This paper presents computational and experimental study of a possible approach to reduce tip leakage losses. The study was conducted on the EEE (Energy Efficient Engine) HPT (High Pressure Turbine) rotor tip geometry. The CFD was done utilizing the commercial numerical solver ANSYS FLUENT. The experimental work was conducted in a low speed wind tunnel with linear cascade at the USNA (for Re = 30,000) and the NASA Transonic Turbine Blade Cascade facility at the NASA John H. Glenn Research Center for Re of 85,000 to 683,000 at two isentropic exit Mach numbers of 0.74 and 0.34 were reported. The overall scope of this study is to investigate how the tip leakage and overall blade losses are affected by injection from the tip surface at the camber line, and the jet blowing ratio. The results identify areas where future investigation can be explored in order to achieve higher performance of the high pressure turbines.
Skip Nav Destination
ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
June 15–19, 2015
Montreal, Quebec, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5672-7
PROCEEDINGS PAPER
Experimental and Computational Study of Novel Tip Leakage Mitigation Methods for High Pressure Turbine Blades
Mounir B. Ibrahim,
Mounir B. Ibrahim
Cleveland State University, Cleveland, OH
Search for other works by this author on:
Ralph J. Volino
Ralph J. Volino
United States Naval Academy, Annapolis, MD
Search for other works by this author on:
Mounir B. Ibrahim
Cleveland State University, Cleveland, OH
Ralph J. Volino
United States Naval Academy, Annapolis, MD
Paper No:
GT2015-44077, V05BT13A027; 16 pages
Published Online:
August 12, 2015
Citation
Ibrahim, MB, & Volino, RJ. "Experimental and Computational Study of Novel Tip Leakage Mitigation Methods for High Pressure Turbine Blades." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Montreal, Quebec, Canada. June 15–19, 2015. V05BT13A027. ASME. https://doi.org/10.1115/GT2015-44077
Download citation file:
20
Views
Related Proceedings Papers
Related Articles
Effect of Roughness and Unsteadiness on the Performance of a New Low Pressure Turbine Blade at Low Reynolds Numbers
J. Turbomach (July,2010)
A Study of Advanced High-Loaded Transonic Turbine Airfoils
J. Turbomach (October,2006)
Influence of Loading Distribution on the Performance of Transonic High Pressure Turbine Blades
J. Turbomach (April,2004)
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential