固液发动机实验燃烧器的气固耦合传热计算

Flow/structure coupled heat transfer calculation for a diffusion flame experimental burner

关键词:  固液火箭发动机  退移速率+  耦合  传热

Key words:  Hybrid rocket motor  Regression rate+  Coupling  Heat transfer

摘要:

针对固液火箭发动机中复杂的燃烧、传热过程,在FLUENT软件的平台上,采用气固耦合传热计算的方法模拟了二维扩散燃烧实验器中的温度、组分分布,并利用动网格方法模拟了固体燃面的不规则热解退移。稳态流场计算的结果和燃面动态退移情况都验证了扩散火焰距燃面的距离和燃面上方主流流速是影响退移速率的主要因素。此方法可以较好地模拟固液火箭发动机中复杂的非定常传热和燃面退移过程,较准确地预示固液发动机的内弹道性能。

Abstract:

In order to understand the complex combustion and heat transfer in hybrid rocket motor,temperature field and gas component distribution were calculated in a two-dimensional experimental burner by using the flow/structure coupled heat transfer method based on the FLUENT software.The irregular regression rate of the burning surface was simulated by using dynamic grid.Results indicate that both the distance between diffusion flame and the solid surface and velocity of gas play important role for the regression rate.This method can be used to simulate the complex process of unsteady heat transfer and fuel regression in the hybrid rocket motor.Also,it can predict the inner ballistic performance of hybrid rocket motor.