公开(公告)号：US20190120061A1

公开(公告)日：2019-04-25

申请号：US16163633

申请日：2018-10-18

申请人： MTU Aero Engines AG

发明人： Wolfgang Horn ,  Daniel Theurich ,  Martin Becker ,  Axel Stettner ,  Wilfried Schuette ,  Michael Junge ,  Hans-Peter Hackenberg ,  Alexander Halcoussis ,  Hannes Wolf

IPC分类号： F01D5/14

摘要： 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.

公开(公告)号：US20230160309A1

公开(公告)日：2023-05-25

申请号：US18056999

申请日：2022-11-18

申请人： MTU Aero Engines AG

发明人： Axel Stettner ,  Ulf Koellmann

IPC分类号： F01D5/20

CPC分类号： F01D5/20 ,  F05D2240/307 ,  F05D2260/941

摘要： 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.

公开(公告)号：US11697995B2

公开(公告)日：2023-07-11

申请号：US18056999

申请日：2022-11-18

申请人： MTU Aero Engines AG

发明人： Axel Stettner ,  Ulf Koellmann

IPC分类号： F01D5/20

CPC分类号： F01D5/20 ,  F05D2240/307 ,  F05D2260/941

摘要： 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.

公开(公告)号：US20240240564A1

公开(公告)日：2024-07-18

申请号：US18408722

申请日：2024-01-10

申请人： MTU Aero Engines AG

发明人： Benjamin Hanschke ,  Benjamin Linke ,  Axel Stettner

IPC分类号： F01D5/14

CPC分类号： F01D5/147 ,  F05D2240/305 ,  F05D2240/306

摘要： A blisk has at least one blade, with a blade airfoil and a blade root; a platform, the blade being integrally attached to the platform; and a fillet arranged on the blade root and between the blade airfoil and the platform. The fillet merges into the blade at a blade connection. The fillet merges into the platform at a platform connection. The fillet extends with a longitudinal extent around the blade root and a transverse extent from the platform to the blade airfoil. The fillet has a variable radius along the transverse extent. The variable radius has, at least in a first section of the fillet, a minimum radius which, at least in the first section, is spaced apart from the platform by at least 15% of the transverse extent along the transverse extent of the fillet.

公开(公告)号：US11585223B2

公开(公告)日：2023-02-21

申请号：US17718710

申请日：2022-04-12

申请人： MTU Aero Engines AG

发明人： Wilfried Schuette ,  Axel Stettner ,  Michael Junge

IPC分类号： F01D5/14

摘要： 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.

公开(公告)号：US20230043732A1

公开(公告)日：2023-02-09

申请号：US17817177

申请日：2022-08-03

申请人： MTU Aero Engines AG

发明人： Axel Stettner ,  Christian Roth ,  Werner Humhauser

IPC分类号： F01D25/28 ,  F04D29/56

摘要： 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.