Loading...
Please wait, while we are loading the content...
Similar Documents
Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine
| Content Provider | University of North Texas |
|---|---|
| Author | Heidmann, M. F. Baker, Louis Jr. |
| Organization | Lewis Flight Propulsion Laboratory |
| Description | Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydrogen injection, and oxygen atomization by two impinging jets with variations in hydrogen injection. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc64263 |
| Language | English |
| Publisher Date | 2018-03-26 |
| Access Restriction | Open |
| Subject Keyword | aircraft combustors hydrogen-oxygen injections aircraft power |
| Content Type | Text |
| Resource Type | Report |