|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/754; 060/732; 431/010|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 2 인용 특허 : 33|
A double annular radially staged combustor for a gas turbine engine having a reduced internal flow transitioning area between an outboard primary combustion zone and al inboard secondary combustion zone. The primary combustion zone is an annular shell form with a radially inboard annular exit. An outboard ring with thru holes and an inboard annular channel yields a quick quench zone. The secondary combustion zone, adjacent to and downstream of the quick quench zone is of an annular shell form, generally radially inboard of the primary combustion zone. In...
1. A combustor, comprising: a primary combustion chamber having an exit area;a secondary combustion chamber having an inlet area, wherein the primary combustion chamber is located radially outboard of the secondary combustion chamber, said primary combustion chamber coupled at an aft end to an end of the secondary combustion chamber;a reduced combustor flow area disposed between the exit area of said primary combustion chamber and the inlet area of said secondary combustion chamber, said reduced combustor flow area in communication with said primary comb...