发明名称 |
Dual flow turboshaft engine and improved hot flow nozzle |
摘要 |
An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first connecting surface to a turbine casing. The hot flow nozzle is formed as a single skin that extends in a rearward direction from an engine cowl, with the hot flow nozzle being connected to the engine cowl along a second connecting surface. The hot flow nozzle and the bulbous boss are positioned relative to one another to delimit a nominal nozzle throat section and a nominal outlet section for hot flow from a hot flow generator. The hot flow nozzle single skin is also approximately bulbous in shape and widens from the second connecting surface in a direction toward the engine cowl's external wall. |
申请公布号 |
US8601788(B2) |
申请公布日期 |
2013.12.10 |
申请号 |
US20080602081 |
申请日期 |
2008.05.22 |
申请人 |
CROSTA FRANCK;PRAT DAMIEN;AIRBUS OPERATIONS SAS |
发明人 |
CROSTA FRANCK;PRAT DAMIEN |
分类号 |
F02K3/02;F02K1/00 |
主分类号 |
F02K3/02 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|