公开(公告)号：US07614845B2

公开(公告)日：2009-11-10

申请号：US11359408

申请日：2006-02-23

申请人： Gerard Lucien Henri Adam ,  Xavier Agneray ,  Kevin Alexandre Dos Santos ,  Son Le Hong

发明人： Gerard Lucien Henri Adam ,  Xavier Agneray ,  Kevin Alexandre Dos Santos ,  Son Le Hong

IPC分类号： F01D25/26

CPC分类号： F01D25/246 ,  F01D25/145 ,  F05D2250/70 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/231 ,  F05D2300/614 ,  Y02T50/675

摘要： The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines.It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.

摘要翻译： 本发明涉及壳体与涡轮机的转子1的动叶片11之间的间隙12的改进，特别是为此目的而设置的壳体，以及装配有这种壳体的涡轮机。 本发明特别适用于飞机涡轮喷气发动机。 更具体地涉及一种涡轮机内壳21，其包括多个环形护罩23，其具有用于将两个相邻的罩23连接在一起的凸缘24。 根据本发明，该内壳21还包括：至少一个圆周热屏蔽5，其覆盖与两个相邻的罩23接触的凸缘24; 以及填充有第一绝热层8的空腔6，所述空腔位于隔热罩5的凹形内表面51a，52a和凸缘24之间。隔热罩5由多个扇形区50形成，这些扇形区50端对端 。