Loading...
Please wait, while we are loading the content...
Similar Documents
Experimental evaluation of the ignition process of carbon monoxide and oxygen in a rocket engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Linne, Diane L. |
| Copyright Year | 1996 |
| Description | Carbon monoxide and oxygen ignition boundaries were determined in a spark torch igniter as a function of propellant inlet temperatures. The oxygen temperature was varied from ambient to -258 F, and the carbon monoxide temperature was varied from ambient to -241 F. With the oxygen and carbon monoxide at -253 F and -219 F, respectively, they successfully ignited between mixture ratios of 2.42 and 3.10. Analysis of the results indicated that the lower ignition boundary was more sensitive to oxygen temperature than to carbon monoxide temperature. Another series of tests was performed in a small simulated rocket engine with oxygen at -197 F and carbon monoxide at -193 F. An oxygen/hydrogen flame was used to initiate combustion of the oxygen and carbon monoxide. Tests performed at the optimum operating mixture ratio of 0.55 obtained steady-state combustion in every test. |
| File Size | 920192 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960045922 |
| Archival Resource Key | ark:/13960/t0xq1xq5s |
| Language | English |
| Publisher Date | 1996-06-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Torches Igniters Oxygen Propellants Inlet Temperature Ignition Rocket Engines Combustion Carbon Monoxide Sparks Steady State Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
