|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-003/06 F02C-007/36 F02K-003/072|
|미국특허분류(USC)||060/226.1; 060/039.163; 060/268; 415/123; 415/055.2; 403/001|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 41|
An adaptive cycle gas turbine engine is disclosed having a number of features. A fan arrangement is provided having counter-rotating fan stages, one fan stage is operable to be clutched and decoupled from the other stage. A high pressure compressor bypass is also provided. A clutch is provided to at least partially drive an intermediate pressure compressor with a high pressure turbine when the high pressure compressor is bypassed. A partial bypass of the high pressure turbine may be provided.
1. An apparatus comprising: a gas turbine engine having three spools including a first pressure spool, a second pressure spool, and a third pressure spool;a fan having a first fan stage and a second fan stage, the fan rotatingly coupled with a first pressure shaft of the first pressure spool;a compressor bypass operable to bypass a compressed air past a third pressure compressor of the third pressure spool, the compressor bypass in fluid communication with a core combustor of the gas turbine engine such that working fluid that flows through the compresso...