GLTRS--Glenn
TITLE AND SUBTITLE:
Flutter Analysis of a Transonic Fan

AUTHOR(S):
R. Srivastava, M.A. Bakhle, T.G. Keith, Jr., and G.L. Stefko

REPORT DATE:
September 2002

FUNDING NUMBERS:
WU-781-30-11-00

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-13511

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-2002-211818

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. Portions of this material were presented at the meeting. R. Srivastava, M.A. Bakhle, and T.G. Keith, Jr., University of Toledo, Toledo, Ohio; and G.L. Stefko, NASA Glenn Research Center. R. Srivastava and M.A. Bakhle, NASA Resident Research Associates at Glenn Research Center. Responsible person, R. Srivastava, organization code 5930, 216-433-6045.

ABSTRACT:
This paper describes the calculation of flutter stability characteristics for a transonic forward swept fan configuration using a viscous aeroelastic analysis program. Unsteady Navier-Stokes equations are solved on a dynamically deforming, body fitted, grid to obtain the aeroelastic characteristics using the energy exchange method. The non-zero inter-blade phase angle is modeled using phase-lagged boundary conditions. Results obtained show good correlation with measurements. It is found that the location of shock and variation of shock strength strongly influenced stability. Also, outboard stations primarily contributed to stability characteristics. Results demonstrate that changes in blade shape impact the calculated aerodynamic damping, indicating importance of using accurate blade operating shape under centrifugal and steady aerodynamic loading for flutter prediction. It was found that the calculated aerodynamic damping was relatively insensitive to variation in natural frequency.

SUBJECT TERMS:
Aeroelasticity; Turbomachine; Fan; Viscous; Numerical

NUMBER OF PAGES:
14

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