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.