PURPOSE: To provide the combustor capable of stable burning and high efficiency burning over wide operational range of gas turbine using a low calorie gas fuel having a low burning rate and a difficulty of high efficiency burning.
CONSTITUTION: An air pressured by a compressor is blown through between an outer cylinder 11 and an inner cylinder 9 in a gas turbine conbustor, a part of the air is supplied into inside of the inner cylinder from an air revolving device 12. A fuel is supplied into inside of the inner cylinder from a fuel revolving device 16 of a fuel nozzle 10. An air flow 19 and a fuel flow 18 inside of the inner cylinder are mixed with a part of the air from the primary air hole 13 and burned under the flame stabilizing condition within a recirculating area 23, simultaneously, located at an outer periphery of the fuel-air revolving device, form a stagnation 22 in the mixed air flow by a flame stabilizing device 20 protruded toward downstream side, also the slow flow rate air which is supplied from the second primary air hole 24 then flowed through an annular part located between the flame stabilizing device and the inner cylinder, is mixed with said mixed air, and the flame stabilizing is maintained under only high ratio of fuel to air condition. At the downstream side of the primary air hole 13, the burning of a large part of the fuel is completed, at the downstream side of the secondary air hole 14, the complete burning of the remaining fuel is contrived and the gas temperature is lowered down to the temperature at the turbine inlet by the air from the diluent air hole 14.
FUJIMURA HIDEKAZU
ISHIBASHI YOUJI
Next Patent: JPS5952134