发明名称 Turbomachine blade mounting system
摘要 Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade, wherein the mounting segment has a multi-piece assembly configured to mount in a radial direction into a slot of a turbomachine rotor.
申请公布号 US9175572(B2) 申请公布日期 2015.11.03
申请号 US201213448238 申请日期 2012.04.16
申请人 General Electric Company 发明人 McMurray Timothy Scott;Farineau Thomas Joseph
分类号 F01D5/14;F01D5/30 主分类号 F01D5/14
代理机构 Fletcher Yoder, P.C. 代理人 Fletcher Yoder, P.C.
主权项 1. A system, comprising: a turbomachine rotor comprising a slot; and a turbomachine blade mounting segment having first and second configurations, wherein the first configuration is configured to tangentially insert in a radial direction into the slot of the turbomachine rotor, and the second configuration is configured to expand relative to the first configuration to retain the turbomachine blade mounting segment in the slot, wherein the turbomachine blade mounting segment comprises a first dovetail segment, a second dovetail segment, a captured spreader piece, and a cover portion having a retention feature, the cover portion is configured to couple the first dovetail segment, the second dovetail segment, and the captured spreader piece to one another, and the first dovetail segment, the second dovetail segment, and the captured spreader piece are each configured to be individually inserted in the radial direction into the slot, and at least one portion of the turbomachine blade mounting segment is integrally formed with a turbomachine blade configured to be coupled to the turbomachine rotor by the turbomachine blade mounting segment.
地址 Schenectady NY US