发明名称 GAS TURBINE ENGINE ROTOR
摘要 A rotor disk (60) includes a web (66) that extends from a rim (62) radially inward to a bore (68). A spacer (76) is integral with and extends generally axially from the rim (62). The spacer (76) includes a flow path surface (78) adjacent to an end wall of the rim (62). An inner surface (92) is spaced radially inwardly from the flow path surface (78) and extends between first and second axial locations. A fillet (94) interconnects the inner surface (92) and the web (66). The inner surface (92) is tangent to the fillet (94) at the first axial location. The second axial location axially aligns beneath vanes (84) and surrounded by the inner surface (92). The spacer (76) has first and second radial thicknesses (96, 98) respectively disposed at the first and second axial locations. The first and second radial thicknesses (96, 98) are different than one another. The spacer (76) is at least partially tapering axially between the first and second axial locations.
申请公布号 EP3045658(A1) 申请公布日期 2016.07.20
申请号 EP20160151287 申请日期 2016.01.14
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 POTTER, CHRISTOPHER L.
分类号 F01D5/06;F01D5/34;F01D11/00 主分类号 F01D5/06
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