Carbonaceous deposits can reduce heat flux in fuel-film-cooled kerosene rocket engines, but the deposition process at rocket conditions is poorly understood. Heat flux was measured in a 4.8 MPa (700 psia) fuel-film-cooled kerosene–hydrogen peroxide axisymmetric rocket combustor using 50 null point calorimeters and the Gauss–Newton algorithm with a constant Jacobian matrix. Carbon deposition caused a reduction in heat flux at axial positions furthest from the fuel-film injector, where deposits were later measured as thickest. Heat flux was reduced by a smaller amount in low-thermal-conductivity chamber liners when compared with high-thermal-conductivity copper liners. The roughness of the chamber-liner surface had little effect on quasi-steady-state heat flux but may have affected heat flux and carbon deposition during startup transients.

碳质沉积物可以减少燃料膜冷却的煤油火箭发动机中的热通量，但人们对火箭条件下的沉积过程了解甚少。热通量是在4.8 MPa（700 psia）的燃料膜冷却的煤油-过氧化氢轴对称火箭燃烧室中使用50个零点量热计和具有恒定雅可比矩阵的高斯-牛顿算法测量的。碳沉积导致距燃料膜喷射器最远的轴向位置处的热通量减少，此后沉积物的厚度被测量为最厚。与高导热铜衬里相比，低导热腔衬里的热通量减少了较少。腔室衬里表面的粗糙度对准稳态热通量几乎没有影响，但在启动瞬态过程中可能会影响热通量和碳沉积。