The present disclosure relates to sealing systems (200) for gas turbine engines. In one embodiment, a seal support structure (100) for a gas turbine engine includes a seal support (110) configured to retain a circumferential seal (130) and an engine support (105) configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel (115) configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system (200) including a circumferential seal (130) and seal support structure configured to provide radial movement.
申请公布号
EP3034801(A1)
申请公布日期
2016.06.22
申请号
EP20150191124
申请日期
2015.10.22
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
WILSON, ROSS;MCCAFFREY, MICHAEL G.;FARRIS, JOHN R.;HALL, THEODORE W.;KORZENDORFER, JOHN R.;VINSON, ELIZABETH F.;JACQUES, JEFFREY M.;PAUL, JOHN E.;STONER, ALAN W.;OTERO, EDWIN