|국가/구분||United States(US) Patent 등록|
|우선권정보||FR-08 02297 (2008-04-24)|
|§371/§102 date||20101025 (20101025)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 2 인용 특허 : 8|
A compressor rotor for a turbomachine including at least two disks on a common axis carrying blades and connected together by a tubular wall, forming a surface of revolution, and a centripetal air bleed mechanism including air passages passing through the tubular wall, together with a wall extending along the tubular wall from the through passages up to one of the disks to channel the air stream inside the tubular wall.
1. A compressor rotor of a turbomachine, the rotor comprising: at least first and second successive disks on a common axis carrying blades which are successive along the axis, the at least first and second successive disks being connected together by a generally tubular wall forming a surface of revolution about said axis; andcentripetal air bleed means comprising air passages passing through the generally tubular wall near the second disk, the centripetal air bleed means opening out, near the first disk, into a chamber formed radially inside the general...