雾化燃料在超声速气流中横向喷射混合的数值模拟

本文用双流体模型对液态雾化燃料在直简形燃烧室中横向喷射问题进行了数值研究，气相用二阶迎负ＴＶＤ格式求解三维全Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，液相用二阶预估、校正ＮＮＤ格式求解三维Ｅｕｌｅｒ方程。描述相间相互作用的常微分方程用预估、校正的二阶Ｒｕｎｇｅ－Ｋｕｔｔａ法求解。分别考察了喷口处气相压力、相间速度滑移、液滴直径和燃烧室入口处预置的超声速流向涡对雾化燃料混合效果的影响。结果表明：气相较液相的扩

Numerical Simulation of Atomized Fuels Transversely Injected into a Supersonic Flow

Two fluid model was used to study the atomized fuels transversely injected into a superso nic flow. A second order upwind TVD scheme was used to solve the 3D fully N S equations. A second order predictor corrector NND scheme was used to solve the Eulerian equations. The ordinary differential equations describing interaction terms between the gas and liquid phase were solved by the predictor corrector Runge Kutta approach. The influences were numerically detected on fuel air mixing of gas injection pressure, velocity slip between the gas and droplets, liquid droplet size and supersonic stream wise vortex at the inlet of combustor. The results indicate that the gas is rapider in diffusion than the liquid. Good mixing can be achieved for droplets with small size. Slip velocity of the droplets at the injector can also contribute to the fuel mixing. The supersonic stream wise vortex can enhance the mixing of gas phase but make little contribution to droplets mixing.