|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 18 인용 특허 : 9|
A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a s...
What is claimed is: 1. A gas turbine engine, comprising:(a) a first turbomachinery core;(b) a second turbomachinery core adjacent to the first core;(c) a low pressure turbine disposed downstream of the first and second cores and in flow communication with at least one of the first and second cores;(d) a rotating fan disposed upstream of the first and second cores and in mechanical communication with the low pressure turbine;(e) at least one inlet control flap disposed downstream of the fan and upstream of the first and second cores, the at least one inle...