|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-011/18 B64D-027/10 F01D-001/26 F01D-005/14 F04D-029/32 B64C-011/48 F02K-003/072 F02C-003/067 B64D-027/00|
|우선권정보||FR-13 54557 (2013-05-21)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 5|
An aircraft turbopropeller includes two coaxial contra-rotating unducted propellers, upstream and downstream respectively, each propeller including an annular row of blades. The blades of the downstream propeller have a reverse sweep in relation to that of the blades of the upstream propeller. The leading edges of the blades of the downstream propeller extend radially outwards from downstream to upstream, at least over a radially outer portion of the blades.
1. An aircraft turboprop engine, comprising: two coaxial unducted and contra-rotating propellers which are upstream and downstream respectively, each propeller comprising an annular array of blades, the blades of the downstream propeller having a sweepback which is inverted with respect to that of the blades of the upstream propeller,wherein the blades of the downstream propeller have their leading edges extending, at least on a radially outer portion of the blades, radially towards an outside, going from downstream to upstream, andwherein an axial dista...