Abstract
Numerical simulation was performed to study the flow characteristics of advanced vortex combustor (AVC) with guide vanes and slots for aircraft engine. The results show that structural parameters of guide vane have significant effects on AVC, when a/B=0.4, b/H=0.4, c/L=0.1, it can obtain desirable dual-vortex structure, acceptable pressure loss and better combustion efficiency. AVC with guide vane has better performance than AVC without guide vane. Five slots air film cooling are brought in, the effect of flow injection angle (θ=30°, 60° and 90°) and injection ratio (R=1.2, 1.5, 2.0) on cooling performance of AVC are analyzed. The results show that there are 5 change regions for each cooling efficiency under different injection conditions. The variation law of the first region is different from the four region behind. The first slot air mainly mixes with the main flow and gets involved in the combustion while the four region behind can play a good role in cooling efficiency. Meanwhile, the effects of θ and R on flow field, temperature field, total pressure loss, combustion efficiency, outlet temperature distribution factor (OTDF) and the average cooling efficiency are presented. Finally, the film cooling conclusions are explained by field synergy theory, and results show that it can optimize the wall cooling effectiveness by field synergy theory.
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