公开(公告)号：US08850824B2

公开(公告)日：2014-10-07

申请号：US13541260

申请日：2012-07-03

申请人： Predrag Todorovic ,  Miles Trumper

发明人： Predrag Todorovic ,  Miles Trumper

IPC分类号： F02K1/08 ,  F02K3/02 ,  F02K1/82

CPC分类号： F02K1/085 ,  F02K1/08 ,  F02K1/827

摘要： The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.

摘要翻译： 技术领域本发明涉及一种具有核心发动机的飞机燃气轮机，其由旁路径径向向外封闭的旁通管道围绕，旁路管道的径向内壁与径向外部旁路壁形成旁路喷嘴，并且与 所述径向内壁包括沿所述内壁的圆周延伸并且可径向向外变形的调节元件。

公开(公告)号：US20130008147A1

公开(公告)日：2013-01-10

申请号：US13541260

申请日：2012-07-03

申请人： Predrag TODOROVIC ,  Miles TRUMPER

发明人： Predrag TODOROVIC ,  Miles TRUMPER

IPC分类号： F02K3/02 ,  F02K1/08

CPC分类号： F02K1/085 ,  F02K1/08 ,  F02K1/827

摘要： The present invention relates to an aircraft gas turbine with a core engine 10 which is surrounded by a bypass duct 29 enclosed radially outwards by a bypass wall 30, with a radially inner wall 31 of the bypass duct 29 forming with the radially outer bypass wall 30 a bypass nozzle 32, and with the radially inner wall 31 including an adjusting element 33 extending along the circumference of the inner wall 31 and being deformable radially outwards.

摘要翻译： 技术领域本发明涉及一种具有核心发动机10的飞机燃气轮机，其由旁路管道29围绕的旁路管道29围绕，旁路管道29的径向内壁31与径向外部旁路壁30形成 旁路喷嘴32，并且径向内壁31包括沿着内壁31的圆周延伸并且可径向向外变形的调节元件33。