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Preliminary investigation of the performance of a single tubular combustor at pressure up to 12 atmospheres
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1954 |
| Description | The effects of combustor operation at conditions representative of those encountered in high pressure-ratio turbojet engines or at high flight speeds on carbon deposition, exhaust smoke, and combustion efficiency were studied in a single tubular combustor. Carbon deposition and smoke formation tests were conducted over a range of combustor-inlet pressures from 33 to 173 pounds per square inch absolute and combustor reference velocities from 78 to 143 feet per second. Combustion efficiency tests were conducted over a range of pressures from 58 to 117 pounds per square inch absolute and velocities from 89 to 172 feet per second. |
| File Size | 1153060 |
| Page Count | 29 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088003 |
| Archival Resource Key | ark:/13960/t5bc8c775 |
| Language | English |
| Publisher Date | 1954-01-28 |
| Access Restriction | Open |
| Subject Keyword | Engines, Turbojet - Combustion Chambers - Allison J-33 Exhaust Gases Flow OF Gases - Velocity Engines, Turbojet - Combustion Fuels, Jet - Carbonization Fuels - Jp4 Engines, Turbojet - Pressure Engines, Jet - Carbon Deposits 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 |
