| 发明名称 |
TURBOPROP AIR INTAKE |
| 摘要 |
A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle. |
| 申请公布号 |
US2016237898(A1) |
申请公布日期 |
2016.08.18 |
| 申请号 |
US201415029588 |
申请日期 |
2014.10.14 |
| 申请人 |
SNECMA ;SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUE |
发明人 |
Poisson Mathieu Ange;Orcel Stéphane;Glemarec Guillaume;Pacary Jean-Luc |
| 分类号 |
F02C7/045;F01D25/24;F02K3/06 |
主分类号 |
F02C7/045 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A turboprop engine comprising a rotary propeller upstream of an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, said bypass comprising an outlet that is oriented substantially axially downstreamward of the engine, the turboprop engine further comprising a nacelle surrounding the engine and the air intake, wherein the air intake is fixed to an engine housing and is not rigidly connected to the nacelle so as to allow relative movements between the air intake and the nacelle during operation, said outlet being connected by means of a flexible link to an intake of an air system borne by the nacelle. |
| 地址 |
Paris FR |
