The question about the possibility of creation of rocket engine, work-ing on the principle of continuous detonation combustion according to the B.V. Vojtsechowski’ scheme is discussed. The detonation combustion is carried out in the annular area between two coaxial cylinders according to such scheme.
Calculation study of acoustic and vortex processes at interaction of jets of kerosene and oxygen with the combustion in chamber of LPRE on the basis of LES-model with a detailed calculation of dynamics of turbu-lent vortexes in the anisotropic range is presented. The results of the study allow to identify specific processes that lead to increased combustion effi-ciency in these engines.
The calculations of flows with burning of kerosene with oxygen in mixing element of gas generator in stationary ap-proximation using Reynolds averaged Navier-Stokes equa-tions are conducted. Picture of flow for regular geometry of gas generator at nominal mode of operation of engine is pre-sented. It’s shown influence of ledge at exit of end-to-end chambers in fire bottom.
In high-power LRE, the flame front is adjacent to edge between oxi-dizer and fuel, so that a high temperature of combustion products is real-ized in area of connection and a large heat flow from gas to edge is formed. On example of RD 191 engine preburner, a picture of flow with combustion in area behind edge is presented and a calculated study of factors that de-termine the temperature in injector body is conducted.
The principles of operation of liquid rocket engine on gaseous oxygen – kerosene, in which combustion is performed in the transverse detonation waves, continuously circulating in a circle in the annular combustion chamber.
Pin injectors were previously optimized on the combus-tion completeness in the combustion chamber of liquid rock-et engine of high thrust . These theoretical studies were completed – it’s found the structure of the pin injectors, which allows to reduce significantly pressure and to reduce temperature of walls. There is a good scalability of consid-ered injectors – the length of combustion is proportional to its radius. It is shown that the deviation from optimum propel-lant mixture ratio Km in pin injectors leads to considerable decrease in combustion completeness.
The optimization of pin injector elements on combustion completeness at use in the combustion chamber of LRE of large thrust is conducted by series of calculations. Their spe-cific advantages and disadvantages are shown. Calculations of steady three-dimensional turbulent mixing of oxidizer flow and fuel jets with combustion were conducted on base of Reynolds averaged Navier-Stokes equations and flamelet-model.