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Advanced High Temperature Combustor Research for Small Gas Turbine Engines
Annotation ability available
Sector:
Event:
Mid-Year Meeting
Language:
English
Abstract
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.
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Topic
Citation
Andersen, 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.Also In
References
- 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