| 摘要 |
<P>PROBLEM TO BE SOLVED: To eliminate incomplete combustion by stabilizing flame in a gas turbine combustor. <P>SOLUTION: The gas turbine combustor 1 has a premixing tube 3 which is composed of a heat chamber 2, an upper peripheral wall 6 having a hole 4 for generating a swirl flow in a space S, and a lower peripheral wall 5 in an outer cylinder 9. There is an inner wall 10 which is shaped like a through hole in the upper wall of the premixing tube. There is a first pressure injecting nozzle 7 at the center of the inner wall, and five pieces of second pressure injecting nozzles 8 are arranged at equiangular distances at the lower peripheral wall. Fuel, injected toward the center from each second pressure injecting nozzle rides on the swirl flow of air going to the heat chamber from the space S, is dispersed widely in the radial direction in the upper region Z2 of the combustor, and evaporated and ignited in an early stage for a long stay time and burnt completely. Unburnt ingredients such as soot decrease and the generation of NOx is also suppressed. <P>COPYRIGHT: (C)2013,JPO&INPIT |
