|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/039.06 ; 60/039.36 ; 60/756 ; 60/757|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 18 인용 특허 : 17|
A compact gas turbine engine having improved fuel efficiency, lower emissions, better starting capability, and longer operational life is provided at low cost through the use of a combustor incorporating tangential fuel injection in conjunction with certain strategically placed and sized oxidant inlet jets. The oxidant inlet jets include deflector jets which deflect a generally circumferentially spiralling flow of gases within the combustor in a manner causing fuel and oxidant to recirculate for a longer period of time within a primary combustion zone, t...
[ I claim:] [1.] A method for combusting fuel in a combustor defining an annular combustion chamber disposed about an axis, with said combustion chamber having a primary combustion zone at an upstream axial end thereof, an outlet at a downstream axial end thereof, and a secondary combustion zone between said primary combustion zone and said outlet, said method comprising the steps of:(a) injecting streams of fuel and oxidant into said primary combustion zone;(b) mixing said streams to form a combustible mixture of fuel and oxidant;(c) combusting said mix...