本发明涉及一种飞机燃气涡轮发动机的一个推力反向器装置，其包括核心发动机10中的罩和一个围绕该二次流路31，以及与周围的前盖29和后面板30的轴向方向的滑动，以及设置成围绕级联元件的圆周上的旁路管31 32，其延伸到前罩29的间隙导致通过大致轴向位移后面板30的位移的情况下引入，其中所述级联元件32直接连接到后面板30上，使得后盖30具有圆形的外 具有前缘33和所述级联元件32具有在其后端部分上的流动引导件34，被布置在其中Schubumkehrleitschaufeln 35的多个前面和后面其中Strömungsleitschaufel设置至少36，D 后盖30的外前边缘33的倒圆的曲率较旧形状等。

The invention relates to a cowl of an aircraft gas turbine engine with a thrust reverser, with a core engine 10 and a surrounding this bypass duct 31, and a the bypass duct 31 surrounds the front cover 29 and a movable axially rear cowl 30, and with circumferentially arranged cascade elements 32 which are in a resulting in a shift of the rear panel 30 to the front cowl 29 gap by a substantially axial displacement introduced, wherein the cascade elements 32 are directly connected to the rear panel 30, the rear cover 30 has a rounded outer leading edge 33 and in that the cascade element 32 at its rear portion a flow guide 34 having, in which a plurality of Schubumkehrleitschaufeln 35 are arranged and behind which at least one Strömungsleitschaufel 36 is arranged, whose curved shape similar to the rounding of the outer front edge 33 of the rear cowl 30th