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Rocket engine injectorhead with flashback barrier
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 2012 |
| Description | Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation. |
| File Size | 2340591 |
| Page Count | 25 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20120012505 |
| Archival Resource Key | ark:/13960/t9576dq4t |
| Language | English |
| Publisher Date | 2012-07-31 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Patents Spark Ignition Injectors Inventions Rocket Engines Porosity Combustion Chambers Flame Propagation Sparks Propellant Combustion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
