|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/32 F02C-007/275 F02C-007/36 F02K-003/06|
|미국특허분류(USC)||060/802; 060/796; 060/788; 074/DIG.5|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 20|
A turbofan gas turbine engine is provided having a unique power off-take shaft and gear system. Other gas turbine engine types are also contemplated herein. Two power off-takes are provided, one each for the low pressure spool and high pressure spool. The power off-takes extend across a core flow path of the turbofan engine between the low and high pressure shafts to a fan frame of the turbofan. A drive gear is provided near the front end of the high pressure shaft, and another drive gear is provided on the low pressure shaft near the drive gear for the ...
1. An apparatus comprising: a gas turbine engine having a first annular flow path disposed radially inward of a second annular flow path and at least two spool shafts;at least two rotatable shafts extending across the first annular flow path of the gas turbine engine and rotatingly coupled with at least one of the spool shafts;a first plurality of power devices in power communication with one of the at least two rotatable shafts and disposed between the first annular flow path and the second annular flow path;wherein the at least two spool shafts include...