FIELD: liquid-propellant rocket engines.
SUBSTANCE: proposed liquid-propellant rocket engine contains wall carrying load with great number of cooling channels to pass coolant. Each cooling channel is provided with surface to direct coolant flow arranged at angle to its axis which creates in additional velocity component in flow of coolant passing through cooling channel in axial direction. Method of manufacture of such member is described.
EFFECT: reduced lamination of coolant in cooling channels.
10 cl, 10 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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| LIQUID-PROPELLANT ENGINE ANNULAR CHAMBER | 2008 |
|
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| COOLING CIRCUIT OF LIQUID-PROPELLANT ENGINE CHAMBER | 2008 |
|
RU2391539C1 |
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|
RU2403424C2 |
