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116 results about "Unburned hydrocarbon" patented technology

Unburned hydrocarbons (UHCs) are the hydrocarbons emitted after petroleum is burned in an engine. When unburned fuel is emitted from a combustor, the emission is caused by fuel "avoiding" the flame zones. For example, in piston engines, some of the fuel-air mixture "hides" from the flame in the crevices provided by the piston ring grooves. Further, some regions of the combustion chamber may have a very weak flame, that is, they have either very fuel-lean or very fuel-rich conditions and consequently they have a low combustion temperature. These regions will cause intermediate species such as formaldehyde and alkenes to be emitted. Sometimes the term "products of incomplete combustion," or PICs, is used to describe such species.

Plasma ignition for direct injected internal combustion engines

An apparatus and method for the creation, placement and control of an area of electrical ionization within an internal combustion engine combustion chamber. This area of electrical ionization is positioned so that all of the fuel being injected into the combustion chamber must pass next to or through the area of electrical ionization to ensure that combustion has been initiated for all of the fuel as it is injected. This area of electrical ionization can be kept on as long as it is necessary to insure that the all of the fuel that is injected into the combustion chamber can be completely combusted. An engine equipped with this electrical ionization device has its fuel economy enhanced by timely, controlled, and complete combustion of all of the fuel injected into its combustion chamber. Furthermore, the pollutant emissions of both oxides of nitrogen and unburned hydrocarbons are reduced dramatically. Further, cold starting capability of this engine is greatly enhanced by a major reduction in the time necessary for the engine to warm up and a major reduction of pollutants created by the engine during the warm-up period. Additionally, this method of combustion also allows the engine to operate at a higher speed (rpm) allowing an increase in peak power output.
Owner:JAYNE MICHAEL E

Method and apparatus for actuating fuel trim valves in a gas turbine

The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each manifold supplies at least one fuel nozzle in multiple combustion chambers with fuel. The fuel control valves are mounted on the manifolds such that the weight of the fuel control valves and nozzles are carried by the manifolds, not the multiple combustion chambers. A plurality of thermocouples for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In carrying out the methods of the present invention for tuning a gas turbine, it is essential to note that the most efficient gas turbine is one which has the least nitrous oxides, the least amount of unburned hydrocarbons, and the least amount of carbon monoxide for a specified energy output. In order to tune the gas turbine to accomplish these objectives, it is desirable that each combustion chamber in the gas turbine be well balanced relative to the remaining combustion chambers. It is an aim of the present invention to tune each of the multiple combustion chambers such that no specific combustion chamber is rich or lean, and all are operating within about 1% of the remaining combustion chambers.
Owner:GENERAL ELECTRIC CO

Method and apparatus for actuating fuel trim valves in a gas turbine

The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each manifold supplies at least one fuel nozzle in multiple combustion chambers with fuel. The fuel control valves are mounted on the manifolds such that the weight of the fuel control valves and nozzles are carried by the manifolds, not the multiple combustion chambers. A plurality of thermocouples for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In carrying out the methods of the present invention for tuning a gas turbine, it is essential to note that the most efficient gas turbine is one which has the least nitrous oxides, the least amount of unburned hydrocarbons, and the least amount of carbon monoxide for a specified energy output. In order to tune the gas turbine to accomplish these objectives, it is desirable that each combustion chamber in the gas turbine be well balanced relative to the remaining combustion chambers. It is an aim of the present invention to tune each of the multiple combustion chambers such that no specific combustion chamber is rich or lean, and all are operating within about 1% of the remaining combustion chambers.
Owner:GENERAL ELECTRIC CO

Lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly

InactiveCN103123122AStable ignition sourceTaking into account the ignitionContinuous combustion chamberCombustion chamberFuel oil
The invention relates to a lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly, and belongs to the field of aero-engines. The core idea of the lean oil pre-mixing and pre-evaporating low-pollution combustion chamber is air classification and fuel oil classification. The lean oil pre-mixing and pre-evaporating low-pollution combustion chamber is composed of an on-duty stage/subsidiary mold and a mainstage / main mold, wherein the on-duty stage is composed of a first-stage axial swirler (8), a second-stage axial swirler (9), a sleeve (10) and an on-duty stage contraction and expansion segment (20), realizes diffusive combustion and provides a stable ignition source; and the main stage comprises a main-stage swirler (11), a main-stage oil supply pipe (15), an oil collection cavity (16), a fuel oil direct-injection type nozzle (17), a main-stage contraction and expansion segment (12) and a main-stage pre-mixing annular cavity (22) and is used for combusting a part of pre-mixed and pre-evaporated lean oil and lowering a high-temperature hotspot so as to reduce the emission of thermal nitric oxide (NOX). The lean oil pre-mixing and pre-evaporating low-pollution combustion chamber is in the mode of lean oil pre-mixing and pre-evaporating combustion with a central classification idea, other properties of the chamber cannot be sacrificed, and the emission of pollutants, including the NOX, smoke, carbon oxide (CO) and unburned hydrocarbon (UHC), of an aero-engine chamber can be effectively lowered at the same time.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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