The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Jun. 29, 1993
Filed:
Jun. 11, 1991
Daniel E Nelson, Altamonte, Springs, FL (US);
Anju Nelson, Altamonte, Springs, FL (US);
Other;
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.