Series jet rocket engine has two pref parallel shafts - each with one turbine to give reduced shaft and engine length

摘要

A series jet engine for rocket propulsion has a pre-combustion chamber, two mechanically independent (H.P. and L.P.) turbines driving fuel pumps, a principal combustion chamber, and the jet nozzle, all arranged thermodynamically in series. Physically, the layout has two (parallel) principal axes (A,B) which comprise the following series of items, considered in succession from an imaginary plane (E) immediately downstream of the jet outlet, axis (A), pre-combustion chamber, H.P. turbine, (fuel) pump, axis (B), principal combustion chamber with jet nozzle, L.P. turbine (fuel) pump. Pref. the H.P. and L.P. turbines lie approximately opposite to each other. The features of a series jet engine, esp. continuing increase in specific thrust with increasing pressure, are obtained, without the disadvantage of a long shaft. The H.P. exhaust and the L.P. inlet are rotationally symmetrical chambers and are connected by a transverse tubular duct whose axis intersects the axes (A,B) pump is for liquid hydrogen, the second for liquid oxygen. The inlets, to the pumps are coaxial with the pumps.