FIELD: astronautics.
SUBSTANCE: invention relates to rocket engines. Liquid rocket engine chamber consisting of impermeable outer wall and impermeable inner wall, combustion chamber and nozzle, according to the invention, a porous insert is arranged between the outer wall and the inner wall, and the chamber is a monolithic structure made by an additive method. Besides, porous insert occupies entire volume between outer wall and inner wall of liquid-propellant engine chamber, as well as porous insert can be located between outer wall and inner wall of this chamber only in area of nozzle critical section, also porous insert can be located between outer wall and inner wall of this chamber only in area of combustion chamber and part of nozzle.
EFFECT: invention provides higher efficiency of cooling, rigidity of design and manufacturability.
4 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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