轴向三级旋流燃烧室流场结构大涡模拟

为深入了解真实航空发动机燃烧室内部复杂流场结构，在自有CFD平台上采用动态亚网格模型对一种轴向3级旋流燃烧室的单个头部矩形试验模型0.5MPa下冷态流场结构进行了LES(大涡模拟).为避免试验模型简化误差，对包括火焰筒上约2000个气膜孔在内的燃烧室所有精细结构进行了完全仿真.计算模拟了燃烧室内复杂流场从静止启动到统计定常状态的完整非定常发展过程，成功捕捉到主旋流与横向对冲射流相互影响作用及涡旋破碎等细观结构，获得的测点湍动能谱与湍流经典理论中惯性子区-5/3规律一致，LES时间平均流场结构与已有PIV（particle image velocimetry）试验结果吻合，表明所建立的高仿真网格与LES方法可进一步用于真实航空发动机环形燃烧室流场数值模拟. 

Large eddy simulation of flow structure in combustor with axial triple swirler

To gain an improved understanding of the complex flow field structures in practical aero-engine combustor,LES (large eddy simulation) with dynamic Smagorinsky sub-grid model on self-developed CFD platform was made to explore the cold flow field in single rectangle dome of triple swirler under 0.5 MPa.The complex geometric configuration including all about 2 000 film cooling holes on liner was fully simulated without any conventional simplification in order to reduce the modeling errors.The capability of the CFD code to simulate very complicated flow was validated by the calculation.Unsteady process of the turbulent swirling flow developing from static to statistically stationary status was totally reproduced.Interaction between mainstream and transverse jet was investigated and swirling flow characteristics like vortex breakdown were well captured.Turbulent kinetic energy spectrum predicted by calculation was in reasonable agreement with the-5/3 law in classic turbulence theory,while time-averaged flow field predicted by LES fitted well with PIV (particle image velocimetry) measurement.It shows that the high fidelity mesh and large eddy simulation can be applied in the simulation of full annular combustor of aero-engine.