| 摘要 |
FIELD: power engineering, applicable in gas-turbine plants and aircraft engines with various (canal-type and remote) combustion chambers and in furnaces operating on liquid or gaseous fuel and air with an air-to-fuel ratio exceeding 1.0. SUBSTANCE: the device has a combustion chamber, furnace with a mixing chamber, fuel and air supply passages, disk installed around the combustion chamber and having axial holes for supply air to the combustion chamber, in its turn the mixing chamber is made in the form of a diffuser with a cylindrical probe for fuel supply coaxially positioned at its inlet, the device is provided with a flap-probe located around the outlet part of the furnace mixing chamber and projecting over its end by a value not less than that of the diameter of its outlet part. The holes in the disk are made inside the zone restricted by the flap-probe. EFFECT: enhanced combustion completeness, reduced harmful ejections due to prevention of supply of additional air to the zone of mixing and beginning of burning. 1 dwg |
