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Design and evaluation of high performance rocket engine injectors for use with hydrocarbon fuels
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Pavli, A. J. |
| Copyright Year | 1979 |
| Description | The feasibility of using a heavy hydrocarbon fuel as a rocket propellant is examined. A method of predicting performance of a heavy hydrocarbon in terms of vaporization effectiveness is described and compared to other fuels and to experimental test results. Experiments were done at a chamber pressure of 4137 KN/sq M (600 psia) with RP-1, JP-10, and liquefied natural gas as fuels, and liquid oxygen as the oxidizer. Combustion length effects were explored over a range of 21.6 cm (8 1/2 in) to 55.9 cm (22 in). Four injector types were tested, each over a range of mixture ratios. Further configuration modifications were obtained by reaming each injector several times to provide test data over a range of injector pressure drop. |
| File Size | 2190355 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800004908 |
| Archival Resource Key | ark:/13960/t8kd6q30q |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Vaporizing Injectors Propulsion System Performance Rocket Propellants Liquid Oxygen Hydrocarbon Fuels Performance Prediction Combustion Efficiency Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
