An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.
Liquid Propellant Tracing Impingement Injector
2005-03-01
Miscellaneous
No indication
English
Propellant Injector Influence on Liquid-Propellant Rocket Engine Instability
Online Contents | 2015
|Liquid-Propellant Rocket Engine Injector Dynamics
AIAA | 1998
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NTIS | 1979
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