A turbine nozzle segment includes a band having a plurality of tabs, an airfoil extending from the band and a support structure attached to the tabs. The support structure has a plurality of biasing structures.
申请公布号
GB2468438(B)
申请公布日期
2012.09.19
申请号
GB20100010144
申请日期
2008.12.18
申请人
GENERAL ELECTRIC COMPANY
发明人
CLIVE ANDREW MORGAN;TODD STEPHEN HEFFRON;SANJEEWA THUSITHA FONSEKA
