Technological advancement in the gas turbine field demands high temperature gases impacting on the turbine airfoils in order to increase the output power as well as thermal efficiency. The leading edge is one of the most critical and life limiting sections of the airfoil which requires intricate cooling schemes to maintain a robust design. In order to maintain coherence with a typical external aerodynamic blade profile, cooling processes usually take place in geometrically-complex internal paths where analytical approaches may not provide a proper solution. In this study, experimental and numerical models simulating the leading-edge and its adjacent cavity were created. Cooling flow entered the leading-edge cavity through the crossover ports on the partition wall between the two cavities and impinged on the internal surface of the leading edge. Three flow arrangements were tested: (1) and (2) being flow entering from one side (root or tip) of the adjacent cavity and emerging from either the same side or the opposite side of the leading-edge cavity, and (3) flow entering from one side of the adjacent cavity and emerging from both sides of the leading-edge cavity. These flow arrangements were tested for five crossover-hole settings with a focus on studying the heat transfer rate dependency on the axial flow produced by upstream crossover holes (spent air). Numerical results were obtained from a three-dimensional unstructured computational fluid dynamics model with 1.1 × 106 hexahedral elements. For turbulence modeling, the realizable k-ε was employed in combination with the enhanced wall treatment approach for the near wall regions. Other available RANS turbulence models with similar computational cost did not produce any results in better agreement with the measured data. Nusselt numbers on the nose area and the pressure/suction sides are reported for jet Reynolds numbers ranging from 8000 to 55,000 and a constant crossover hole to the leading-edge nose distance ratio, Z/Dh, of 2.81. Comparisons with experimental results were made in order to validate the employed turbulence model and the numerically-obtained results. Results show a significant dependency of Nusselt number on the axial flow introduced by upstream jets as it drastically diminishes the impingement effects on the leading-edge channel walls. Flow arrangement has immense effects on the heat transfer results. Discrepancies between the experimental and numerical results averaged between +0.3% and −24.5%; however, correlation between the two can be clearly observed.
Skip Nav Destination
Article navigation
January 2013
Research-Article
Experimental/Numerical Crossover Jet Impingement in an Airfoil Leading-Edge Cooling Channel
M. E. Taslim
M. E. Taslim
Mechanical and Industrial
Engineering Department
Engineering Department
Northeastern University
Boston, MA 02115
Search for other works by this author on:
M. E. Taslim
Mechanical and Industrial
Engineering Department
Engineering Department
Northeastern University
Boston, MA 02115
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 27, 2011; final manuscript received August 7, 2011; published online October 31, 2012. Editor: David Wisler.
J. Turbomach. Jan 2013, 135(1): 011037 (12 pages)
Published Online: October 31, 2012
Article history
Received:
July 27, 2011
Revision Received:
August 7, 2011
Citation
Elebiary, K., and Taslim, M. E. (October 31, 2012). "Experimental/Numerical Crossover Jet Impingement in an Airfoil Leading-Edge Cooling Channel." ASME. J. Turbomach. January 2013; 135(1): 011037. https://doi.org/10.1115/1.4006420
Download citation file:
Get Email Alerts
Related Articles
Experimental and Numerical Study of Mass/Heat Transfer on an Airfoil Trailing-Edge Slots and Lands
J. Turbomach (April,2007)
Crossover Jet Impingement in a Rib-Roughened Trailing-Edge Cooling Channel
J. Turbomach (July,2017)
Aerothermal Challenges in Syngas, Hydrogen-Fired, and Oxyfuel Turbines—Part I: Gas-Side Heat Transfer
J. Thermal Sci. Eng. Appl (March,2009)
Experimental and Numerical Cross-Over Jet Impingement in an Airfoil Trailing-Edge Cooling Channel
J. Turbomach (October,2011)
Related Proceedings Papers
Related Chapters
Adding Surface While Minimizing Downtime
Heat Exchanger Engineering Techniques
Liquid Cooled Systems
Thermal Management of Telecommunications Equipment
Introduction
Thermal Power Plant Cooling: Context and Engineering