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为研究级间通道构型对双脉冲发动机一脉冲燃烧室气流再附着点的位置和对流换热系数的影响,本文采用基于格心的迎风型有限体积法数值求解雷诺平均Navier-Stokes方程组,空间离散采用AUSM-PW矢通量分裂格式,时间推进采用3阶三步TVD型Runge-Kutta显式方法,湍流模型采用适合模拟分离流动的改进SST湍流模型,并通过经验公式计算再附着点处的对流换热系数。结果表明:亚声速后台阶流动和固体火箭发动机燃烧室内流动的最大绝对误差分别为8.9%和5.8%;二脉冲工作的不同时刻,当二脉冲装药内孔直径大于级间通道直径时,级间孔直径每增大9.1%,气流再附着点位置平均减小28.2%,对流换热系数平均下降9.6%;其它条件相同时,级间孔宽度增加对气流再附着点位置和对流换热的影响比较小;级间孔角度变大使得气流再附着点的位置和对流换热系数分别平均下降3.4%和3.1%。
In order to study the effect of interstage channel configuration on the position of airflow reattachment point and the convective heat transfer coefficient in a pulsed combustion chamber of a two-pulse engine, a Renault-averaged Navier-Stokes equations was solved by the finite volume method based on the lattice- AUSM-PW vector flux splitting scheme is used for spatial discretization. Three-step three-step TVD Runge-Kutta explicit method is used for time discretization. The turbulence model adopts an improved SST turbulence model suitable for analogue separation flow, and the reattachment point Convection heat transfer coefficient. The results show that the maximum absolute errors of sub-sonic flow and solid rocket motor flow are 8.9% and 5.8%, respectively. At the different time of two-pulse operation, when the diameter of the two-pulse charge hole is larger than the diameter of the interstage passage, For every 9.1% increase in inter-pore diameter, the re-attachment point of the air flow decreases by an average of 28.2% and the convective heat transfer coefficient decreases by an average of 9.6%. When the other conditions are the same, the interstage hole width increases the re-attachment point and convection heat transfer The influence is small; the angle of inter-stage pore becomes larger so that the position of air reattachment point and the convective heat transfer coefficient decrease by 3.4% and 3.1% respectively on average.