公开(公告)号：US20230279777A1

公开(公告)日：2023-09-07

申请号：US18176304

申请日：2023-02-28

申请人： MTU Aero Engines AG

发明人： Benjamin Hanschke ,  Alexander Halcoussis ,  Amadeusz Rekosiewicz ,  Moritz Thon ,  Benjamin Linke

IPC分类号： F01D5/34

CPC分类号： F01D5/34 ,  F05D2240/80

摘要： The invention relates to a blisk segment for a gas turbine, comprising at least one first blade having an airfoil, a leading edge, a trailing edge, a blade root, a suction side and a pressure side, a pedestal, and a first fillet having a device for influencing crack growth. The robustness of the gas turbine is improved in accordance with the invention in that, at the leading edge of the first blade, at least on the first fillet, a first surface structure is arranged and interacts with the crack-influencing device for influencing crack growth and for flow influencing.

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：US12018584B2

公开(公告)日：2024-06-25

申请号：US17930012

申请日：2022-09-06

申请人： MTU Aero Engines AG

发明人： Benjamin Hanschke ,  Michael Junge ,  Astrid Kraus ,  Francesca Storti

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F05D2220/3216 ,  F05D2240/301 ,  F05D2240/303

摘要： The invention relates to an airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip, wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of which to each other represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle.

公开(公告)号：US20230070018A1

公开(公告)日：2023-03-09

申请号：US17930012

申请日：2022-09-06

申请人： MTU Aero Engines AG

发明人： Benjamin Hanschke ,  Michael Junge ,  Astrid Kraus ,  Francesca Storti

IPC分类号： F01D5/14

摘要： The invention relates to an airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip, wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of which to each other represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle.