Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 127 deg of nominal turning and an axial chord of 130 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the facility maximum point of 2.50 × 106, as well as conditions which represent 50%, 25%, and 15% of this maximum condition. Three ideal exit pressure ratios were examined including the design point of 1.443, as well as conditions which represent −25% and +20% of the design value. Three inlet flow angles were examined including the design point and ±5 deg off-design angles. Measurements were made in a linear cascade with highly three-dimensional blade passage flows that resulted from the high flow turning and thick inlet boundary layers. Inlet turbulence was generated with a blown square bar grid. The purpose of the work is the extension of three-dimensional predictive modeling capability for airfoil external heat transfer to engine specific conditions including blade shape, Reynolds numbers, and Mach numbers. Data were obtained by a steady-state technique using a thin-foil heater wrapped around a low thermal conductivity blade. Surface temperatures were measured using calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, and also show good detail in the stagnation region.
Skip Nav Destination
ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference
June 16–19, 2003
Atlanta, Georgia, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-3688-6
PROCEEDINGS PAPER
Measurements and Predictions of Heat Transfer on Rotor Blades in a Transonic Turbine Cascade
Paul W. Giel,
Paul W. Giel
NASA Glenn Research Center, Cleveland, OH
Search for other works by this author on:
Robert J. Boyle,
Robert J. Boyle
NASA Glenn Research Center, Cleveland, OH
Search for other works by this author on:
Ronald S. Bunker
Ronald S. Bunker
General Electric Company – Global Research Center, Schenectady, NY
Search for other works by this author on:
Paul W. Giel
NASA Glenn Research Center, Cleveland, OH
Robert J. Boyle
NASA Glenn Research Center, Cleveland, OH
Ronald S. Bunker
General Electric Company – Global Research Center, Schenectady, NY
Paper No:
GT2003-38839, pp. 623-638; 16 pages
Published Online:
February 4, 2009
Citation
Giel, PW, Boyle, RJ, & Bunker, RS. "Measurements and Predictions of Heat Transfer on Rotor Blades in a Transonic Turbine Cascade." Proceedings of the ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. Volume 5: Turbo Expo 2003, Parts A and B. Atlanta, Georgia, USA. June 16–19, 2003. pp. 623-638. ASME. https://doi.org/10.1115/GT2003-38839
Download citation file:
31
Views
Related Proceedings Papers
Related Articles
1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and Theoretical Analysis
J. Turbomach (July,2000)
A Study of Advanced High-Loaded Transonic Turbine Airfoils
J. Turbomach (October,2006)
Endwall Heat Transfer Measurements in a Transonic Turbine Cascade
J. Turbomach (April,1998)
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Natural Gas Transmission
Pipeline Design & Construction: A Practical Approach, Third Edition