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Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor
| Content Provider | University of North Texas |
|---|---|
| Author | Zettle, Eugene V. Mark, Herman |
| Organization | Lewis Flight Propulsion Laboratory |
| Description | The design principle of injecting liquid fuel at more than one axial station in an annual turbojet combustor was investigated. Fuel was injected into the combustor as much as 5 inches downstream of the primary fuel injectors. Many fuel-injection configurations were examined and the performance results are presented for 11 configurations that best demonstrate the trends in performance obtained. The performance investigations were made at a constant combustor-inlet pressure of 15 inches of mercury absolute and at air flows up to 70 percent higher than values typical of current design practice. At these higher air flows, staging the fuel introduction improved the combustion efficiency considerably over that obtained in the combustor when no fuel staging was employed. At air flows currently encountered in turbojet engines, fuel staging was of minor value. Radial temperature distribution seemed relatively unaffected by the location of fuel-injection stations. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc59600 |
| Language | English |
| Publisher Date | 2018-04-09 |
| Access Restriction | Open |
| Subject Keyword | aircraft combustors turbojet engines |
| Content Type | Text |
| Resource Type | Report |
