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Method for determining optimum injector inlet geometry
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 2015 |
| Description | A method for determining the optimum inlet geometry of a liquid rocket engine swirl injector includes obtaining a throttleable level phase value, volume flow rate, chamber pressure, liquid propellant density, inlet injector pressure, desired target spray angle and desired target optimum delta pressure value between an inlet and a chamber for a plurality of engine stages. The method calculates the tangential inlet area for each throttleable stage. The method also uses correlation between the tangential inlet areas and delta pressure values to calculate the spring displacement and variable inlet geometry of a liquid rocket engine swirl injector. |
| File Size | 945566 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150003443 |
| Archival Resource Key | ark:/13960/t47q40f4k |
| Language | English |
| Publisher Date | 2015-01-27 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Flow Velocity Patents Sprayers Injectors Liquid Propellant Rocket Engines Inlet Pressure Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
