发明名称 Turbine engine disk spacers
摘要 A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The spacers may provide a longitudinal compression force that increases with rotational speed.
申请公布号 US7186079(B2) 申请公布日期 2007.03.06
申请号 US20040985863 申请日期 2004.11.10
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 SUCIU GABRIEL L.;NORRIS JAMES W.
分类号 F01D5/06 主分类号 F01D5/06
代理机构 代理人
主权项
地址
您可能感兴趣的专利