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发明名称
low-Modulus Gas-Turbine Compressor Blade
摘要
The present invention relates to an aircraft gas-turbine compressor blade having an airfoil with a leading edge, with at least the area of the leading edge being made from a low-modulus titanium alloy.
申请公布号
US2014030109(A1)
申请公布日期
2014.01.30
申请号
US201313953934
申请日期
2013.07.30
申请人
ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
发明人
SCHREIBER KARL
分类号
F01D5/28
主分类号
F01D5/28
代理机构
代理人
主权项
地址
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