Invention Grant
US08827654B2 Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
有权
具有自磨锐前缘结构的燃气涡轮发动机的压缩机叶片
- Patent Title: Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
- Patent Title (中): 具有自磨锐前缘结构的燃气涡轮发动机的压缩机叶片
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Application No.: US13188759Application Date: 2011-07-22
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Publication No.: US08827654B2Publication Date: 2014-09-09
- Inventor: Karl Schreiber , Werner Beck
- Applicant: Karl Schreiber , Werner Beck
- Applicant Address: DE DE
- Assignee: Rolls-Royce Deutschland Ltd & Co KG,Formtech GmbH
- Current Assignee: Rolls-Royce Deutschland Ltd & Co KG,Formtech GmbH
- Current Assignee Address: DE DE
- Agency: Shuttleworth & Ingersoll, PLC
- Agent Timothy J. Klima
- Priority: DE102010032097 20100723
- Main IPC: F01D5/28
- IPC: F01D5/28 ; F04D29/32 ; F04D29/02
Abstract:
A compressor blade 1 of a gas-turbine engine has a flow-exposed leading edge 2. A component 3, made of wear-resistant material and featuring a higher erosive wear resistance than the base material, is attached to at least part of a length of the leading edge 2 The component 3 forming the flow-exposed leading edge 2 is strip-shaped, has an essentially rectangular cross-section and, with reference to a sectional plane perpendicular to the radial direction, is arranged only on an inflow side of the compressor blade profile in a partial area of a sectional surface of the inflow area.
Public/Granted literature
- US20120020802A1 COMPRESSOR BLADE OF A GAS-TURBINE ENGINE WITH A SELF-SHARPENING LEADING-EDGE STRUCTURE Public/Granted day:2012-01-26
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