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Simulated altitude performance of two annular combustors with continuous axial openings for admission of primary air

Author
Mark, Herman
Physical Description
1 electronic document
Additional Creators
Zettle, Eugene V
Online Version

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Summary
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated with two fuels, AN-F-32 and AN-F-58. Investigations were made with two single-annulus liners in a one-quarter sector of a 25 1/2-inch-diameter turbojet combustor. Altitude performance data for these combustors are compared with existing data for a production-model double-annulus combustor. Altitude operating limits and combustion efficiencies of both single-annulus combustors were considerably higher than those of the double-annulus combustor; combustion efficiencies were insensitive to changes in fuel-air ratio.
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19930086163.
Accession ID: 93R15453.
NACA-RM-E50E18a.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15431830