|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F01D-017/08 F02C-007/045 F02C-007/042 F02C-007/052 F01D-017/10 F02C-007/05 F02K-003/02|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 26|
An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided fo...
1. A compressor inlet system for an aeroengine, the compressor inlet system comprising: a main inlet duct for directing a first air flow from a main intake opening to a compressor, the main intake opening defined at a forward end of the compressor inlet system with respect to a flight direction, a secondary inlet duct in fluid communication with the main inlet duct for directing a second air flow from a secondary opening to the compressor, and a control apparatus for selecting which of the first and second air flows to provide to the compressor, the cont...