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Combustion instability analysis and the effects of drop size on acoustic driving rocket flow
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moser, Marlow D. Harper, Brent Technical Monitor Ellison, L. Renea |
| Copyright Year | 2004 |
| Description | High frequency combustion instability, the most destructive kind, is generally solved on a per engine basis. The instability often is the result of compounding acoustic oscillations, usually from the propellant combustion itself. To counteract the instability the chamber geometry can be changed and/or the method of propellant injection can be altered. This experiment will alter the chamber dimensions slightly; using a cylindrical shape of constant diameter and the length will be varied from six to twelve inches in three-inch increments. The main flowfield will be the products of a high OF hydrogen/oxygen flow. The liquid fuel will be injected into this flowfield using a modulated injector. It will allow for varied droplet size, feed rate, spray pattern, and location for the mixture within the chamber. The response will be deduced from the chamber pressure oscillations. |
| File Size | 427056 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040075603 |
| Archival Resource Key | ark:/13960/t8nd0x926 |
| Language | English |
| Publisher Date | 2004-05-13 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Sound Waves Drop Size Propellant Combustion Combustion Stability Pressure Oscillations Rocket Flight Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
