An integrally bladed rotor (10) for use in a gas turbine engine comprises a plurality of pairs of airfoil blades (18). Each pair of blades (18) has a spar (20) which extends from a first tip (24) of a first one of the airfoil blades (18) in the pair to a second tip (26) of a second one of the airfoil blades (18) in the pair. The rotor further preferably comprises an outer shroud (12) integrally joined to the first and second tips (24,26) in each pair of airfoil blades (18) and an inner diameter hub (14). <IMAGE>
申请公布号
EP1396608(B1)
申请公布日期
2009.07.22
申请号
EP20030255505
申请日期
2003.09.03
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
HORNICK, DAVID CHARLES;EUVINO, FRANK J., JR.;ROACH, JAMES TYLER