5results 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.

The application relates to the technical field of gas turbine engines and discloses a laser ignition device and a combustion chamber with the same. The laser ignition device comprises a laser mounting seat, an igniter mounting hole and a protection component mounting hole are arranged on the laser mounting seat; an igniter component, a lens body on the igniter component extends into the igniter mounting hole; a lens protection component, the lens protection component comprises a shell and a valve, the shell is fixedly connected with the laser mounting seat, a gas leakage hole is arranged through the shell, the valve is rotatably arranged in the shell, an extension piece is connected to the valve, a shielding piece is arranged at one end of the extension piece away from the valve, and a spiral vane is arranged on the valve in the axial direction of the shell. The laser ignition device is provided with the lens protection component, the valve is driven to rotate by the airflow in the combustion chamber, the lens body is automatically shielded and exposed in the ignition and non-ignition states. The time that the lens body is exposed to the high-temperature airflow is effectively reduced, the lens body is prevented from being polluted, scratched and corroded, and the service life of the lens body is prolonged.

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.

To improve ignition performance of a gas generating agent in a gas generator. A gas generator includes: an igniter assembly including an igniter body accommodating an ignition charge, the igniter body including an igniter cup ruptured by a combustion product generated by combustion of the ignition charge and an electro-conductive pin that supplies a current for igniting the ignition charge, a collar portion holding the igniter body, and a holding portion interposed between the igniter body and the collar portion and fixing the igniter body to the collar portion, the igniter assembly releasing the combustion product; a housing having a tubular shape, the housing including a combustion chamber accommodating a gas generating agent, and including a gas discharge port through which a combustion gas generated by combustion of the gas generating agent is discharged; and an elastic member having a tubular shape, the elastic member being disposed between the igniter assembly and the gas generating agent in the housing with an axial direction of the elastic member being in a direction same as a direction of the housing, the elastic member including a regulation portion at an inner periphery thereof, the regulation portion being configured to regulate a direction in which the igniter cup ruptured expands.

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.