METHOD FOR COMPENSATION OF FUEL PHYSICAL PROPERTIES DIFFERENCES IN UNIVERSAL GENERATOR-FREE LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2009 - IPC F02K9/42 

FIELD: engines and pumps.

SUBSTANCE: in method for compensation of differences in physical properties of fuel components based on matching of operation modes of universal liquid-propellant rocket engine supply units, according to invention for generator-free engine with separate turbine pump (TP) during its transfer from hydrogen to liquefied natural gas (LNG) (methane), at first fuel (LNG, methane) flow is increased to required value for provision of reliable cooling of chamber, after cooling prior to fuel supply to turbine of TP its total flow is divided into two parts, one of which is supplied to TP turbine, and the other one is discharged, at that after TP passing, fuel fission process is repeated, at that its one part is sent for combustion in combustion chamber, and the other is discharged or sent for further use. Discharged parts of fuel flow may be used as working fluid, for instance, for steering nozzles, for turbine of engine swinging system, for supercharging of tanks, repeatedly as working fluid of chamber fuel and/or propellant pump. Invention provides for operation of engine both on fuel components "oxygen+hydrogen" and also on fuel "oxygen+liquefied natural gas" (methane).

EFFECT: reduced cost of engine and expanded field of its application.

7 cl, 4 dwg