<p>A spacer (62C) for a gas turbine engine includes a rotor ring (84) defined along an axis of rotation and a plurality of core gas path seals (82) which extend from the rotor ring (84). Each of the plurality of core gas path seals (82) extends from the rotor ring (84) at an interface (86I), the interface (861) defined along a spoke (86).</p>
申请公布号
EP2586970(A2)
申请公布日期
2013.05.01
申请号
EP20120190264
申请日期
2012.10.26
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
SUCIU, GABRIEL L.;MURON, STEPHEN P.;DYE, CHRISTOPHER M.;ALVANOS, IOANNIS;MERRY, BRIAN D.;SALVE, ARTHUR M.;NORRIS, JAMES W.
