| 摘要 |
<p>PURPOSE: To stabilize the operation of an annular combustor for a gas turbine in the environment of high temperature rise by reducing the length of the combustor, and combining the air intake through constitution of regions on the circumference. CONSTITUTION: An air intake is of one stage, and a combustor is divided into a primary region and a dilution region 30. Air passages 44, 46 are provided on each of a plurality of fuel nozzles 20, and a vortex flow chamber to give the vortex flow to the air in sucking the air in the normal combustion region is provided. The fuel nozzles 20 are arranged with intervals on the circumference flitted in a dome. The air passages 40, 42 in the fuel nozzles, and the air passages 44, 46 in an outer annular wall, i.e., a liner 48 and in an inner annular wall, i.e., a liner 50 are of different dimensions so as to demarcate the space in the combustor to which the air flow is fed. That means, the air intake openings 42, 44, 46 to make the air flow smaller than the air flow to be sucked in other spaces on the circumference are included in the specified spaces on the circumference.</p> |
