127results about How to "Reduce gas emissions" patented technology

A carbon sequestration and dry reforming process for the production of synthesis gas and sequestered carbon from carbon dioxide. Two-dimension catalysts for sequestering carbon and a process to produce same. A method for activating two dimension catalysts.

A carbon sequestration and dry reforming process for the production of synthesis gas and sequestered carbon from carbon dioxide. Two-dimension (non-porous) catalysts for sequestering carbon are also disclosed and a process to produce same as well as a method for activating two dimension catalysts.

In a fuel supply system for an internal combustion engine having two separate storage containers for liquid fuels, both connected to a first controllable valve which is connected, via a connecting line including a fuel pump to an inlet of a second controllable valve having two outlets in communication by separate fuel lines with a fuel injection nozzle of the internal combustion engine, each of the two separate fuel lines includes a fuel pressure regulator, one being in communication with one and the other with the other of the two separate fuel storage containers for returning exess fuel to the fuel storage container from which fuel is being supplied to the fuel injection nozzle.

In a turbine engine hydrogen is injected into the combustor in response to a power output level of the turbine engine. In a preferred embodiment, gaseous hydrogen is always injected at low-power operations and switched off at mid-power and high-power operations.

A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.

Apparatus for controlling emissions from an internal combustion engine including an enclosed housing one end of which is provided with an inlet and the other end an outlet. A coaxial tubular member extends from the inlet into the housing. A catalytic cell surrounds the tubular member and separates two chambers, a first surrounding the tubular member near the inlet and the other on the opposite side of the catalytic cell. Exhaust gases from the internal combustion engine flow through the tubular member, expanding into the other chamber, then through the catalytic cell for conversion of nitrogen oxides, carbon monoxide and unburned hydrocarbons to less noxious components, expanding into the first chamber for eventual discharge through the outlet.

An apparatus includes a low temperature fuel cell, a high temperature fuel cell or a hydrocarbon reformer, a hydrocarbon fuel supply, an oxygen generator, and a molecular sieve. The oxygen generator separates air to provide oxygen enriched air to the fuel cells and the reformer. Hydrocarbon fuel is provided to the high temperature fuel cell or the reformer, and the exhaust gas thereof may be separated through the molecular sieve, to provide hydrogen enriched gas to the low temperature fuel cell, water, carbon monoxide, and carbon dioxide. The low temperature fuel cell outputs nitrogen gas and high purity water. The emitted carbon oxides and nitrogen oxides are catalytically converted to nitrogen and carbon dioxide being returned to the atmosphere. The process and apparatus are very efficient, produce high purity water and electrical energy, and are environmentally friendly.

A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas emissions during engine operation. The plurality of main fuel injector assemblies are arranged in a substantially circular pattern of a first radius, and each includes an outlet port having a first divergence angle. The plurality of pilot fuel injector assemblies are arranged in a substantially circular pattern of a second radius. Each pilot fuel injector assembly is disposed between at least two main fuel injector assemblies, and each includes an outlet port having a second divergence angle.