|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-001/00 F02C-009/20 B64D-033/04 F02K-001/30 F02K-001/72 F01D-005/02 F01D-015/12 F01D-017/14 F01D-025/24 F02C-003/04 F02C-009/18|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 2 인용 특허 : 39|
A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.
1. A gas turbine engine comprising: a core nacelle defined about an engine centerline axis;a core engine at least partially disposed within the core nacelle;a fan section with twenty (20) or less fan blades;a gear system driven by the core engine to drive said fan section;a fan nacelle mounted at least partially around said fan section and said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan section having a fan pressure ratio less than 1.45;a variable fan nozzle axially movable relative to the fan nacelle, the variable f...