|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/06 F02C-007/36 F01D-025/18 F02K-003/06 F02C-003/107|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 143|
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
1. A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis;a fan pressure ratio across a fan blade alone of less than 1.45;a bypass duct;a compressor section;a bypass ratio greater than ten (10), the bypass ratio being defined as the portion of air delivered into the bypass duct divided by the amount of air delivered into the compressor section;a combustor in fluid communication with the compressor section;a fan drive turbine in communication with the combustor, the fan drive turbine comprising a pressure ratio ...