Simulation of Cryogenic Jet Injection, RCM 1

Understanding the complex environment of the rocket chamber involves good knowledge of the injection phenomena. Understanding the injection phenomena allows the rocket designer to employ time and cost saving modeling tools to design a higher performance rocket engine. The rocket engine performance is highly dependent on the injection processes within the chamber. This project looked at injection processes in the supercritical regime of the injected fluid, cryogenic nitrogen, in order to better understand realistic conditions in the rocket engines of today. The investigation considered test conditions from 4.0 to 6.0 MPa at two different injection velocities and temperatures. For the RCM-1-A and RCM-1-B cases, the target test conditions are 5 m/s injection velocity and 120 K injection temperature. RCM-1-A is at 4 MPa and RCM-1-B is at 6 MPa. Experimental data taken by Raman imaging and Shadowgraphy were compared to computational models for these various test conditions. The test data allows comparisons of density, length scales and jet spreading angles. The results validate the computational models and agree with classical theory. --Original contains color plates: All DTIC reproductions will be in black and white. Prepared in collaboration with German Aerospace Center (DLR), Space Propulsion Institute, Lampoldshausen. This article is from ADA402618 2nd International Workshop on Rocket Combustion Modeling: Atomization, Combustion and Heat Transfer held in Lampoldshausen, Germany on 25-27 Mar 2001