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Effect of swirling flow on augmentor performanceA 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.
Document ID
19750003900
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Clements, T. R. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1974
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-134639
FR-6534
Report Number: NASA-CR-134639
Report Number: FR-6534
Accession Number
75N11972
Funding Number(s)
CONTRACT_GRANT: NAS3-17348
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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