Abstract:Tungsten"s distinctive physical and chemical properties make it a highly suitable material for rocket applications. Chemical vapor deposition (CVD) is a promising technique for applying uniform tungsten coatings to complex-shaped components (e.g., rocket engine throat liner). This study adapts a previously established low-pressure CVD model for tungsten, enabling its application under atmospheric pressure conditions to deposit high-performance coatings on rocket engine throat liners. We investigate the influence of three distinct reactor configurations—a straight-tube inlet, an integrated gas distribution device, and a combination of a distribution device with a flow guide baffle—on the reactor"s flow dynamics, thermal field, species concentration, and deposition kinetics. Numerical and experimental results demonstrate that the configuration incorporating both a distribution device and a baffle eliminates vortices within the liner region by promoting radial gas diffusion, thereby significantly improving flow field uniformity. This optimized design not only improves the uniformity of the deposition rate on the throat insert, but also slightly enhances the utilization efficiency of tungsten hexafluoride. This work provides a theoretical foundation for designing CVD systems for highly uniform tungsten coatings and offers a practical solution for their engineering application.