|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/242 ; 60/261 ; 60/271 ; 239/26515|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 6 인용 특허 : 0|
A turbojet afterburner engine has an expendable nozzle portion which can be jettisoned when the afterburner is placed in operation.
A turbojet engine for aircraft missiles including an afterburner, an exhaust nozzle duct disposed downstream of said afterburner for discharge of the engine exhaust therethrough and having a non-variable throat portion of convergent-divergent profile, an element secured to and within said nozzle duct at its said throat portion and coacting with said throat portion to provide a non-variable reduced cross-sectional flow area nozzle for non-afterburning operation of the engine, and means operative during flight to jettison said element when the engine after...