Invention Grant
US08147207B2 Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion
有权
压缩机叶片具有前缘扫掠与前缘二面体的比例，沿着径向外部部分为1：1至3：1的范围
- Patent Title: Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion
- Patent Title (中): 压缩机叶片具有前缘扫掠与前缘二面体的比例，沿着径向外部部分为1：1至3：1的范围
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Application No.: US12204034Application Date: 2008-09-04
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Publication No.: US08147207B2Publication Date: 2012-04-03
- Inventor: John Orosa , Matthew Montgomery
- Applicant: John Orosa , Matthew Montgomery
- Applicant Address: US FL Orlando
- Assignee: Siemens Energy, Inc.
- Current Assignee: Siemens Energy, Inc.
- Current Assignee Address: US FL Orlando
- Main IPC: F01D5/14
- IPC: F01D5/14
Abstract:
An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.
Public/Granted literature
- US20100054946A1 COMPRESSOR BLADE WITH FORWARD SWEEP AND DIHEDRAL Public/Granted day:2010-03-04
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