|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-003/075 F01D-019/00 F01D-009/06 F04D-029/52 F01D-009/04 F04D-027/00 F01D-017/00 F01D-001/02|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 34|
A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.
1. A gas turbine engine comprising: a high spool along an engine axis, said high spool operable to communicate a core airflow through a core flow path;a fan section operable to communicate a fan airflow into a secondary flow path and said core flow path;a low spool along said engine axis to drive said fan section;a starter/generator connected to said low spool, said starter/generator having a start mode in which the starter/generator rotationally drives said low spool and a generate mode in which said low spool drives said starter/generator to produce el...