FIELD: liquid-propellant rocket engines. SUBSTANCE: nozzle has outer and inner envelopes forming cooling duct which is communicated with supply collector, longitudinal and U-shaped fins located inside cooling duct. Circular radial bore is provided between longitudinal and U-shaped fins under collector for mixing the jets. Width of this bore is no less than 0.4 of width of slot between longitudinal fins before U-shaped fins and no more than width of slot between U-shaped fins at nozzle exit section. EFFECT: enhanced reliability due to reduced irregularity of distribution of coolant among of cooling duct. 3 cl, 6 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| RING CHAMBER OF LIQUID-PROPELLANT ROCKET ENGINE | 1999 |
|
RU2151318C1 |
| LIQUID-PROPELLANT JET ENGINE CHAMBER NOZZLE | 2008 |
|
RU2366825C1 |
| CHAMBER OF LIQUID-PRPELLANT ROCKET ENGINE | 1999 |
|
RU2171388C2 |
| TUBE-IN-TUBE HEAT EXCHANGER | 2001 |
|
RU2204773C2 |
| LIQUID-PROPELLANT THRUST CHAMBER NOZZLE | 1989 |
|
RU2095609C1 |
| LIQUID-PROPELLANT ROCKET ENGINE CHAMBER | 2022 |
|
RU2774754C1 |
| LIQUID-PROPELLANT ROCKET ENGINE AND METHOD OF COOLING ITS CHAMBER HIGH-HEAT AREAS | 2011 |
|
RU2472962C2 |
| METHOD OF CURTAIN COOLING OF LIQUID-PROPELLANT ROCKET ENGINE CHAMBER AND DEVICE FOR REALIZATION OF THIS METHOD (VERSIONS) | 1998 |
|
RU2135809C1 |
| INJECTOR ASSEMBLY OF LIQUID-PROPELLANT ROCKET ENGINE | 2000 |
|
RU2205289C2 |
| LIQUID-PROPELLANT ENGINE ANNULAR CHAMBER | 2008 |
|
RU2391541C1 |
