Combustor development for automotive gas turbinesThe development of a combustion system for the AGT 100 automotive gas turbine engine is described. A maximum turbine inlet temperature of 1288 C is reached during the regenerative cycle, and air up to 1024 C is supplied to the combustor inlet. A premix/prevaporization ceramic combustor employing variable geometry to control burning zone temperature was developed and tested. Tests on both metal and ceramic combustors showed that emissions were a function of burner inlet temperature (BIT). At 999 C BIT, NO(x) emissions were two orders of magnitude below program goals, and at the same temperature but at a different variable geometry position, the CO was 30 times below program goal. Tests to evaluate the durability of the ceramic materials showed no failures during steady-state operation; however, some cracks developed in the dome during extended transient operation.
Document ID
19820051527
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ross, P. T. (General Motors Corp. Indianapolis, IN, United States)
Williams, J. R. (General Motors Corp. Detroit Diesel Allison Div., Indianapolis, IN, United States)
Anderson, D. N. (NASA Lewis Research Center Cleveland, OH, United States)