公开(公告)号：US06164563A

公开(公告)日：2000-12-26

申请号：US356321

申请日：1999-07-16

申请人： Philippe Pierre Vincent Bouiller ,  Pierre-Yves Bourquin ,  Fabrice Michel Olivier Cot ,  Daniel Kettler ,  Jean-Pierre Ruis

发明人： Philippe Pierre Vincent Bouiller ,  Pierre-Yves Bourquin ,  Fabrice Michel Olivier Cot ,  Daniel Kettler ,  Jean-Pierre Ruis

IPC分类号： F02K1/11 ,  F02K1/82 ,  B05B12/00

CPC分类号： F02K1/11 ,  F02K1/825 ,  F05D2250/323 ,  F05D2250/34

摘要： A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).

摘要翻译： 一种用于飞行器的喷射推进系统的气体流动排气组件，其中会聚的排气喷嘴（4）装配有平移的冷襟翼（21,22）。 主排气喷嘴（4）包括位于由飞行器整流罩（2）包围的主管道（1）之外的两个热襟翼（5,6）。 整流罩（2）由辅助排气喷嘴（20）延伸，二次排气喷嘴（20）由主管道（1）支撑，并可由控制机构（27a，27b）平移。 二次排气喷嘴（20）包括与另一个控制机构（29a，29b）驱动的冷襟翼（21,22），独立于热襟翼（5,6）的角位置。 优选地，在水平横向轴（23a，23b）上铰接并支撑有两个眼睑形冷舌片（21,22）。 轴（23a，23b）优选地固定在两个横向滑动件（24a，24b）上，滑动件（24a，24b）在主导管（1）上滑动，并可通过使辅助排气喷嘴（20）平移的控制机构（27a，27b）移动。

公开(公告)号：US06179225B2

公开(公告)日：2001-01-30

申请号：US09356362

申请日：1999-07-19

申请人： Philippe Pierre Bouiller ,  Pierre-Yves Bourquin ,  Daniel Kettler ,  Jean-Pierre Ruis

发明人： Philippe Pierre Bouiller ,  Pierre-Yves Bourquin ,  Daniel Kettler ,  Jean-Pierre Ruis

IPC分类号： B63H2546

CPC分类号： F02K1/825 ,  F02K1/11

摘要： An axially symmetric turbojet engine exhaust-nozzle includes a system for masking the exhaust jet, such system including inner hot flaps (7), hinging on a conical shell (4) and driven by a first control ring (10) powered by linear actuators (11), and outer cold flaps (20) hinging on an annular assembly (12) and driven by a second control ring (22) powered by linear actuators (23) to vary the angle of the cold flaps. The annular assembly (12) is axially displaceable by a third set of linear actuators (30). Each cold flap (20) comprises an inner skin (40) fitted with orifices (43) and hinging on the annular assembly(12) and an outer skin (41) spaced radially away of the inner skin (40) to define an air flow channel between the skins. When the annular assembly (12) is moved downstream by the third set of linear actuators (30), the outer skins (41) form a scoop introducing fresh air into the cold flaps (20), and said air is injected into the hot gas flow through the orifices (43) in the inner skin and other orifices (44) at the trailing edge (42) of the cold flaps to reduce the exhaust signature.

摘要翻译： 轴向对称的涡轮喷气发动机排气喷嘴包括用于遮蔽排气射流的系统，该系统包括铰接在锥形壳体（4）上并由第一控制环（10）驱动的内部热襟翼（7），该第一控制环由线性致动器 以及铰链在环形组件（12）上并由由线性致动器（23）供电的第二控制环（22）驱动的外部冷襟翼（20），以改变冷襟翼的角度。 环形组件（12）可被第三组线性致动器（30）轴向移动。 每个冷翼（20）包括装配有孔（43）并铰接在环形组件（12）上的内表皮（40）和径向远离内表皮（40）的外表皮（41），以限定空气流 皮肤之间的通道。 当环形组件（12）由第三组线性致动器（30）向下游移动时，外表面（41）形成将新鲜空气引入冷襟翼（20）中的勺子，并将所述空气注入到热气体 流过冷皮瓣后缘（42）的内皮和其他孔（44）中的孔（43），以减少排气特征。