发明名称 FUEL NOZZLE FOR GAS TURBINE COMBUSTOR
摘要 PURPOSE:To keep stable combustion upon low load without spoiling the low NOx characteristics of the combustor by a method wherein the position of the fuel nozzle can be moved on the axial line of the combustor to utilize an air pressure at the entrance of the combustor, which is proportional to the load of the combustor. CONSTITUTION:Gas fuel enters from a flange 4, passes through the center of a piston rod and a swirler 6, then, is injected from the nozzle under being sent by the air in the swirler. Combustion is generated in a primary combustion area immediately after the fuel nozzle while dilution holes 8 are provided to introduce much amount of air and effect combustion. When the load of the combustor is reduced, the air pressure at the entrance of the combustor becomes small in accordance with the load, therefore, a piston 3 moves upward by the force of a spring 10 and the tip end of the fuel nozzle moves to the upper end of a combustor liner 7 together with the swirler 6. In this case, the dilution holes do not affect to the primary combustion area, therefore, the optimum air-fuel ratio in accordance with a no-load condition may be set. The movement of the fuel nozzle is continuous from no load to a rated load, therefore, the stability of the flame of combustion may be excellent at any load.
申请公布号 JPS6017635(A) 申请公布日期 1985.01.29
申请号 JP19830123357 申请日期 1983.07.08
申请人 HITACHI SEISAKUSHO KK 发明人 WADA KATSUO
分类号 F23C5/06;F02C7/232;F23C99/00;F23R3/28;F23R3/34;(IPC1-7):F23R3/34;F02C9/00;F23C11/00 主分类号 F23C5/06
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