|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F23R-003/04 F23R-003/42 F23R-003/54|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 0 인용 특허 : 8|
A combustor assembly (17) including guide vanes (44) located between an inner cylinder (24) and a flow sleeve (25). Each guide vane (44) includes a circumferentially angled flow directing portion (60) adjacent to a leading edge (46). The leading edge (46) of at least one guide vane (44) can be located radially inward along the longitudinal axis (54) relative to the leading edge (46) of at least one other of the guide vanes (44). The length of the guide vanes (44) may vary, and the circumferential spacing between a first pair of the guide vanes (44) can b...
1. A can annular gas turbine engine having a gas delivery structure for delivering gases from a plurality of combustors each having a longitudinal axis tangentially arranged with respect to a circumference defined by an annular chamber that extends circumferentially about a gas turbine engine axis for delivering the gas flow to a first row of blades, a gas flow path formed by a duct arrangement between a respective combustor of the plurality of combustors and the annular chamber for conveying gases in a downstream direction from the respective combustor ...