An air seal assembly (10) includes a featherseal (76) engaged between adjacent turbine engine components (54) to close a gap therebetween. The featherseal (76) includes a first lateral tab (80) and a second lateral tab (82) which defines a tab space (84) therebetween. The tab space (84) locks the featherseal (76) into the turbine engine component (54) to prevent fore-aft movement thereof.
申请公布号
EP1965031(B1)
申请公布日期
2016.07.27
申请号
EP20080250314
申请日期
2008.01.25
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
SPANGLER, BRANDON W.;MONGILLO, DOMINIC J.;PAAUWE, CORNEIL S.