| 摘要 |
FIELD: power engineering.SUBSTANCE: supersonic plasma-chemical combustion-stabilisation device for a forward-flow combustion chamber, comprises two electrodes installed in the flow path of the combustion chamber that are serially arranged along the flow and made in the form of streamlined pylons with symmetrical aerofoil sections, one of which is an anode, electrically isolated from the metal wall of the combustion chamber and equipped with a tube to supply fuel and injectors for injection of fuel into the flow. At the same time the anode is bent so that the root part of the anode has negative sweep relative to the flow direction, and the end one - zero sweep, and the second electrode - cathode is arranged in the trace following the first one and is directly fixed on the wall of the combustion chamber, in the anode there is additionally a tube and injectors for injection of chemically active additives into the flow simultaneously with the fuel, the end of the root part of the anode at the side of the forward flow has a ledge in the form of a thin rectangular plate arranged in the plane of symmetry of the pylon, the rear edge of the plate is bevelled and has fillets in the corner points. At the same time the angle between the end surface and the rear edge of the anode is also rounded. Besides, on the rear edge of the end part of the anode in the zone of formation of the lower pressure zone there may be a cog arranged, for instance, of triangular or other shape, to ensure linkage of the discharge channel to it.EFFECT: invention makes it possible to provide for reliable ignition and stabilisation of combustion of hydrocarbon fuels in forward-flow supersonic combustion chambers in conditions, when traditional gas dynamic methods do not allow to do so.2 cl, 2 dwg |
