Transient and steady-state performance of a single turbojet combustor with four different fuel nozzles

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Summary: Acceleration and steady-state performance of a tubular combustor was evaluated at two simulated altitudes with four different fuel nozzles. Temperature response lag was observed with all the nozzles. Except for rich-limit blowout, the only combustion failures observed during acceleration were with a fuel nozzle that gave an interrupted flow delivery during the acceleration. This same nozzle, because of superior fuel atomization, gave the highest steady-state combustion efficiencies.
Collection: NASA Technical Reports Server (NTRS) Collection.
Note: Document ID: 19930088974.
Accession ID: 93R18264.
NACA-RM-E55H03a.
Terms of Use and Reproduction: No Copyright.

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