METHOD OF CURTAIN COOLING OF LIQUID-PROPELLANT ROCKET ENGINE CHAMBER AND DEVICE FOR REALIZATION OF THIS METHOD (VERSIONS) Russian patent published in 1999 - IPC

FIELD: engine chamber wall cooling systems. SUBSTANCE: zone of free gas flows at rather low rates are formed in boundary layer by means of gas-dynamic planing step; continuous film of liquid coolant is formed within this zone and is brought to wall of chamber. Invention proposes four versions of cooling curtain which may be used in liquid-propellant rocket engines having various parameters. All belts of cooling curtain include such main members as circular collector with inlet holes which are used for distributing and twisting the flow of liquid coolant changing into outlet slot, gas-dynamic planing step and profiled wall of after-step space. According to two versions, slots are smooth and have different width and according to other two versions, outlet slot has small inclined blades, closed in one version and open in other version. EFFECT: concentration of liquid coolant in thin boundary layer of gases; enhanced efficiency of gas curtain; minimum and even zero losses of specific impulse of engine thrust. 6 cl, 15 dwg