| Autor: |
Chad J. Eberhart, David M. Lineberry, Marlow D. Moser |
| Rok vydání: |
2010 |
| Předmět: |
|
| Zdroj: |
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. |
| DOI: |
10.2514/6.2010-6665 |
| Popis: |
A geometrically full-scale swirl injector element was subjected to cold flow testing to explore the influence of steady chamber pressure on spray characteristics and selfatomization at conditions that reflect real liquid rocket combustor conditions. Propellant simulant flow rate was held constant at 0.82 kg/s over a chamber pressure range of 0.95 MPa to 3.45 MPa. Imaging studies observed free cone spray angle to deviate from the theoretical value when conditioned with positive variation in chamber pressure. Additionally, sheet penetration length decreased as a function of chamber pressure conditions. Phase Doppler Particle Analyzer measurements resolved droplet velocity and diameter profiles through the spray envelope. Analysis showed mean velocities and diameters in the primary atomization region to behave inversely to chamber pressure. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
|
