A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine which includes a lox post terminating in a cylindrical barrel. A lox plug received within the barrel which is threaded in the lox post and includes an interchangeable lox metering sieve which meters the lox into an annular lox passage. A second annular gas passage is coaxial with the annular lox passage. A cylindrical sieve surrounds the annular gas passage and includes an interchangeable gas metering sieve with metering orifices through which a hot gas passes into the annular passage. The jets which emerge from the annular lox passage and annular gas passage intersect at a point which is recessed away from the combustion area. The procedure enhances mixing and combustion stability.
Low Loss Injector for Liquid Propellant Rocket Engines
1985
16 pages
Report
No indication
English
Low loss injector for liquid propellant rocket engines
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