This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Advanced High Temperature Combustor Research for Small Gas Turbine Engines
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1968 by SAE International in United States
Annotation ability available
Event: Mid-Year Meeting
Design studies and an experimental test program have been conducted to provide basic technology and preliminary flightweight designs for a small (2 lb/sec total engine airflow) high temperature rise combustor with a 3000 F exit temperature, as a first step towards demonstration in a research engine. Tests were conducted to evaluate the combustor design parameters developed in the initial design study phase of the program pertaining to liner cooling techniques, fuel introduction, and primary zone performance. The preliminary designs optimize the technology developed in this program and comprise both annular and can end-mounted combustor configurations incorporating an annular vaporizer fuel introduction system and transpiration cooled liners.
|Technical Paper||Afterburners and Variable Nozzles|
|Technical Paper||Fuel Properties and Jet-Engine Combustor Performance|
|Technical Paper||A METHOD FOR CORRECTING EXISTING JET ENGINE PERFORMANCE|
CitationAndersen, R. and Wagner, D., "Advanced High Temperature Combustor Research for Small Gas Turbine Engines," SAE Technical Paper 680446, 1968, https://doi.org/10.4271/680446.
- Gaydon Wolfhard “Flames-Their Structure, Radiation, and Temperature.” Chapman and Hall, Ltd.
- Lombardo Lauziere Kump “Design and Fabrication Aspects of Transpiration Cooled Turbine Blades for 2500 F Turbine Operation.” SAE Paper 820A Jan. 13 1964
- Lombardo Moskowitz Schnure “Experimental Results of a Transpiration Cooled Turbine Operated in an Engine for 150 hr at 2500 F Turbine Inlet Temperature.” ASME Paper 67-GT-29 March 5 1967