以某波瓣形混合器加力燃烧室三维模型为研究对象，采用CFD方法对模型进行数值分析，建模时重点对波瓣形混合器和环形火焰稳定器进行网格加密。以飞行试验工况点获取的低压涡轮后总温、总压结合Gasturb软件计算出加力燃烧室出口的总温、总压作为整体流场CFD计算的边界条件进行计算。计算结果表明：经过波瓣形混合器后，内、外涵气流能够在较短轴向距离充分混合，总压恢复系数最大为0.984；在接近出口处热混合效率达到0516；气流经过环形火焰稳定器后，形成明显的低压回流区，且在出口处截面静压分布均匀，因此该加力燃烧室模型具有非加力状态流阻小的特点。通过对该型加力燃烧室流场特性分析，为加力燃烧室加力接通前内部参数获取提供技术支撑。

Taking the threedimensional model of afterburner of a certain lobed mixer as the research object,the model was analyzed numerically by computational fluid dynamics (CFD) method.In the modeling,the mesh encryption was focused on the lobed mixer and annular flame stabilizer.The total temperature and total pressure at the rear of the lowpressure turbine obtained from the flight test operating point,and the total temperature and total pressure at the outlet of the afterburner calculated by the Gasturb software were used as the boundary conditions for the whole flow field CFD calculation.The calculation results shows that after airflow passes through the lobed mixer,the inner flow and outer flow can be fully mixed in a short axial distance,and the total pressure recovery coefficient is 0.984 at the maximum; the thermal mixing efficiency reaches 0.516 near the outlet; after the airflow passes through the annular flame stabilizer,an obvious low pressure and return flow zone are formed,and the static pressure distribution in the outlet section is uniform,so the afterburner has the characteristics of the low flow resistance in the nonafterburning state.Through the analysis of the flow field characteristic of the afterburner,technical support is provided for the acquisition of internal parameters of the afterburner before the afterburner is switched on.

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