公开(公告)号：EP3387244A1

公开(公告)日：2018-10-17

申请号：EP16805124.1

申请日：2016-12-01

申请人： Rolls-Royce Deutschland Ltd & Co KG

发明人： KÖPF, Frank Uwe

IPC分类号： F02K1/08

CPC分类号： F02K1/08 ,  B64D27/16 ,  B64D31/06 ,  F05D2220/323

摘要： The invention relates to an aircraft gas turbine, comprising a core engine (10) and a bypass flow channel (25), which bypasses the core engine and which forms an outlet nozzle (31) together with a casing (29) of the core engine (10) and together with a radially outer housing wall (30), characterized in that a ring element (32), which can be displaced in the axial direction, is arranged in the region of the outlet nozzle (31), wherein a ring channel (33) that can be varied by the displacement of the ring element (32) is formed between the casing (29) of the core engine (10) and the ring element (32).