|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3936 ; 60/746 ; 60/755 ; 60/756|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 27 인용 특허 : 6|
The combustion dynamics and efficiency of a gas turbine having an annular combustor 26 provided with fuel injection nozzles 50 that inject fuel generally tangentially is improved by providing the walls 32, 34, 39 of the combustor 26 with cooling air film injectors 70, 86; 72, 88; 74, 90 at substantially equally angularly spaced locations about each such wall and which are oriented to generally tangentially inject a film-like air stream on the associated wall 32, 34, 39.
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; an annular combustor having radially inner and outer walls connected by a generally radially extending wall about said rotor and having an outlet connected to said nozzle and a primary combustion annulus defined by said walls remote from said ...