| 发明名称 |
UNDUCTED PROPELLER TURBOSHAFT ENGINE PROVIDED WITH A REINFORCING SHELL INTEGRATING PIPE SEGMENTS |
| 摘要 |
An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall. |
| 申请公布号 |
US2017002688(A1) |
申请公布日期 |
2017.01.05 |
| 申请号 |
US201515113683 |
申请日期 |
2015.01.14 |
| 申请人 |
SAFRAN AIRCRAFT ENGINES |
发明人 |
BEUTIN Bruno Albert;LLAMAS CASTRO Nuria;NATAL Maria;RAMOS Bruna |
| 分类号 |
F01D25/26;B64D27/16;F01D25/12;F02K3/072;F02C7/20 |
主分类号 |
F01D25/26 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying at least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator;
a reinforcing shell presenting a first attachment zone mounted on the first casing, a second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing; wherein the reinforcing shell further comprises at least one pipe segment integrated in said wall, said pipe segment locally lying between the inner and outer surfaces of said wall. |
| 地址 |
Paris FR |
