|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/039.36 ; 60/733 ; 60/737 ; 60/746|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 52 인용 특허 : 0|
A high performance annular combustor for a gas turbine engine powering aircraft consisting of a primary combustion zone with the fuel nozzles and air swirlers in the dome and having typical combustion/dilution air holes in the liner and a secondary zone downstream of the primary zone having fuel nozzles and air swirlers operational solely when the primary zone is at a predetermined stoichiometric condition and issuing fuel which is at parity with the fuel/air ratio of the primary zone.
[ I claim:] [1.] An annular combustor having a first axially extending, annular shaped liner, a second axially extending, annular shaped liner concentrically mounted to and spaced from said first liner, said first liner and said second liner defining an annular chamber where combustion ensues, a dome interconnecting said first liner and said second liner at the forward end for enclosing said forward end, the aft end of said annular chamber being opened for flowing the products of combustion, spaced inner casing and outer casing surrounding said first lin...