LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2008 - IPC F02K9/42 

FIELD: aircraft industry; rocketry.

SUBSTANCE: invention relates to design of liquid-propellant rocket engines. Proposed liquid-propellant rocket engine without afterburning of generator gas contains regenerative cooling chamber 1, turbopump set 2 with gas generator 3 to drive turbine 4, two flow rate controls and two nozzles 9, 10 installed in pressure main lines 11, 12 of pumps of turbopump set 2. Sensing elements of spools 5, 6 of controls communicate through pipelines with inputs of nozzles 9, 10 and their minimum sections. According to invention servo-actuate restrictor 14 of control, playing the part of thrust control, installed in feed main line 12 of one of propellant components into gas generator 3. Restricting element of servo-actuated restrictor 14 communicates through pipeline 21 with pressure main line 12 of pump of said component after nozzle 10, and pipeline 22 delivering second component into gas generator 3 is connected with pressure main line 11 of pump of said component after servo-actuated restrictor 13 of control playing the part of propellant components flow rate ratio control.

EFFECT: improved energy-mass ratios of engine, provision of constant propellant components flow rate through engine and thrust irrespective of ratio of components passing through engine.

1 dwg