|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-001/09 F02K-001/04 F02K-003/04|
|미국특허분류(USC)||60/204 ; 60/271 ; 60/226.2 ; 60/226.1 ; 239/265.29 ; 239/265.33 ; 244/110B|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 115 인용 특허 : 0|
A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing edge portion of the fan cowl and the core engine housing. A trailing edge cowl portion is slidably positioned in a rearwardly opening annular cavity in the aft end of the fan cowl for reciprocal axial translation between a deployed position to provide an enlarged exit throat area to provide enhanced performance of the aircraft engine during take off and climb to...
[ What is claimed is:] [1.] A structure to provide a variable nozzle for the fan air flow of an aircraft gas turbine engine, the nozzle being defined by the spacing between a trailing edge portion of the translating cowl and the core engine housing to provide a determinable exit throat area for such fan air flow, said structure comprising:a generally annularly shaped translating cowl that is spaced from and which surrounds a portion of an aft portion of the housing of the core jet engine, said cowl being translatable for thrust reverser purposes and havi...