GLTRS--Glenn
TITLE AND SUBTITLE:
Calculation and Correlation of the Unsteady Flowfield in a High Pressure Turbine

AUTHOR(S):
Milind A. Bakhle, Jong S. Liu, Josef Panovsky, Theo G. Keith, Jr., and Oral Mehmed

REPORT DATE:
March 2002

FUNDING NUMBERS:
WU-910-30-11-00

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-13242

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-2002-211475

SUPPLEMENTARY NOTES:
Prepared for the Turbo Expo 2002 sponsored by the American Society of Mechanical Engineers and the International Gas Turbine Institute, Amsterdam, The Netherlands, June 3-6, 2002. Milind A. Bakhle and Theo G. Keith, Jr., University of Toledo, Toledo, Ohio; Jong S. Liu and Josef Panovsky, Honeywell Engines, Systems, & Services, Pheonix, Arizona; Oral Mehmed, NASA Glenn Research Center. Responsible person, Milind A. Bakhle, organization code 5930, 216-433-6037.

ABSTRACT:
Forced vibrations in turbomachinery components can cause blades to crack or fail due to high-cycle fatigue. Such forced response problems will become more pronounced in newer engines with higher pressure ratios and smaller axial gap between blade rows. An accurate numerical prediction of the unsteady aerodynamics phenomena that cause resonant forced vibrations is increasingly important to designers. Validation of the computational fluid dynamics (CFD) codes used to model the unsteady aerodynamic excitations is necessary before these codes can be used with confidence. Recently published benchmark data, including unsteady pressures and vibratory strains, for a high-pressure turbine stage makes such code validation possible. In the present work, a three dimensional, unsteady, multi blade-row, Reynolds-Averaged Navier Stokes code is applied to a turbine stage that was recently tested in a short duration test facility. Two configurations with three operating conditions corresponding to modes 2, 3, and 4 crossings on the Campbell diagram are analyzed. Unsteady pressures on the rotor surface are compared with data.

SUBJECT TERMS:
Forced response; Turbine; Navier-Stokes; Unsteady flow

NUMBER OF PAGES:
20

PDF AVAILABLE FROM URL:
2002/TM-2002-211475.pdf
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