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Thermal analysis of cryogenic hydrogen liquid separator
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Congiardo, Jared F. |
| Editor | Fortier, Craig R. |
| Copyright Year | 2014 |
| Description | During launch for the new Space Launch System (SLS) liquid hydrogen is bleed through the engines during replenish, pre-press, and extended pre-press to condition the engines prior to launch. The predicted bleed flow rates are larger than for the shuttle program. A consequence of the increased flow rates is having liquif hydrogen in the vent system, which the facilities was never designed to handle. To remedy the problem a liquid separator is being designed in the system to accumulated the liquid propellant and protect the facility flare stack (which can only handle gas). The attached document is a presentation of the current thermalfluid analysis performed for the separator and will be presented at the Thermal and Fluid Analysis Workshop (NASA workshop) next week in Cleveland, Ohio. |
| File Size | 797487 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20140016866 |
| Archival Resource Key | ark:/13960/t4zh1n367 |
| Language | English |
| Publisher Date | 2014-08-04 |
| Access Restriction | Open |
| Subject Keyword | Liquid Separator Cryogenic Thermal Analysis Vents Liquid Rocket Propellants Cryogenics Flow Velocity Separators Liquid Hydrogen Spacecraft Launching Accumulations Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
