Simulation of Cryogenic Jet Injection, RCM 1
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2001
- Accession Number
- ADP012359
Entities
People
- J. Telaar
- R. Branam
- W. Mayer
Organizations
- Air Force Research Laboratory