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Performance of an annual combustor designed for a low-cost turbojet engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Fear, J. S. |
| Copyright Year | 1973 |
| Description | Performance tests were conducted on a combustor designed for use in a low-cost turbojet engine. Low-cost features included the use of very inexpensive simplex fuel nozzles and combustor liners of perforated sheet material. Combustion efficiencies at the altitude-cruise and sea-level design points were approximately 94 and 96 percent, respectively. The combustor isothermal total-pressure loss was 8.8 percent at the altitude-cruise-condition diffuser-inlet Mach number of 0.335. The combustor-exit temperature pattern factor was less than 0.3 at the altitude-cruise, sea-level-cruise, and sea-level-static design conditions. The combustor-exit average radial temperature profiles at all conditions were in very good agreement with the design profile. The intense mixing required because of the very high combustor heat-release rate had an adverse effect on ignition capability at altitude windmilling design conditions. |
| File Size | 4557387 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730020186 |
| Archival Resource Key | ark:/13960/t7hq8q93t |
| Language | English |
| Publisher Date | 1973-08-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Engine Design Systems Analysis Product Development Aircraft Engines Cost Analysis Combustion Chambers Turbojet Engines 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 |
