STAND FUEL SUPERSONIC combustor ramjet ENGINE

摘要

The utility model to create a workable stand under conditions exposing it to high air flow, to provide autoignition fuel mixture in the chamber and increase the reliability of its operation, to compensate for thermal deformation and simplify the construction of the rack. These technical results are achieved in that the flat oval tube is made Front airfoil oriented along the camera path and installed on the combustion chamber wall through the support rotatably. Wherein the fuel feed channels to the front and rear edges of the profile are separately formed, and the ends of the channels are plugged. Holes fuel nozzles arranged on the front edges and the side surfaces of the airfoil rack. The stand is attached to the wall of the pan to the camera path axis at a sweep angle χ. Where the discrete value of the sweep angle χ for a specific mode of operation of the engine is determined by a predetermined ratio. When running in a combustion chamber supplied with air and fuel in the rack. At supersonic airflow speeds at the temperature of the incoming air flow rack rises above the autoignition temperature of the fuel-air mixture. This leads to the ignition and combustion of the mixture. 1 bp 3 and ZP f-ly.