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Low loss injector for liquid propellant rocket engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1986 |
| Description | A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine which includes a lox post terminating in a cylindrical barrel. Received within the barrel is a lox plug which is threaded in the lox post and includes an interchangeable lox metering sieve which meters the lox into an annular lox passage. A second annular gas passage is coaxial with the annular lox passage. A cylindrical sleeve surrounds the annular gas passage and includes an interchangeable gas metering seive having metering orifices through which a hot gas passes into the annular passage. The jets which emerge from the annular lox passage and annular gas passage intersect in a recessed area away from the combustion area. Thus, mixing and combustion stability are enhanced. |
| File Size | 737837 |
| Page Count | 9 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870004987 |
| Archival Resource Key | ark:/13960/t7pp4045j |
| Language | English |
| Publisher Date | 1986-11-11 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Injectors Combustion Stability Baffles Liquid Oxygen Liquid Rocket Propellants Rocket Engines Fuel Injection Combustion Chambers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
