|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-005/00 F02C-003/32 B64D-027/10 B64D-027/12 B64D-027/14 F01D-015/10 F02K-003/06 F02C-007/32 B64D-031/04 B64D-027/02|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 4 인용 특허 : 2|
A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.
1. A hybrid gas turbine propulsion system comprising: a turbojet thrust module being a modified Brayton-cycle jet thrust engine comprised of an enclosing duct having an inlet and a center body for one or more turbocompressors of axial or centrifugal type in one or more stages driven by variable frequency drive (VFD) controlled, variable speed electric motors, followed by a combustor stage where fuel is mixed with air compressed by the one or more turbocompressors then ignited and combusted via a fuel manifold sufficient to achieve stoichiometric mixtures...