Power plants – Reaction motor – Including mechanical air compressor or air flow inducing means
Patent
1991-06-11
1993-06-29
Bertsch, Richard A.
Power plants
Reaction motor
Including mechanical air compressor or air flow inducing means
60729, F02K 300
Patent
active
052223612
ABSTRACT:
A rocketjet engine has a light, hollow double-acting compressor piston (35 and 123). It is reciprocated by a smaller-diameter double-acting power piston (51) through a power shaft (52 and 60) connecting them. Up to 90 percent of intake air is routed from a compressor cylinder (36) to a thruster (1 and 106) and the remaining ten percent to a power cylinder (55). Fuel and water are preheated and sprayed into the power cylinder with phase-change injectors 67-70 at ends of compression strokes after complete flame-front propagation to actuate the compressor with combined combustion and steam pressure. To provide steam-propulsion pressure in addition to peak-heat combustion pressure and to cool the thruster, fuel is preheated and spray injected into an upstream combustor (8 and 109) portion of the thruster (1 and 106). Water is added as wet steam through a flash-boiler-steam injector (30) at a downstream portion of the combustor in order achieve prior peak combustion heat, pressure and completeness of flame propagation. Variable nozzle-to-throat-ratio thrusters (1) maximize thrust efficiency at any atmospheric or space altitude. Fixed-nozzle-to-throat-ratio thrusters (106) maximize efficiency and low weight at dedicated altitude ranges. A porous intake cone (90) has less frontal drag than pointed rocket engines. Various vibration-damping, power-take-off and operational features are provided.
REFERENCES:
patent: 3541795 (1970-11-01), Nelson
patent: 3570463 (1971-03-01), Nelson
Nelson Anju
Nelson Daniel E.
Bertsch Richard A.
Wicker W. T.
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