公开(公告)号：US06082669A

公开(公告)日：2000-07-04

申请号：US71157

申请日：1998-05-04

申请人： Thierry Pascal Bardagi ,  Gerard Ernest Andre Jourdain

发明人： Thierry Pascal Bardagi ,  Gerard Ernest Andre Jourdain

IPC分类号： F02C7/042 ,  F02K3/06 ,  B64B1/24

CPC分类号： F02C7/042

摘要： The system (13) for admitting external air (12) into a working section (11) of a gas turbine engine through a jacket (10) of the working section is characterised by the combination of doors (15) sliding towards the front (ramps) and rotating doors (14). The ramps (15) are fitted with grooved lateral arms (30) in which run wheels mounted on the doors (14). When they reach an ascending part (33) of the grooves (31) after sufficient movement of the ramps (15) towards the front, they are caused to rise, which opens the doors (14). This system can be used on double flow gas turbine engines for supersonic aircraft.

摘要翻译： 用于通过工作部分的护套（10）将外部空气（12）进入燃气涡轮发动机的工作部分（11）的系统（13）的特征在于门（15）朝向前部（斜坡） ）和旋转门（14）。 坡道（15）装有开槽的侧臂（30），其中安装在门（14）上的跑轮。 当坡道（15）向前方充分移动之后，当它们到达凹槽（31）的上升部分（33）时，它们被升高，这就打开门（14）。 该系统可用于超音速飞机的双流燃气涡轮发动机。

公开(公告)号：US5934564A

公开(公告)日：1999-08-10

申请号：US874507

申请日：1997-06-13

申请人： Philippe Pierre Vincent Bouiller ,  Pierre Yves Bourquin ,  Gerard Ernest Andre Jourdain ,  Jean-Pierre Ruis

发明人： Philippe Pierre Vincent Bouiller ,  Pierre Yves Bourquin ,  Gerard Ernest Andre Jourdain ,  Jean-Pierre Ruis

IPC分类号： F02K1/12 ,  B05B12/00

CPC分类号： F02K1/1292

摘要： A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to the rear portion of the turbojet engine, and an inner flap ring having a plurality of inner forward driven flaps and a plurality of inner forward interlock flaps, each having a forward portion pivotally attached to the rear portion of the turbojet engine, the inner flap ring also having a plurality of inner rear driven flaps and a plurality of inner rear interlock flaps, each inner rear flap having a front edge portion pivotally connected to a rear edge portion of a corresponding inner forward flap. The inner and outer flap rings are radially spaced apart and are arranged symmetrically about an axis of symmetry, with a drive collar located in the space between the inner and outer flaps that is movable between forwardmost and rearmost positions in a direction substantially parallel to the axis of symmetry of the nozzle. A plurality of translating levers are each pivotally attached to the drive collar and to one of the inner forward driven flaps. A plurality of interlock levers are each pivotally connected to one of the translating levers and to one of the inner rear driven flaps. Each interlock lever is connected to one of the outer driven flaps by a link rod pivotally connected to the interlock lever and to the outer driven flaps. Actuators are connected to the rear portion of the turbojet engine and to the translating levers to move the drive collar between its forwardmost and rearmost positions, such movement causing the inner flap ring to move between a converging-diverging configuration and a converging--converging configuration. Thus, the nozzle is suitable for both subsonic and supersonic aircraft operation.

摘要翻译： 公开了一种用于具有后部的涡轮喷气发动机的可变几何形状排气喷嘴，该喷嘴具有带有多个从动外侧翼片的外侧翼环和多个外部互锁翼片，每个外部翼片可枢转地连接到 涡轮喷气发动机和具有多个内部向前驱动翼片和多个内部向前互锁翼片的内翼片环，每个翼片环具有可枢转地附接到涡轮喷气发动机的后部的前部，内翼片环还具有多个 内部后驱动翼片和多个内部后互锁翼片，每个内后翼片具有可枢转地连接到相应内部前翼片的后边缘部分的前边缘部分。 内侧翼片环和外侧翼片环径向间隔开并且围绕对称轴线对称地布置，其中驱动套环位于内侧翼片和外部翼片之间的空间中，其可以在基本上平行于轴线的方向上在最前方和最后方向的位置之间移动 喷嘴的对称性。 多个平移杆各自枢转地附接到驱动轴环和内部向前驱动的挡板中的一个。 多个互锁杠杆各自枢转地连接到平移杆中的一个和内部后驱动翼片中的一个。 每个互锁杆通过连杆与连接杆连接到一个外驱动挡板上，该连杆与联动杆和外驱动挡板枢转连接。 致动器连接到涡轮喷气发动机的后部和平移杆，以使驱动套环在其最前面和最后面的位置之间移动，这样的运动使得内翼片环在会聚发散构型和会聚会聚构型之间移动。 因此，喷嘴适用于亚音速和超音速飞行器操作。