FIELD: engines and pumps.
SUBSTANCE: proposed system comprises inner profiled shell with constant-thickness ribs that form cooling channels, profiled outer shell fitted on inner shell and secured thereto. Note here that additional lengthwise ribs are made on inner shell inner surface on the side of combustion chamber. Height and thickness of said additional ribs do not exceed thickness of the cooling channel bottom wall.
EFFECT: improved conditions of heat exchange between combustion products and coolant.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COOLING CIRCUIT OF LIQUID-PROPELLANT ENGINE CHAMBER | 2008 |
|
RU2410558C2 |
| COOLING CIRCUIT OF LIQUID-PROPELLANT ENGINE CHAMBER | 2008 |
|
RU2392478C1 |
| COOLING CIRCUIT OF LIQUID-PROPELLANT ENGINE CHAMBER | 2008 |
|
RU2391539C1 |
| METHOD OF COOLING HEAT-STRESSED SECTIONS OF LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER | 2008 |
|
RU2394168C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE CHAMBER | 2013 |
|
RU2511961C1 |
| LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER COOLING SYSTEM | 2013 |
|
RU2514863C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE CHAMBER | 2013 |
|
RU2511785C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE CHAMBER | 2013 |
|
RU2511942C1 |
| LIQUID PROPELLANT ROCKET ENGINE ANNULAR CHAMBER | 2008 |
|
RU2403425C2 |
| LIQUID-PROPELLANT ENGINE ANNULAR CHAMBER | 2008 |
|
RU2391540C1 |
