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
US2009169370(A1)
申请公布日期
2009.07.02
申请号
US20070967176
申请日期
2007.12.29
申请人
GENERAL ELECTRIC COMPANY
发明人
MORGAN CLIVE ANDREW;HEFFRON TODD STEPHEN;FONSEKA SANJEEWA THUSITHA
