Volume 35 Issue 9
Sep.  2020
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CHEN Xuanren, LIU Aiguo, HU Jian. Effect of fuel distribution on combustion performance for micro gas turbine combustor,[J]. Journal of Aerospace Power, 2020, 35(9): 1875-1883. doi: 10.13224/j.cnki.jasp.2020.09.009
Citation: CHEN Xuanren, LIU Aiguo, HU Jian. Effect of fuel distribution on combustion performance for micro gas turbine combustor,[J]. Journal of Aerospace Power, 2020, 35(9): 1875-1883. doi: 10.13224/j.cnki.jasp.2020.09.009

Effect of fuel distribution on combustion performance for micro gas turbine combustor,

doi: 10.13224/j.cnki.jasp.2020.09.009
  • Received Date: 2020-02-28
  • Publish Date: 2020-09-28
  • A dry low emission (DLE) micro gas turbine combustor with variable nozzle position and multi-point fuel injection was put forward. In order to gain the effect of different fuel-staged methods on the combustion performance for the combustor, and the effect of fuel distribution mode between pilot and primary on combustion performance, different distribution modes of the combustor were experimentally studied by numerical simulation. Results showed that: the change of fuel nozzle position had little effect on the emissions. With the increase of two-stage fuel distribution ratio, the NOx emissions decreased first and then increased, and there existed an optimal fuel distribution ratio to minimize NOx emissions. There existed obviously a primary recirculation zone (PRZ) in combustor, helping to facilitate ignition and propagation of flame. The amount of thermal NOx produced was directly related to the size of the region above 1 950 K and the highest gas temperature. The NOx emissions of the designed combustion can be reduced to below 50 mg/m3 under all working conditions with natural gas as fuel, which can reach the level of low-emission combustion (less than 50 mg/m3).

     

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