发明名称 |
Method for reducing sound output at the back of a turbo engine and turbo engine improved by this method |
摘要 |
Disclosed is a method for producing a modified aircraft bypass turbojet engine having reduced sound output, in which the method is based on modifying an initial configuration of a rear portion of the turbojet engine to produce a modified rear portion of the turbojet engine. The modified rear portion includes a modified outer convex rear part shaped with a modified concave inner rear part that delimits an intermediate space beyond an initial cold stream outlet orifice. The intermediate space has a thickness at least equal to the thickness (E) of a sound deadening coating, which is placed in the intermediate space. |
申请公布号 |
US8607452(B2) |
申请公布日期 |
2013.12.17 |
申请号 |
US20080532397 |
申请日期 |
2008.03.17 |
申请人 |
CROSTA FRANCK;PRAT DAMIEN;AIRBUS OPERATIONS SAS |
发明人 |
CROSTA FRANCK;PRAT DAMIEN |
分类号 |
B21K25/00;F02K1/00;F02K1/82 |
主分类号 |
B21K25/00 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|