Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.

Abstract: A two-stroke, opposed-piston engine with one or more ported cylinders and uniflow scavenging includes an exhaust gas recirculation (EGR) construction that provides a portion of the exhaust gasses produced by the engine for mixture with charge air to control the production of NOx during combustion.

Abstract: A power-generating system is provided for operating adiabatically and reducing emissions of greenhouse gases contributing to global warming. The system may include gas reactors and/or combustors that burn a fuel and an oxygen-containing gas under substantially adiabatic conditions such that high-pressure combustion products and low pressure combustor housing cooling air are combined to produce a medium pressure working fluid. Higher thermal efficiencies reduce emissions of greenhouse gases. Products of combustion can be processed to further reduce emissions of carbon dioxide and other greenhouse gases from portable and stationary exhaust-producing devices using different fuels. The system may also include solar collectors that pick up a spectrum of solar energy by means of cells containing fluids, aligned to concentrate the solar rays. The collectors may pick up direct and/or diffused solar radiation and can be used to power self-propelled vehicles or function as a roof of a building.

Abstract: A power generation system (10) and method of operating a power generation system (10). An exemplary power generation system (10) shown in FIG. 1 includes a gasification system (2) for generating a supply (33) of a first gas comprising hydrogen and a supply (39) of a second gas comprising carbon monoxide based on a chemical breakdown of hydrocarbons in a melt (17). A component system (3) produces a supply of steam (99) by reacting one of the streams of gas and a steam turbine (120) generates mechanical power by expanding the steam (99). In an associated method, a melt (17) is created in a gasifier (12) which then receives a hydrocarbon source (22) to generate a continuous supply (33) of a first gas comprising hydrogen while increasing concentration of dissolved carbon in the melt (17). Hydrogen present in the first gas is supplied to a first combustor (90). A continuous supply (39) of a second gas comprising carbon monoxide is generated with carbon present in the melt (17).

Abstract: An adiabatic power generation method and apparatus includes at least one combusting device to combust any suitable fuel and an oxygen-containing gas to produce hot high pressure combustion gases. Also includes modified present art combustors, wind and solar energy sources. A portion of the expanded gases, or ambient air is mixed with the combustion gases to form a mixture of gases as working fluid that is fed to a work-producing device.

Abstract: A system for propelling a watercraft using hydrogen. The system comprises a combustion chamber, an accumulator system, an ignition system, and a propulsion control system. The combustion chamber defines an upper portion and a lower portion. The accumulator system stores pressurized fluid. A first check valve is arranged to allow water to flow from the exterior of the watercraft into the lower portion of the combustion chamber. A second check valve is arranged to allow water to flow from the lower portion of the combustion chamber to the accumulator system. A propulsion control valve is arranged to control the flow of water from the accumulator system to the exterior of the watercraft. A mixture of hydrogen and oxygen is introduced into the upper portion of the combustion chamber.

Abstract: A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to the combustor. A secondary fuel, comprising air and an amount of one or more volatile organic compounds, is supplied to a compressor, which compresses the secondary fuel and directs the secondary fuel to the combustor and the reaction chamber. The system is suitably configured to enable the stoichiometric reaction of the two fuels in a manner sufficient to destroy the volatile organic compounds contained in the secondary fuel and power a turbine engine connected to an exit of the reaction chamber.

Abstract: A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to the combustor. A secondary fuel, comprising air and an amount of one or more volatile organic compounds, is supplied to a compressor, which compresses the secondary fuel and directs the secondary fuel to the combustor and the reaction chamber. The system is suitably configured to enable the stoichiometric reaction of the two fuels in a manner sufficient to destroy the volatile organic compounds contained in the secondary fuel and power a turbine engine connected to an exit of the reaction chamber.

