GB619036A - Improvements in or relating to combustion gas generators for gas turbines and like power plants - Google Patents

Abstract

619,036. Burners. BENDIX AVIATION CORPORATION. Sept. 21, 1945, No. 8290/48. Convention date, Oct. 9, 1944. Divided out of 604,466. [Class 75 (i)] [Also in Group XII] A generator for heating and expanding air flowing thereto under pressure comprises a combustion chamber provided with a fuel discharge nozzle at one end, and means for admitting air to the burner in a plurality of strata of varying velocities with the stratum of lowest velocity in the immediate region of the nozzle. The combustion chamber 8 comprises a tube 7a surrounded by a casing 5 to which air is supplied through a conduit 6. A baffle wall 107 at the end of the tube 7a is formed with a series of annularly arranged calibrated air inlet orifices 108, 109, and 110, which are of progressively decreasing area or flow capacity as they approach the centre of the wall 107 where a fuel nozzle 9 is fitted. The air passes through the orifices 108, 109, 110 into pressure regulating compartments 1081, 1091, and 1101, which may contain steel wool, and thence through baffles 103, 106, and 111, formed with calibrated orifices, so that the air flows into the combustion chamber in a plurality of concentric masses having velocities progressively decreasing' towards the common control axis. Additional air is admitted to the combustion zone through orifices 100 in the tube 7a. The apparatus may be used in conjunction with the fuel feeding system described in Specification 604,466, and the fuel nozzle may be of the form described in Specification 608,031.