The present invention relates to an incinerating system comprising an ejector system comprising an ejection nozzle and a fuel-air mixing system, a combustor, and an exhaust system, wherein the fuel-air mixing system and/or at least a portion of the combustor are oriented in a non-conventional direction/configuration, and wherein the ejector system is configured to provide required motive force in order to drive flame to continue through the burner in a desired direction.
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
F23D 11/24 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
F23D 14/10 - Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner with elongated tubular burner head
F23D 14/64 - Mixing devicesMixing tubes with injectors
The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system comprising at least one fluid intake member having an inlet end and an outlet end, the inlet end being in fluidic communication with the fluid ejection nozzle to receive the propellant ejected from the nozzle.
F02C 7/042 - Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
F02C 7/10 - Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
F02C 7/224 - Heating fuel before feeding to the burner
F02K 7/10 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
F02K 9/08 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants
F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
The present invention relates to an incinerating system comprising an ejector system comprising an ejection nozzle and a fuel-air mixing system, a combustor, and an exhaust system, wherein the fuel-air mixing system and/or at least a portion of the combustor are oriented in a non-conventional direction/configuration, and wherein the ejector system is configured to provide required motive force in order to drive flame to continue through the burner in a desired direction.
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system comprising at least one fluid intake member having an inlet end and an outlet end, the inlet end being in fluidic communication with the fluid ejection nozzle to receive the propellant ejected from the nozzle.
The present invention provides a fuel incinerating system comprising a fuel injector, a multi-stage fuel-air mixing device comprising a plurality of fuel intake tubes stacked vertically and configured to provide annular gaps between one or more of the vertically stacked fuel intake tubes to entrain ambient air to form a fuel-air mixture; and a combustor in communication with the fuel-air mixing device and defining a combustion chamber and in communication with an ignition source. The combustor is configured to impede flow of the fuel-air mixture through the combustion chamber to achieve a desired retention time of the fuel-air mixture within the combustion chamber to achieve substantially complete combustions of the fuel.
F23D 14/02 - Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
F23C 7/00 - Combustion apparatus characterised by arrangements for air supply
F23D 14/08 - Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner with axial outlets at the burner head
F23J 15/00 - Arrangements of devices for treating smoke or fumes
The present invention provides a fuel incinerating system comprising a fuel injector, a multi- stage fuel-air mixing device comprising a plurality of fuel intake tubes stacked vertically and configured to provide annular gaps between one or more of the vertically stacked fuel intake tubes to entrain ambient air to form a fuel-air mixture; and a combustor in communication with the fuel-air mixing device and defining a combustion chamber and in communication with an ignition source. The combustor is configured to impede flow of the fuel-air mixture through the combustion chamber to achieve a desired retention time of the fuel-air mixture within the combustion chamber to achieve substantially complete combustions of the fuel.
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
The present invention provides a fuel incinerating system comprising a fuel injector, a multi- stage fuel-air mixing device comprising a plurality of fuel intake tubes stacked vertically and configured to provide annular gaps between one or more of the vertically stacked fuel intake tubes to entrain ambient air to form a fuel-air mixture; and a combustor in communication with the fuel-air mixing device and defining a combustion chamber and in communication with an ignition source. The combustor is configured to impede flow of the fuel-air mixture through the combustion chamber to achieve a desired retention time of the fuel-air mixture within the combustion chamber to achieve substantially complete combustions of the fuel.
F23C 7/00 - Combustion apparatus characterised by arrangements for air supply
F23D 14/02 - Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system comprising at least one fluid intake member having an inlet end and an outlet end, the inlet end being in fluidic communication with the fluid ejection nozzle to receive the propellant ejected from the nozzle.
The present invention relates to an incinerating system comprising an ejector system comprising an ejection nozzle and a fuel-air mixing system, a combustor, and an exhaust system, wherein the fuel-air mixing system and/or at least a portion of the combustor are oriented in a non-conventional direction/configuration, and wherein the ejector system is configured to provide required motive force in order to drive flame to continue through the burner in a desired direction.
F23G 7/08 - Methods or apparatus, e.g. incinerators, specially adapted for combustion of specific waste or low grade fuels, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases using flares, e.g. in stacks
The present invention relates to a propellant feed system for a rocket engine including a jet pump including a motive inlet for receiving a gaseous propellant, a driven inlet for receiving a liquid propellant, and an outlet for ejecting a mixed stream of the gaseous propellant and the liquid propellant. The propellant feed system further includes a heat exchanger configured to transfer thermal energy from a combustion chamber to the liquid propellant or the mixed stream, thereby transforming the liquid propellant or the mixed stream into the gaseous propellant. The propellant feed system further includes a pump configured to pump the liquid propellant or the mixed stream into the heat exchanger.
F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
F02M 31/14 - Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture for heating by using heat from working cylinders or cylinder heads
F04B 17/00 - Pumps characterised by combination with, or adaptation to, specific driving engines or motors
F04B 19/06 - Pumps for delivery of both liquid and elastic fluids at the same time
