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Transient and steady-state performance of a single turbojet combustor with four different fuel nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1955 |
| Description | Acceleration and steady-state performance of a tubular combustor was evaluated at two simulated altitudes with four different fuel nozzles. Temperature response lag was observed with all the nozzles. Except for rich-limit blowout, the only combustion failures observed during acceleration were with a fuel nozzle that gave an interrupted flow delivery during the acceleration. This same nozzle, because of superior fuel atomization, gave the highest steady-state combustion efficiencies. |
| File Size | 7664410 |
| Page Count | 48 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088974 |
| Archival Resource Key | ark:/13960/t6wx2405n |
| Language | English |
| Publisher Date | 1955-10-21 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |