The object - Combined rocket engines with integrated in the combustion chamber fuel supply system. The purpose is to develop the scientific bases for the design of combined rocket engines with an integrated in the combustion chamber a fuel supply system with porous elements, to study the basic laws of the intracellular processes occurring, to determine the mechanisms of influence on them, including smooth, deep throttling, finding ways to increase their thrust, reducing the cost of using the apparatus, using mathematical and physical modeling methods, based on the fundamental laws of hydromechanics and the theory of similarity and physical planning of the experiment, using conventional methods of processing the results of measurements, comparative analysis of results of mathematical modeling results of field experiments and research combined rocket engines and components supply units of fuel. Scientific novelty, and the most significant results. For the first time, the problem of creating the scientific basis for the design of a combined rocket engine with integrated into the combustion chamber of a system of supply of fuel components based on porous rings, with the possibility of smooth deep throttling along the thrust, as a single functional structure, was formulated and solved. Schemes and method of throttling of a rocket stage of the combined rocket engine which will allow to carry out deep, smooth throttling on draft are developed. The effect of porosity of the porous rings in the composition of the pump, the depth of throttling of he combustion chamber of the engine, and the magnitude of the supply breakdown zone were etermined. The expediency of using the stability parameter for the estimation of the steady supply of fuel components in the chamber with the backpressure of the supply system, which is integrated into the combustion chamber of the combined rocket engines, formulated its physical content. The limits of complete evaporation of water in high-speed, high-temperature streams are determined, as well as the dependence that allows to determine its rational consumption in combined rocket motors for water use apparatus. The minimum values of absolute velocity and static gas pressure drop for the conditions of complete evaporation of the liquid in it have been experimentally determined. For the first time, the characteristics of hydro-responsive liquid and solid fuels were obtained, depending on the ratio of the fuel components ratio, which create the scientific and technical basis for the design of combined rocket engines with a fuel system integrated into the combustion chamber. The vibrations of the turbine pump body vibration and pressure pulsations at the outlet of the impellers of the fuel components delivery system with the blade frequency and its harmonics were experimentally established. It is proved that the use of pumps at the outlet of the porous rings in the impellers of the pump leads to a decrease in the vibrations of the housing and pressure pulsations. The use of porous elements in the radial dynamic seals of the turbo pump units for the supply of fuel components makes it possible to completely eliminate the leakage of the fluid in the calculation mode. The use of porous elements on the periphery of the pump components of the fuel components supply systems has increased the efficiency and pressure of the pumps. The dependences of the mass of the main elements of the combined rocket engines with integrated into the combustion chamber of the system of supply of fuel components from the scheme of the active stage, the pressure in the combustion chamber and its thrust, which allows to clarify and accelerate the process of harmonization of the parameters of the flying. The materials of the dissertation were used at the enterprises: JSC "MOTOR SICH" - the result of studies of porous brush seals, JSC "ON-STATE" - design of a liquid evaporator, and in the educational process of the Oles Honchar Dnipro National University. The areas of use are aviation and space technology and thermal power.
