NASA NTRS · 19830035445
Small gas turbine combustor study - Combustor liner evaluation
Abstract
A reverse flow combustor liner constructed of Lamilloy (a multilaminate transpiration type material) is compared both analytically and experimentally with a conventional splash film-cooled design with the same combustor configuration. Comparison of selected critical combustor panels indicated that it was possible to maintain the liner temperature similar between the two configurations using 50 percent less coolant for the Lamilloy as compared with the reference film-cooled combustor. Additional benefits indicated improvement in outlet temperature distribution and NOx emission level.
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Norgren, C. T., Riddlebaugh, S. M.. 1983-01-01. Small gas turbine combustor study - Combustor liner evaluation. https://ntrs.nasa.gov/citations/19830035445
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