|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||416/193A; 416/2190R; 416/2450R; 416/248|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 28 인용 특허 : 19|
A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to ...
1. A non-integral gas turbine engine fan blade platform for circumferential disposition between fan blades, said platform comprising:a platform wall with a radially outer surface which faces radially outwardly and a radially inner surface which faces radially inwardly, said platform wall is sloped with respect to a centerline with an increasing radius of the outer surface in the axially aft direction, forward, mid, and aft mounting lugs depend radially inwardly from said platform wall, and a wedge shaped platform bumper depends radially inwardly from the...