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Anju Nelson

Daniel Paul Nelson

Daniel E Nelson

Daniel Emmet Nelson

A complete machining center has a horizontal machine bed () with a vertical-axis trunnion () pivotal horizontally with computer-coordination proximate a first-end portion () and a traveling tool column () with computer-coordinated horizontal X and Y axes and vertical Z tool travel on a compound slide () proximate a second-end portion () for horizontal access of a cutting tool () on the traveling tool column to work pieces on a work-piece rotator () and for horizontal access of the cutting tool to work pieces on a vertical-axis milling table (), either of which are positioned on the horizontally pivotal vertical-axis trunnion (). A work-piece changer () is provided for optionally manual or computer-coordinated work-piece setup, setup reversing and finished-work-piece removal.

Complete machining center and method

A method and apparatus to heat-activate hydrogen of water for powering rotational, reaction-thrust and projectile-expulsion embodiments () of a water engine () with hydrogen energy of water which is spray-atomized and electrically heated internally in one or more hydrogen activators (). Water-hydrogen electrons of the spray-atomized water are heat-activated up to exponentially greater output heat-activation energy than input activation-heat energy added electrically with power generated from forms of the water engine. A minor portion of the output heat-activation energy of the water hydrogen is utilized for generating electrical current for the input activation heat of the spray-atomized water in the hydrogen activators. Net output heat-activation pressure of water-hydrogen is directed from one or more of the hydrogen activators to one or more use chambers () of universal-use forms of the water engine. Rotational features of the water engine preferably employ a turbocam drive ().

Water engine and method

A combustion-and-steam engine system has a phase-change water injector (1) through which water is spray-injected into combustion gases in a combustion chamber (2) of a Nelson Engine (79) or any type of heat engine with either rotational or thrust power. A steam tube 45 in fluid communication between an injector orifice (25) and an internal periphery of the combustion chamber can be heated with resistance heat from an engine-electrical source (46) to provide phase-change of water en route to the combustion chamber in the steam tube. An injection-metering valve (22, 25, 26, 43) has a return spring (31) with pressure regulatable by an adjustment means (32, 33, 36, 37, 38, 40) to select flow rate past the injection-metering valve to a return tube (57, 74) without requiring lubricity of water or other fluid under high pressure. A phase-change fuel injector (65) has similar components with a heat tube (13) that can be shorter and bigger around to allow rapid entry of fuel-rich combustion gases into the combustion chamber ahead of steam from the phase-change water injector. Design levels of completeness of combustion of fuel are provided prior to injection of a design heat and consistency of wet steam and dissociated water. This provides a combination of designedly fuel and hydrogen combustion in combination with steam pressures from cooling a heat engine with phase-change heat absorption of water particles in the combustion chamber.

Combustion and steam engine system and methods

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.

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Orlando, FL, United States of America

Anju Nelson