公开(公告)号：US20160237949A1

公开(公告)日：2016-08-18

申请号：US15023952

申请日：2014-09-16

申请人： SNECMA

发明人： Romain FERRIER ,  Alexandre COUILLEAUX ,  Jackie Raymond Julien PROUTEAU ,  Nicolas SIRVIN

IPC分类号： F02K1/46 ,  F02K1/40

CPC分类号： F02K1/46 ,  F02K1/386 ,  F02K1/40 ,  F05D2220/30 ,  F05D2240/127 ,  F05D2250/36

摘要： A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

摘要翻译： 具有汇合流的涡轮发动机喷嘴，所述喷嘴包括围绕环形中心体布置并与之配合的芯罩，以限定用于使芯流的流动通过的芯环形通道，所述芯流进入具有 方位角分量驱动核心流在对应于发动机的两个操作速度的两个相对的旋转流动方向上的残余回转运动，所述芯整流罩具有环形上游部分，该环形上游部分由环形端部部分延伸，所述环形端部部分具有形成多个折翼的纵向切口 通过它们各自的侧边缘成对地径向重叠，使得对于每个翼片，翼片的两个侧边缘中的一个相对于相邻翼片的相应侧边缘位于内部，而另一侧边缘 的翼片相对于另一相邻翼片的相应侧边缘位于外部。