|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/26 F02C-007/06 F02C-007/275|
|미국특허분류(USC)||060/786; 060/039.08; 060/788|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 7|
A turboprop propulsion unit for an aircraft comprises a propeller 22 which is driven by a core engine by means of a propeller turbine 26 which drives the propeller 22 through a shaft 28 and a propeller gearbox 24. Restarting of the engine in flight is achieved by windmilling of the propeller 22, which drives a propeller gearbox lubricant pump 30. A diverter valve 40 causes lubricant delivered by the propeller gearbox lubricant pump 30 to be supplied to a turbomachinery lubricant pump 18 along a restart conduit 44, so as to drive the turbomachinery lubric...
1. A propulsion unit for an aircraft, the propulsion unit comprising: a gas turbine engine including: first and second spools, an accessory gearbox driven by the second spool, a propeller gearbox provided with a propeller gearbox lubricant pump, and an integral turbomachinery lubricant pump driven from the accessory gearbox;a propeller configured to be driven by the first spool through the propeller gearbox; anda restart conduit configured to supply fluid delivered from the propeller gearbox lubricant pump to the turbomachinery lubricant pump, whereinwin...