|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/224 ; 60/3926 ; B|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 6 인용 특허 : 2|
An optimized propulsion system for aircraft whose flight range extends over a wide range of speeds. It comprises an outer turbojet engine and an inner turbojet engine housed within a single engine nacelle and arranged concentrically, the outer turbojet engine extending axially and around a narrow portion of the casing of the inner turbojet engine. The invention may be used in the field of variable-cycle engines, and particularly in the field of supersonic transport aircraft.
Propulsion system for supersonic aircraft, characterized by the fact that it comprises, arranged within a single engine nacelle and mounted concentrically so as to be able to operated independently, an outer turbojet engine and an inner turbojet engine, the outer turbojet engine extending around a narrow axial portion of the inner turbojet engine which narrow portion defines an air conduit from a high-pressure compressor to a combustion chamber.