|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3936 ; 60/746 ; 60/748 ; 60/755|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 22 인용 특허 : 7|
The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between the fuel injectors 50 to achieve uniform turbine inlet temperature distribution while requiring fewer of the nozzles 50 and allowing those nozzles 50 that are utilized to have larger fluid flow paths that are less prone to clogging.
A gas turbine comprising: a rotor including compressor blades and turbine blades; an inlet adjacent one side of said compressor blades; a diffuser adjacent the other side of said compressor blades; a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotation of said rotor; and an annular combustor about said rotor and having an outlet connected to said nozzle and a primary combustion annulus remote from said outlet, a plurality of fuel injectors to said primary combustion annulus and being substantially equally ...