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21. 发明申请

US20090317244A1 GAS TURBINE ENGINE WITH IMPROVED THERMAL ISOLATION 失效
标题翻译：具有改进的热隔离的气体涡轮发动机
公开(公告)号：US20090317244A1
公开(公告)日：2009-12-24
申请号：US12138108
申请日：2008-06-12
申请人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
发明人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
IPC分类号： F02C7/12
CPC分类号： F01D11/001 , F01D5/08 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.
摘要翻译：燃气涡轮发动机包括壳体，其具有限定用于燃烧气体通过的大致环形且轴向伸长的热气体流路的管道壁。发动机还包括安装在内部发动机腔内的轮廓罩，并且限定热气体再循环袋，用于接收从热气流通道穿过环形空间摄取的热气体，并将所摄取的热气体通过环形空间循环回热气体流路。成型护罩包括从管道壁径向向内延伸的底壁，从底壁沿轴向方向朝向转子延伸的内壁，以及从内侧壁沿径向向外的方向延伸的端壁。端壁终止于靠近环形空间设置的周向延伸的自由边缘。端壁限定开口。

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