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Energy Efficient Engine exhaust mixer model technology report addendum; phase 3 test programThe Phase 3 exhaust mixer test program was conducted to explore the trends established during previous Phases 1 and 2. Combinations of mixer design parameters were tested. Phase 3 testing showed that the best performance achievable within tailpipe length and diameter constraints is 2.55 percent better than an optimized separate flow base line. A reduced penetration design achieved about the same overall performance level at a substantially lower level of excess pressure loss but with a small reduction in mixing. To improve reliability of the data, the hot and cold flow thrust coefficient analysis used in Phases 1 and 2 was augmented by calculating percent mixing from traverse data. Relative change in percent mixing between configurations was determined from thrust and flow coefficient increments. The calculation procedure developed was found to be a useful tool in assessing mixer performance. Detailed flow field data were obtained to facilitate calibration of computer codes.
Document ID
19900019240
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Larkin, M. J.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Blatt, J. R.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1984
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.26:174799
PWA-5594-271-ADD
NASA-CR-174799
Report Number: NAS 1.26:174799
Report Number: PWA-5594-271-ADD
Report Number: NASA-CR-174799
Accession Number
90N28556
Funding Number(s)
CONTRACT_GRANT: NAS3-20646
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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