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Detailed design of a quiet high flow fanA single stage fan was designed to demonstrate the noise abatement properties of near-sonic inlet flow and long-chord stator vanes for the reduction of both upstream and downstream propagated fan source noise. It is designed to produce a pressure ratio of 1.653:1 with an adiabatic efficiency of 83.9%. The fan has a 508 mm inlet diameter with a hub/tip ratio of 0.426 and a design tip speed of 533.4 m/sec. The design inlet specific flow rate is 219.71 kg/sec sq m and there are 10 tandem stator vanes with a combined aspect ratio of 0.54.
Document ID
19770012126
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Soltau, J. D. (Detroit Diesel Allison Indianapolis, IN, United States)
Orelup, M. J. (Detroit Diesel Allison Indianapolis, IN, United States)
Beguhn, A. A. (Detroit Diesel Allison Indianapolis, IN, United States)
Wiles, F. M. (Detroit Diesel Allison Indianapolis, IN, United States)
Anderson, M. J. (Detroit Diesel Allison Indianapolis, IN, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-135126
EDR-9071
Report Number: NASA-CR-135126
Report Number: EDR-9071
Accession Number
77N19070
Funding Number(s)
CONTRACT_GRANT: NAS3-19433
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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