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Title: Component testing of a ground based gas turbine steam cooled rich-burn primary zone combustor for emissions control of nitrogenous fuels

Technical Report ·
OSTI ID:5125390

This effort summarizes the work performed on a steam-cooled, rich-burn primary zone, variable geometry combustor designed for combustion of nitrogenous fuels such as heavy oils or synthetic crude oils. The steam cooling was employed to determine its feasibility and assess its usefulness as part of a ground based gas turbine bottoming cycle. Variable combustor geometry was employed to demonstrate its ability to control primary and secondary zone equivalence ratios and overall pressure drop. Both concepts proved to be highly successful in achieving their desired objectives. The steam cooling reduced peak liner temperatures to less than 800 K. This low temperature offers the potential of both long life and reduced use of strategic materials for liner fabrication. Three degrees of variable geometry were successfully employed to control air flow distribution within the combustor. A variable blade angle axial flow air swirler was used to control primary zone air flow, while the secondary and tertiary zone air flows were controlled by rotating bands which regulated air flow to the secondary zone quench holes and the dilutions holes, respectively. 7 refs., 7 figs., 1 tab.

Research Organization:
National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
DOE Contract Number:
AI21-77ET13111
OSTI ID:
5125390
Report Number(s):
DOE/NASA/13111-16; NASA-TM-88873; ON: DE87002082
Resource Relation:
Other Information: Portions of this document are illegible in microfiche products. Original copy available until stock is exhausted
Country of Publication:
United States
Language:
English