Patent ID: 6973774
Filing Date: 2005-12-13
Classification: F02C,F05D

Abstract:
1. A hybridized rocket and jet engine apparatus operating in the atmosphere and in the outer space comprising: a housing; a fuel tank and at least two fuel pumps providing a fuelling rate; a liquid oxygen tank and a cryogenic pump; said housing comprising: a gas turbine engine serially comprising: an intake, a compressor, a combustor, a turbine, an afterburner, and an outlet; said afterburner comprising a heat exchanger wherein liquid oxygen is vaporized by indirect heat exchange with hot gases flowing in said afterburner; said vaporized oxygen injected between said intake and said compressor; said outlet comprising at least one graphite steering vane; said intake comprising a gate regulating the air/oxygen ratio during atmospheric operation; wherein during operation in space and during atmospheric re-entry said gate closes said intake; and wherein a control system links said intake aperture as defined by a position of said gate, said cryogenic pump rate, and said engine fuelling rate.