Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

TITLE AND SUBTITLE:
Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

AUTHOR(S):
P.W. Giel, G.J. Van Fossen, R.J. Boyle, D.R. Thurman and K.C. Civinskas

REPORT DATE:
August 1999

FUNDING NUMBERS:
WU-523-26-13-00
1L161102AH45
NAS3-98008

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
NASA Glenn Research Center
Cleveland, Ohio 44135-3191
and
U.S. Army Research Laboratory
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-11775

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001
and
U.S. Army Research Laboratory
Adelphi, Maryland 20783-1145

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-1999-209296
ARL-TR-2029

SUPPLEMENTARY NOTES:
Prepared for the 1999 International Gas Turbine and Aeroengine Congress cosponsored by the American Society of Mechanical Engineers and the International Gas Turbine Institute, Indianapolis, Indiana, June 7-10, 1999. P.W. Giel, Dynacs Engineering Company, Inc., Brook Park, Ohio; (work funded under NASA Contract NAS3-98008); G.J. VanFossen and R.J. Boyle, NASA Glenn Research Center; D.R. Thurman and R.C. Civinskas, U.S. Army Research Laboratory, NASA Glenn Research Center. Responsible person, R.J. Boyle, organization code 5820, (216) 433-5889.

ABSTRACT:
Detailed heat transfer measurements and predictions are given for a turbine rotor with 136° of turning and an axial chord of 12.7 cm. Data were obtained for inlet Reynolds numbers of 0.5 and 1.0¥106, for isentropic exit Mach numbers of 1.0 and 1.3, and for inlet turbulence intensities of 0.25% and 7.0%. Measurements were made in a linear cascade having a highly three-dimensional flow field resulting from thick inlet boundary layers. The purpose of the work is to provide benchmark quality data for three-dimensional CFD code and model verification. Data were obtained by a steady-state technique using a heated, isothermal blade. Heat fluxes were determined from a calibrated resistance layer in conjunction with a surface temperature measured by calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, shock impingement, and increased inlet turbulence on the surface heat transfer.

SUBJECT TERMS:
Gas turbines; Heat transfer; Transonic flow; Supersonic turbines; Cascade wind tunnel; Liquid crystals; Turbomachinery; Turbulent heat transfer; Convective heat transfer;
Stanton number

NUMBER OF PAGES:
21

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