Abstract: A hot gas manifold system for a gas turbine power plant utilizing a pressurized fluidized bed combustor producing gas that is heated in two topping combustors. Each topping combustor is connected to a separate manifold. The manifolds, which are adjacent each other in a forward and aft arrangement, are disposed in the turbine shell between the compressor and turbine sections of the gas turbine and each forms a toroidal chamber that encloses the rotor. A plurality of ducts extend downstream from each manifold, with the ducts of the forward manifold extending through the aft manifold. Each of the ducts has an arcuate outlet that together form an annular hot gas path that matches the annular inlet to the turbine section. The ducts from each manifold form an alternating array so the hot gas from each of the individual topping combustors is symmetrically distributed around the turbine inlet.

Abstract: A low pollution combustion chamber for a turbojet engine is disclosed in which first and second combustion chambers are oriented in a counter-flow direction and both combustion chambers communicate with a separate and distinct exhaust chamber. The first combustion chamber has a fuel injector, as well as a primary oxidizer intake, and the wall bounding the first combustion chamber defines a plurality of dilution oxidizer intake orifices. The wall also defines a first exhaust orifice located approximately midway between the upstream and downstream ends of the first combustion chamber. A second combustion chamber has a second fuel injector, as well as a second primary oxidizer intake, but the wall defining the second combustion chamber does not define any dilution oxidizer intake orifices. A second exhaust orifice also communicates with the exhaust chamber.

Abstract: A combustion chamber suitable for use in a gas turbine engine includes a first enclosure with a fuel injector for low-power operation and a primary-oxidizer intake, a second enclosure with a fuel injector for full-power operation and a primary-oxidizer intake, and a third enclosure from which to evacuate burnt gases and which communicates with the first and second enclosures. The wall of the first enclosure includes intake orifices for a dilution oxidizer, but the wall bounding the second enclosure lacks any orifices other than the primary-oxidizer intake orifices.

Abstract: The engine described herein is adapted for a continuous supply of compressed gases and includes a first and second compressor mounted on a common shaft with a turbine. The air which enters the engine is compressed by the first compressor and passed into a combustion chamber, wherein it is mixed with fuel and the mixture is ignited. Resulting combustion products are conveyed to the turbine which is driven thereby and are further compressed by the second compressor. The compressed exhaust is led into an exhaust chamber via openings provided in an end plate, at which the common shaft supporting the compressors and the turbine terminates.

Abstract: A gas turbine combustion chamber, includes a common spherical purely mixing chamber having inlet openings and an outlet opening formed therein and being otherwise closed, the mixing chamber having a hemispherical end zone and a spherical segment zone disposed between the hemispherical end zone and the outlet opening, the inlet openings being formed in the hemispherical and spherical segment zones, a multiplicity of primary combustion chambers each being adjacent a respective one of the inlet openings for discharging into the mixing chamber, each of the primary combustion chambers having a respective longitudinal axis coinciding at least substantially at the center of the mixing chamber, a separate air supply and a separate fuel feed for each respective primary combustion chamber, the fuel feeds being switchable on and off in dependence on the load of the gas turbine.

Abstract: A low emission combustor assembly particularly suited for an automotive gas turbine engine has an inlet plenum supplied with regenerated compressor discharge, an exhaust plenum, a diffusion flame combustion chamber disposed between the inlet and exhaust plenums, and a catalytic combustion chamber also disposed between the inlet and exhaust plenums so that parallel flow paths are established between the inlet and exhaust plenums. During engine start-up, fuel is supplied only to the diffusion flame combustion chamber and regenerated compressor discharge simultaneously flowing through the catalytic combustion chamber heats the catalyst to operating temperature and cools and dilutes exhaust from the diffusion flame combustion chamber.

Abstract: A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to the combustor. A secondary fuel, comprising air and an amount of one or more volatile organic compounds, is supplied to a compressor, which compresses the secondary fuel and directs the secondary fuel to the combustor and the reaction chamber. The system is suitably configured to enable the stoichiometric reaction of the two fuels in a manner sufficient to destroy the volatile organic compounds contained in the secondary fuel and power a turbine engine connected to an exit of the reaction chamber.