the blade airfoil front edge, and an intersection point that is closer to the blade airfoil rear edge, and a best-fit line of least square distances from the curved contour. The curved contour includes first and/or the second contour section which meet specified conditions.Type: GrantFiled: April 12, 2022Date of Patent: February 21, 2023Assignee: MTU Aero Engines AGInventors: Wilfried Schuette, Axel Stettner, Michael Junge
-
Publication number: 20230043732Abstract: The invention relates to a connecting device for an adjustable blade or vane of a gas turbine, comprising a journal element connected to a respective blade or vane and a lever element connected to the journal element, wherein the lever element and the journal element are jointly movable about a journal axis of rotation. A clamping element is provided, being situated between the lever element and the journal element, such that a force-locking connection is or can be produced between the journal element, the clamping element, and the lever element. The lever element, the clamping element, and the journal element are aligned relative to each other by means of a positioning element, the positioning element being received in a first seat of the journal element and a corresponding second seat of the lever element.Type: ApplicationFiled: August 3, 2022Publication date: February 9, 2023Applicant: MTU Aero Engines AGInventors: Axel Stettner, Christian Roth, Werner Humhauser
-
Patent number: 11525369Abstract: A vane assembly for a turbomachine includes a variable vane (10-15), the vane having at least one first, in particular plane or curved, engagement surface (11; 11?) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.Type: GrantFiled: November 28, 2018Date of Patent: December 13, 2022Assignee: MTU Aero Engines AGInventors: Vitalis Mairhanser, Manuel Hein, Axel Stettner
-
Publication number: 20220333488Abstract: A curved contour of the lateral surface of a blade arrangement includes in at least one meridian section on mutually opposite sides of a blade airfoil an intersection point that is closer to the blade airfoil front edge, and an intersection point that is closer to the blade airfoil rear edge, and a best-fit line of least square distances from the curved contour. The curved contour includes first and/or the second contour section which meet specified conditions.Type: ApplicationFiled: April 12, 2022Publication date: October 20, 2022Inventors: Wilfried SCHUETTE, Axel STETTNER, Michael JUNGE
-
Patent number: 10844726Abstract: The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.Type: GrantFiled: October 18, 2018Date of Patent: November 24, 2020Assignee: MTU Aero Engines AGInventors: Wolfgang Horn, Daniel Theurich, Martin Becker, Axel Stettner, Wilfried Schuette, Michael Junge, Hans-Peter Hackenberg, Alexander Halcoussis, Hannes Wolf
-
Publication number: 20190178100Abstract: A vane assembly including a variable vane (10-15) for a turbomachine is provided, the vane having at least one first, in particular plane or curved, engagement surface (11; 11?) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.Type: ApplicationFiled: November 28, 2018Publication date: June 13, 2019Inventors: Vitalis Mairhanser, Manuel Hein, Axel Stettner
-
Publication number: 20190120061Abstract: The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.Type: ApplicationFiled: October 18, 2018Publication date: April 25, 2019Applicant: MTU Aero Engines AGInventors: Wolfgang Horn, Daniel Theurich, Martin Becker, Axel Stettner, Wilfried Schuette, Michael Junge, Hans-Peter Hackenberg, Alexander Halcoussis, Hannes Wolf