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Combustion chamber inlet manifold separates vapor from liquid
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1966 |
| Description | Circular manifold with tangential orifices at the inner circumference provides for the vapor constituent of a vaporized cryogenic propellant to enter a rocket combustion chamber before the liquid constituent. The vapor is separated from the liquid by centrifugal action and precedes it into the chamber through carefully positioned orifices. |
| File Size | 75053 |
| Page Count | 1 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19660000052 |
| Archival Resource Key | ark:/13960/t3518r58r |
| Language | English |
| Publisher Date | 1966-02-01 |
| Access Restriction | Open |
| Subject Keyword | 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 |
