FIELD: liquid jet engines. SUBSTANCE: chamber has outer shell 3, fire shell 1 and turbulizing projections 4. Ш - shaped inserts 2 are interposed between the shells. The inserts are rigidly connected with shells 1,3. The turbulizing projections are made of a wire 1-0.2 mm in diameter. The wire is soldered to the cooled surface of fire shell 1 to be lateral with respect to the passageways . Additionally, lateral turbulizing projection 5 are made outer vertical wall and shelf surfaces of Ш - shaped . Long-wise step between projections 5 on the wall and shelves is given, the bushings being in one plane, The projections are at the same level. EFFECT: improved design. 3 dwg
Title | Year | Author | Number |
---|---|---|---|
METHOD FOR MANUFACTURING REGENERATIVE COOLING PATH FOR LIQUID-FUEL ROCKET ENGINE CHAMBER | 2012 |
|
RU2516723C2 |
REGENERATIVE COOLING PATH FOR LIQUID-FUEL ROCKET ENGINE CHAMBER | 2012 |
|
RU2516678C2 |
LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER | 2012 |
|
RU2517949C2 |
LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER NOZZLE | 2012 |
|
RU2515576C2 |
HEAT-BEAT STRUCTURE COOLING CIRCUIT | 2012 |
|
RU2513059C2 |
LIQUID-PROPELLANT ENGINE CHAMBER | 2018 |
|
RU2720596C1 |
INJECTOR ASSEMBLY OF LIQUID-PROPELLANT ROCKET ENGINE AND CHAMBER WITH SUCH INJECTOR ASSEMBLY | 2000 |
|
RU2205973C2 |
HEAT-EXCHANGER | 1993 |
|
RU2054614C1 |
LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER | 2015 |
|
RU2614902C2 |
LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER COOLING SYSTEM | 2013 |
|
RU2514863C1 |
Authors
Dates
1996-06-10—Published
1992-07-21—Filed