Abstract: An engine including a means for supplying fuel to the combustion chamber of the fire tube, that includes a variable-volume transfer chamber for receiving fuel, a fuel transfer means from the tank of the engine towards the transfer chamber, and injection means for injecting fuel into the combustion chamber from the transfer chamber. The engine further includes an elastic return at least partially defined by the fuel contained in the transfer chamber.

Abstract: The method and apparatus of the present invention discloses a power plant operating at low inlet pressure and temperature using a combination of conventional internal combustion engine techniques and jet engine techniques. The combination of a unique combustion chamber design, a novel variable impedance blade set turbine and a closed loop control system allows a variable resonant frequency for combusted gases. As the resonant frequency is approached a control mechanism uses sensor data to maintain the operating point such that maximum power output is achieved for a given throttle setting. The combination of the unique combustion chamber design, multiple fuel injector/sparking device pairs, finely atomized fuel, excess oxygen and the closed loop control system further provides a very linear power curve with low exit hydrocarbon pollution levels and high fuel efficiency.

Abstract: This invention is a fuel injection control system for a turbine engine. The invention uses at least one fuel injector, having means for injecting fuel in pulses to the combustion chamber of a turbine engine, and an electronic control unit to receive and interpret input sensor signals from selected operating functions of the engine and to generate and direct fuel injection signals to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired operating speed, caused by variable operating loads encountered by the turbine engine. This configuration provides significantly greater fuel efficiency, better operational control and response time, and a lighter weight than is currently available in turbine engines. The invention may be used in many applications such as commercial, private, experimental and military aviation, power plant turbines, and other industrial, military and mining applications.

Abstract: A miniature heat source capable of being used in a hand-held device for delivering a metered pulse of fuel to a combustion chamber where it is converted into a pulsed amount of heat. For example, the heat source apparatus can be used in a hand-held cigarette smoking system or within a portable device wherein a microturbine generates electricity, as well as any type of environment where a high energy pulse of heat is desired. The heat source includes a valve such as a sliding, rotatable or timed valve which delivers a metered volume of fuel to the combustion chamber. The valve can deliver the fuel, in an expanded gaseous form, to a venturi conduit which increases the velocity of the gas flow, and delivers the fuel to a combustion chamber where the gas is mixed with air. The combustible mixture is then combusted within the combustion chamber by ignition and/or by catalyzed oxidation.

Abstract: In a staged gas turbine combustion engine, each combustion chamber of an annular array of chambers includes at least a pilot and a main combustion stage each having an fuel injection nozzle; the method includes feeding fuel continuously in operation to the pilot stage nozzle and controlling the fuel flow to the main stage nozzle through a pulsing and dosing valve to control the fuel flow delivered to the main stage fuel nozzle.