NASA NTRS · 19750003900
Effect of swirling flow on augmentor performance
Abstract
A test program was conducted with an augmentor which employed swirling flow as a means of promoting rapid flame propagation. The program evaluated the effect of augmentor length, swirl intensity, fuel zoning and Mach number on augmentor performance. Combustion efficiencies near 100% were demonstrated over most of the operating range which extended from an equivalence ratio of 0.2 to over 1.0. The tests were conducted at an inlet temperature of 649 C (1200 F) and at a pressure of 2 atmospheres. The augmentor total pressure losses were typical of current state of the art augmentors.
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Clements, T. R.. 1974-11-01. Effect of swirling flow on augmentor performance. https://ntrs.nasa.gov/citations/19750003900
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