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High-loading, 1800 ft/sec tip speed transonic compressor fan stage. 1: Aerodynamic and mechanical designA single stage fan with a tip speed of 1800 ft/sec (548.6m/sec) and hub/tip ratio of 0.5 was designed to produce a pressure ratio of 2.285:1 with an adiabatic efficiency of 84.0%. The design flow per inlet annulus area is 38.7 lbm/sq ft-sec (188.9KG/sqm-sec). Rotor blades have modified multiple-circular-arc and precompression airfoil sections. The stator vanes have multiple-circular-arc airfoil sections.
Document ID
19720023124
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Morris, A. L. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Halle, J. E. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Kennedy, E. E. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 2, 2013
Publication Date
September 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-120907
PWA-4534
Report Number: NASA-CR-120907
Report Number: PWA-4534
Accession Number
72N30774
Funding Number(s)
CONTRACT_GRANT: NAS3-13493
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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