LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: rocketry. SUBSTANCE: liquid-propellant rocket engine includes two chambers secured on frame, turbo-pump unit secured to frame and provided with turbine, oxidizer and fuel pumps, pipe lines feeding oxidizer and fuel to gas generator and engine chambers. Sectional frame includes at least two sections which are symmetrical in mirror image. This frame is provided with supports for taking up forces from engine and pivots for securing the frame to rocket body. Pivots and supports are located in planes perpendicular relative to longitudinal axis of engine. Plane of position of pivots is located between plane of position of supports and rocket body. Engine is provided with forked bent pipe line feeding the high- temperature oxidizing gas whose single end section is connected with turbine outlet. Two other elbows are connected with respective chambers through bellows expansion joints which are used as swinging units of chambers. These elbows are secured to two above-mentioned sections. Each pipe line feeding the fuel to chambers is provided with two bellows expansion joints. EFFECT: possibility of using rocket engine space; facilitated procedure of assembly of engine; reduced axial dimensions of engine and launch vehicle mass. 9 cl, 5 dwg