The Influence of Thrust Chamber Structure Parameters on Regenerative Cooling Effect with Hydrogen Peroxide as Coolant in Liquid Rocket Engines

Liquid rocket engines with hydrogen peroxide and kerosene have the advantages of high density specific impulse, reliability, no ignition system. At present, cooling problem engines, especially regenerative cooling, has been little explored. In this study, a realizable k-epsilon turbulence model, discrete phase eddy dissipation concept 10-step 10-component reaction mechanism oxygen are used. The increased rib height channel causes inner wall temperature engine increases, average coolant outlet decreases slightly, pressure decreases. overall as width increases. However, in nozzle throat area, decreases, drop A decrease thickness results significant small increase temperature. These findings contribute to further development can guide design its process.