Purpose of the development: Ignition of a combustion-mixture and stabilization of combustion in combustion chambers of turbine jets, transportable installations and gas-pumping stations operating in extreme conditions. Good prospects for application in technological and power plants employing hydrocarbon fuels.

Recommended application field: Power Engineering.

Advantages over analogues: As compared with its nearest analogs - rotational burners of a straight-flow type - this burner ensures formation of the starting and stabilizing plume in a broad range of nozzle outlet temperatures, including the highest possible temperature corresponding to the stoichiometric ratio of the air-fuel mixture components; corners of disclosure of 100-1200; exhaust velocities, including supersonic velocity, of the combustion products. The devices are of simple design and reliable. They have small mass-size parameters. They can operate in various climatic conditions in a broad range of temperatures, pressure and humidity. They have natural thermal self-isolation of the heat-stressed elements (temperature of the body of the device does not exceed 3000С while the temperature of the combustion products is over 2000 град.С). A new kind of product with improved technical and economic characteristics and broader technological possibilities. It has good prospects for entering the market.

The development stage readiness: Pre-production model is made

Description of the development:
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A distinctive feature of the process is formation of a reverse-flow vortex motion of the combustion-mixture and combustion products, which ensures optimal conditions for the processes of mixing, primary inflammation and combustion of the mixture. The mixture is formed as a peripheral curl, and the combustion products - as the central one. The combustion process is carried out in the area a heat tube, opposite to the torquing apparatus, and the air moves through the torquing apparatus of an original design. The burners are designed as igniters stabilizing torches and front burners of combustion chambers. The igniters have a single-stage combustion chamber of a rotational reverse-flow type. Compressed air is supplied from an autonomous source. The stabilizing torches have a two-stage combustion chamber. Fuel for the first and second stages is liquid or gaseous. Temperature of the plume at the exit of the nozzle: 700-2000 degr. С, consumption of compressed air: 5-60 g/s, pressure of the compressed air in a start-up mode: 0.15-0.6 МPа, fuel-air charge pressure in the combustion chamber: 10.3-101.3 kPа, range of the air surplus coefficient for a reliable start-up and stable operation: 0.3-8.0. With the use of heated air at the inlet of igniter a spontaneous combustion of the air-fuel mixture is ensured in the rotational chamber of the igniter. This allows to do without spark-plugs, for example, in afterburners of turbine jets. Patents № 1726917 of 16.03.1993; № 2196940 of 20.01.2003 of the Russian Federation have been obtained. Application for patent № 2002125476 of 09. 2002 of the Russian Federation has been submitted.

Information about newness of the development:
there are Ukrainian patents -- 2 items

Possibility of transfer abroad:
Licence's sale
Licence's sale
Creation of joint enterprise

Photo

Country Russia

For additional information turn to:
E-mail: gal@uintei.kiev.ua