公开(公告)号：WO2014109811A2

公开(公告)日：2014-07-17

申请号：PCT/US2013066531

申请日：2013-10-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M ,  STAUBACH JOSEPH B ,  SUYDAM ADAM JOSEPH

CPC classification number: B64D27/14 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

Abstract translation: 燃气涡轮发动机具有并入涡轮的核心发动机和位于涡轮下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，每个机舱接收风扇转子。 风扇转子被固定以随着安装在风扇转子的径向外部位置处的尖端涡轮机旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。