3results about How to "Improve ignition performance" patented technology

The application relates to a grain refinement and ignition performance synergic optimization preparation method of a rare earth ignition alloy, and belongs to the technical field of rare earth ignition alloy manufacturing. According to percentages, the preparation raw material of the blank includes 35-45% of lanthanum, 15-30% of cerium, 5-15% of tin, 5-10% of zinc, 5-10% of praseodymium, 1-5% of neodymium and 15-25% of iron. The synergic action of the nanoscale active metal additive and the blank enables the rare earth ignition alloy to generate continuous sparks under slight friction or impact, and improves the ignition performance of the traditional rare earth ignition alloy.

This invention discloses a fuel atomization system suitable for the combustion chamber of a regenerative micro gas turbine, comprising: a T-shaped evaporator, a swirling oil-gas duct, a coaxial atomizing nozzle, an air intake pipe, and a fuel line protection sleeve; the T-shaped evaporator, the swirling oil-gas duct, and the coaxial atomizing nozzle are arranged coaxially, the air intake pipe is eccentrically connected to the side wall of the coaxial atomizing nozzle and can introduce high-pressure gas from the section before the regenerator after the compressor, the initially atomized mixed oil and gas enters the swirling oil-gas duct for further atomization and then evaporates and is ejected through the T-shaped evaporator, the fuel line protection sleeve is coaxially arranged on the outside of the swirling oil-gas duct and the coaxial atomizing nozzle and can avoid the direct impact of high-temperature backflow gas on the coaxial atomizing nozzle. This invention can significantly optimize fuel atomization quality, shorten the combustion chamber length, improve combustion efficiency, and improve the uniformity of combustion chamber outlet temperature distribution by adding a coaxial atomizing nozzle and an air intake pipe upstream of the traditional evaporator.

A gas turbine combustor is provided. The gas turbine combustor includes a first air flow passage that causes air to flow out toward a combustion chamber, and a fuel flow passage that causes fuel to flow out with respect to the air flowing out from the first air flow passage. The first air flow passage is configured to expand the air flowing out from the first air flow passage toward the inside of the combustion chamber. The gas turbine combustor includes a second air flow passage that causes air to flow out from a vertical direction with respect to the air flowing out from the first air flow passage.