Variation in Airflow Coefficient for Allison T56 Combustor Liners

摘要

It is shown that it is possible to have a circumferential turbine inlet temperature variation in excess of 90 C in a correctly assembled T56 Series III engine. A significant part of this variation is due to differences in airflow into the liner caused by the variations in airflow area associated with manufacturing tolerances. A simple technique is described that will enable matched sets of liners to be selected to build engines and thus avoid excessive temperature maldistributions. Preliminary experimental results are described. Keywords: Turboprop engines; Combustion chamber liners; Temperature distribution; Allison T56 engine, Australia. (EDC)