发明名称 Gas turbine bladed disk
摘要 A new and improved rotor blade and bladed disk assembly are disclosed. In the preferred embodiment, the blade includes a curved and twisted dovetail disposed generally parallel to a sloping outer perimeter of a rotor disk which allows the dovetail to accommodate centrifugal loading of the blade through complementary dovetail slots for obtaining improved low cycle fatigue and high cycle fatique life limits and a relatively stiff blade for maintaining 2/REV margin. In an exemplary embodiment, the dovetail comprises a section of a helix and the dovetail is self retaining in the dovetail slot against axial components of centrifugal loading.
申请公布号 US5067876(A) 申请公布日期 1991.11.26
申请号 US19900500974 申请日期 1990.03.29
申请人 GENERAL ELECTRIC COMPANY 发明人 MOREMAN, III, OTIS S.
分类号 F01D5/02;F01D5/30 主分类号 F01D5/02
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