GLTRS--Glenn
TITLE AND SUBTITLE:
Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

AUTHOR(S):
Dale E. Van Zante, Wai-Ming To, and Jen-Ping Chen

REPORT DATE:
March 2003

FUNDING NUMBERS:
WBS-22-714-03-54

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-13781

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-2003-212180
GT-2002-30575

SUPPLEMENTARY NOTES:
Prepared for the Turbo Expo 2002 cosponsored by the American Society of Mechanical Engineers and the International Gas Turbine Institute, Amsterdam, The Netherlands, June 3-6, 2002. Dale E. Van Zante, NASA Glenn Research Center; Wai-Ming To, AP Solutions, Inc., Cleveland, Ohio 44135; and Jen-Ping Chen, Mississippi State University, Mississippi State University 39762. Responsible person, Dale E. Van Zante, organization code 5810, 216-433-3640.

ABSTRACT:
Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect on the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

SUBJECT TERMS:
Machines; Compressing; Air; Fluids

NUMBER OF PAGES:
18

PDF AVAILABLE FROM URL:
2003/TM-2003-212180.pdf ( 964 KB )
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