LIQUID-PROPELLANT ROCKET ENGINE

摘要

FIELD: rocketry and space engineering; upper stages and engine plants of launch vehicles and spacecraft. SUBSTANCE: engine has combustion with regenerative cooling passage. Regenerator heat exchanger is mounted at outlet of turbine of turbopump unit. Inlet and outlet of heat exchanger are connected with outlet of pump supplying one component of propellant and inlet of above-mentioned passage. Heat-transfer agent inlet and outlet of heat exchanger are connected with turbine outlet and combustion chamber inlet. EFFECT: enhanced efficiency; improved mass and dimensional characteristics. 2 cl, 1 dwg