发明名称 |
DUAL FLOW TURBOSHAFT ENGINE WITH ADVANCED 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 |
EP2171218(A2) |
申请公布日期 |
2010.04.07 |
申请号 |
EP20080805597 |
申请日期 |
2008.05.22 |
申请人 |
AIRBUS OPERATIONS (SAS) |
发明人 |
CROSTA, FRANCK;PRAT, DAMIEN |
分类号 |
F01D17/10;F01D25/26;F02C9/52;F02K1/38;F02K1/46;F02K3/06;F02K3/075 |
主分类号 |
F01D17/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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