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Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part 1: Analysis and design of stages A, B, and CA conventional rotor and stator, two dual-airfoil tandem rotors, and one dual-airfoil tandem stator were designed. The two tandem rotors were each designed with different percentages of the overall lift produced by the front airfoil. Velocity diagrams and blade leading and trailing edge metal angles selected for the conventional rotor and stator blading were used in the design of the tandem blading. Rotor inlet hub/tip ratio was 0.8. Design values of rotor tip velocity and stage pressure ratio were 757 ft/sec and 1.30, respectively.
Document ID
19720019039
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)
Nilsen, A. W. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
August 6, 2013
Publication Date
June 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-120803
PWA-FR-4667-PT-1
Report Number: NASA-CR-120803
Report Number: PWA-FR-4667-PT-1
Accession Number
72N26689
Funding Number(s)
CONTRACT_GRANT: NAS3-11158
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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