公开(公告)号：US20160032834A1

公开(公告)日：2016-02-04

申请号：US14775141

申请日：2014-03-12

Applicant: SNECMA

Inventor： Romain Plante ,  Jérémy Galiano ,  Florent Roggin ,  Gérome Sonois

IPC: F02C7/045

CPC classification number: F02C7/045 ,  F02K3/06 ,  F05D2230/60 ,  F05D2250/283 ,  F05D2260/96 ,  F16B11/006 ,  Y02T50/671

Abstract: The invention relates to a turbine engine, such as an aircraft turbofan or a turboprop engine, including a fan casing (10) having a substantially cylindrical wall (12) surrounding the blades of the fan, and at least two annular acoustic insulation panels (18, 20) mounted radially inside said wall (12), a first panel (18) being mounted upstream of the fan, a second panel (20) being located downstream of the first panel (18) and supporting an inner layer (42) of abradable material located opposite the radially outer ends of the blades of the fan, characterised in that the two annular panels (18, 20) form a single structural unit.

Abstract translation: 本发明涉及一种涡轮发动机，例如飞机涡轮风扇或涡轮螺旋桨发动机，其包括具有围绕风扇叶片的大致圆柱形壁（12）的风扇壳体（10）和至少两个环形隔音板（18 ，20），安装在所述壁（12）的径向内部，安装在所述风扇的上游的第一面板（18），位于所述第一面板（18）的下游的第二面板（20） 与风扇的叶片的径向外端相对的可磨损材料，其特征在于，所述两个环形板（18,20）形成单个结构单元。