|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-003/08 F02C-007/18 F02C-007/22 F02C-007/30|
|미국특허분류(USC)||60/3936 ; 60/3965 ; 60/3974 ; S|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 26 인용 특허 : 1|
A gas turbine has a combustion chamber of toroidal configuration that includes separation structure dividing the combustion chamber into an annular primary zone and an annular dilution zone. Injection of compressor discharge air into the primary zone sets up a toroidal recirculation pattern of generally circular cross-sectional configuration. Fuel slinger structure at the inner periphery of the primary zone has a generally cylindrical surface for receiving and distributing fuel in a thin sheet for discharge in a radially outward direction as minute dropl...
A gas turbine comprising: a rotatable unit mounted for rotation about a system axis, said rotatable unit including a compression component and an expansion component, a combustion chamber disposed between said compression and expansion components, said gas turbine having a gas flow path serially through said compression component, said combustion chamber, and said expansion component, said combustion chamber being of toroidal configuration and having two distinct annular zones, a primary zone and a dilution zone, structure in said combustion chamber havi...