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Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05
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Author and Affiliation:
Moore, R. D.(NASA Lewis Research Center, Cleveland, OH, United States);
Reid, L.(NASA Lewis Research Center, Cleveland, OH, United States)
Abstract: The overall and blade-element performances of a low-aspect-ratio transonic compressor stage are presented over the stable operating flow range for speeds from 50 to 100 percent of design. At design speed the rotor and stage achieved peak efficiencies of 0.876 and 0.840 at pressure ratios of 2.056 and 2.000, respectively. The stage stall margin at design speed was 10 percent.
Publication Date: Apr 01, 1980
Document ID:
19800012840
(Acquired Nov 14, 1995)
Accession Number: 80N21325
Subject Category: AIRCRAFT PROPULSION AND POWER
Report/Patent Number: NASA-TP-1659, E-138
Document Type: Technical Report
Publisher Information: Washington, United States
Contract/Grant/Task Num: RTOP 505-04
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Description: 103p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: LOW ASPECT RATIO; ROTOR AERODYNAMICS; STATOR BLADES; TRANSONIC COMPRESSORS; TURBOCOMPRESSORS; AXIAL FLOW; GRAPHS (CHARTS); PRESSURE DISTRIBUTION; RADIAL DISTRIBUTION; TABLES (DATA)
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