Patent ID: 6786040
Filing Date: 2004-09-07
Classification: F02K,F05D

Abstract:
An ejector ramjet engine suitable for use with a flying vehicle in a range of speeds from zero to hypersonic flight comprising:an inlet with a variable inlet system attached to a mixer located downstream therefrom; the mixer having an injector assembly mounted in the fluid flow zone of the mixer near the intersection with the inlet to form an ejector and a fluid supply system connected to the injector assembly wherein the injector assembly having a plurality of injector exhaust nozzles defined therein with the injector exhaust nozzles oriented to direct fluid release in the downstream flow direction partially offset from the engine longitudinal axis wherein the injector exhaust, nozzles are alternatively offset radially at an angle away from and toward the engine longitudinal axis and the injector assembly supported in the mixer by a support element attached to an engine internal wall; a diffuser having an expanding cross sectional area relative to the mixer attached downstream of the mixer; a combustor having a larger cross sectional area relative to the mixer attached downstream of the diffuser and the fluid supply system connected to the combustor; an exit nozzle having an expanding cross sectional area relative to the combustor attached downstream of the combustor with a choke constriction point intermediate the combustor and the exit nozzle.