A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.
申请公布号
WO2015130382(A3)
申请公布日期
2015.11.05
申请号
WO2014US69774
申请日期
2014.12.11
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
TURNER, MATTHEW, A.;ALARCON, ANDREW, G.;BUGAJ, SHARI, L.