An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
申请公布号
EP2932039(A1)
申请公布日期
2015.10.21
申请号
EP20130863829
申请日期
2013.12.04
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
SUCIU, GABRIEL, L.;CHANDLER, JESSE, M.;MERRY, BRIAN, D.
