FIELD: engines.
SUBSTANCE: invention relates to rocket engine combustion chambers. Injector for mixing two fuel components upstream of a combustion chamber, comprising at least one injection element (14) with a tricoaxial structure installed between two plates (12, 13) which between them delimit space (65); and coaxial ducts including internal coaxial duct (23) and external coaxial duct (24) that are supplied in parallel with same fuel component, for example via space (65).
EFFECT: higher quality of mixing fuel components.
18 cl, 8 dwg
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