LIQUID-PROPELLANT ENGINE Russian patent published in 2020 - IPC F02K9/46 F02K9/48 

FIELD: rocket construction.

SUBSTANCE: invention relates to rocket science and can be used in liquid-propellant rocket engines (LPRE), nuclear rocket engines (NRE) and power plants for various purposes. Liquid-propellant rocket engine consists of chamber 1, turbo-pump unit 2 (TPU), booster pumping units 3 (BPU1) and 4 (BPU2) installed on line of each of fuel components. Booster pump units are driven by electric drives 5 and 6. Electric drive is understood to mean set of the electric motor regulated by frequency of rotation, and electric control system of it. Electrical control system of electric motor can include both in composition of liquid-propellant engine and aircraft. Power supply system is a part of aircraft. To provide for recharging of power supply system along high pressure line of one or both components of fuel turbo-electric generator/turbo-electric generators 9 and 10 are installed, driven by hydraulic turbines. In order to ensure separation of pumps BPU1 and BPU2 with pumps of TPU, for example, for prelaunch cooling, between the outputs from BPU1 and BPU2 and the inputs of the corresponding pumps of TPU, valves 7 and 8, respectively, are installed.

EFFECT: invention provides for simplification of design, increased reliability due to minimization of number of units in engine, increasing the LPRE control range due to provision of optimum parameters at the booster pump units output - inputs to the TPU pumps irrespective of the TPU operation mode in the engine.

8 cl, 6 dwg