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CN106930863A 用于联机的分布式推进的方法及系统 无效 - 驳回

用于联机的分布式推进的方法及系统
摘要：
提供了一种燃气涡轮发动机组件(200)和飞行器(900)。燃气涡轮发动机组件(200)包括燃气涡轮发动机(202)，其包括构造成绕着旋转轴线(204)旋转的动力轴(126)。燃气涡轮发动机组件(200)还包括与燃气涡轮发动机同轴地联接于动力轴(126)的第一风扇(206)和第二风扇(208)。燃气涡轮发动机组件(200)还包括构造成将第一空气流引导至第一风扇(206)的第一风扇函道(210)。燃气涡轮发动机组件(200)还包括构造成将第二空气流引导至第二风扇(208)的第二风扇函道(216)。燃气涡轮发动机组件(200)还包括排气函道(226)，其构造成沿旋转轴线(204)的方向引导燃气涡轮发动机(202)的排出气流。
摘要（英）：

The invention provides a gas turbine engine assembly (200) and an aircraft (900). The gas turbine engine assembly (200) includes a gas turbine engine (202), and also includes a power shaft (126) configured to rotate about an axis (204) of rotation. The gas turbine engine assembly (200) also includes a first fan (206) and a second fan (208) coupled to the power shaft (126) coaxially with the gas turbine engine. The gas turbine engine assembly (200) also includes a first fan duct (210) configured to direct a first stream of air to the first fan (206). The gas turbine engine assembly (200) also includes a second fan duct (216) configured to direct a second stream of air to the second fan (208). The gas turbine engine assembly (200) also includes an exhaust duct (226) configured to direct a stream of exhaust gases of the gas turbine engine (202) in a direction of the axis (204) of rotation.

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