|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-009/18 F02C-003/10 F02C-007/047 F02C-007/27 F02C-007/32 B64D-013/06|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 38|
Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to...
1. A bleed air system for an aircraft comprising: a turbo-compressor comprising a compressor, a turbine, and a first drive shaft coupled between the compressor and the turbine, the first drive shaft to enable the turbine to selectively drive the compressor, the compressor having a compressor inlet and a compressor outlet, the compressor outlet to be fluidly coupled to a system of the aircraft that receives pressurized air, the compressor inlet to receive bleed air from a low-pressure compressor of an engine of the aircraft;a gearbox operatively coupled t...