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Study of controlled diffusion stator bladingTests were conducted on a high tip speed, highly loaded front compressor stage having low aspect ratio rotor and stator airfoils. The stator airfoils were designed by the controlled diffusion procedure recently developed by P&WA for designing transonic cascade airfoils. The rotor blades consisted of multiple-circular-arc airfoil sections. The stage had a tip speed of 442 m/sec (1450 ft/sec), a hub/tip ratio of 0.597, a rotor aspect ratio of 1.3, and a stator aspect ratio of 1.45. At design speed the rotor-stator stage achieved an adiabatic efficiency of 89.1% at design flow and pressure ratio. Surge margin was 14%. The stage efficiency exceeded the design goal by 0.6 percentage points. The rotor efficiency was 92.4%, exceeding design by 0.3 percentage points. The controlled diffusion stator demonstrated a lower minimum loss over the multiple-circular-arc stator from the root to 70 percent span. A surge diffusion factor of 0.72 was reached at both the rotor tip and the stator root. The NAS3-22008 program demonstrated its intent: high efficiency and loading levels with low aspect ratio blades and the controlled diffusion stator in the unfavorable front stage environment.
Document ID
19850009749
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Behlke, R. F. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Brooky, J. D. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Canal, E. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.26:167995
NASA-CR-167995
PWA-5698-77
Accession Number
85N18058
Funding Number(s)
CONTRACT_GRANT: NAS3-22008
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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