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Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part 5: Analysis and design of stages D and EA conventional and a tandem bladed stage were designed for a comparative experimental evaluation in a 0.8 hub/tip ratio single-stage compressor. Based on a preliminary design study, a radially constant work input distribution was selected for the rotor designs. Velocity diagrams and blade leading and trailing edge angles selected for the conventional rotor and stator were used in the design of the tandem blading. The effects of axial velocity ratio and secondary flow on turning were included in the selection of blade leading and trailing edge angles. Design values of rotor tip velocity and stage pressure ratio were 757 ft/sec and 1.26, respectively.
Document ID
19730005052
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Brent, J. A. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Cheatham, J. G. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Clemmons, D. R. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 2, 2013
Publication Date
December 15, 1972
Subject Category
Propulsion Systems
Report/Patent Number
FR-5212
NASA-CR-121008
Accession Number
73N13779
Funding Number(s)
CONTRACT_GRANT: NAS3-11158
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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