公开(公告)号：US20140321981A1

公开(公告)日：2014-10-30

申请号：US13871080

申请日：2013-04-26

申请人： Jose L. Rodriguez ,  David A. Little ,  Jiping Zhang ,  Patrick M. Pilapil

发明人： Jose L. Rodriguez ,  David A. Little ,  Jiping Zhang ,  Patrick M. Pilapil

IPC分类号： F01D11/24

CPC分类号： F01D11/24 ,  F01D19/02 ,  F01D25/26 ,  F02C7/18

摘要： A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart.

摘要翻译： 公开了一种涡轮发动机关闭温度控制系统，其被配置成在压缩机和涡轮叶片组件周围的空腔内促进恒定的空气温度，以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。 涡轮发动机关闭温度控制系统可以包括定位在涡轮机壳体中的一个或多个空气放大器。 空气放大器的排气出口可以延伸到由涡轮壳体产生的空腔中，并且可以被配置为沿大致圆周方向排出空气以夹带空腔内的空气以周向流动，以在空腔内建立一致的空气温度，从而防止不均匀 关闭后对涡轮发动机部件进行冷却，并防止在热启动期间对涡轮机部件造成损坏。