Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade: Part 2 — Simulation Results

A combined experimental and numerical study to investigate the heat transfer distribution in a complex blade trailing edge passage was conducted. The geometry consists of a two pass serpentine passage with taper toward the trailing edge, as well as from hub to tip. The upflow channel has an average aspect ratio of roughly 14:1, while the exit passage aspect ratio is about 5:1. The upflow channel is split in an interrupted way and is smooth on the trailing edge side of the split and turbulated on the other side. A turning vane is placed near the tip of the upflow channel. Reynolds numbers in the range of 31,000 to 61,000, based on inlet conditions were simulated numerically. The simulation was performed using the Glenn-HT code, a full three-dimensional Navier-Stokes solver using the Wilcox k-ω turbulence model. A structured multi-block grid is used with approximately 4.5 million cells, and average y+ values on the order of unity. Pressure and heat transfer distributions are presented with comparison to the experimental data. While there are some regions with discrepancies, in general the agreement is very good for both pressure and heat transfer.Copyright © 2002 by ASME

[1]  R. J. Moffat,et al.  Measurement of temperature and heat transfer coefficient distributions in a complex flow using liquid crystal thermography and true-color image processing , 1989 .

[2]  A. A. Ameri,et al.  Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 2 — Simulation Results , 1999 .

[3]  James D. Heidmann,et al.  A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane , 1999 .

[4]  Meng-Sing Liou,et al.  Development of an explicit multiblock/multigrid flow solver for viscous flows in complex geometries , 1993 .

[5]  David L. Rigby,et al.  Prediction of Heat and Mass Transfer in a Rotating Ribbed Coolant Passage With a 180 Degree Turn , 1998 .

[6]  D. Rigby,et al.  A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models , 1999 .

[7]  R. J. Goldstein,et al.  Heat transfer and friction in tubes with repeated-rib roughness , 1971 .

[8]  David L. Rigby,et al.  Conjugate Heat Transfer Analysis of Internally Cooled Configurations , 2001 .

[9]  D. Wilcox.  Simulation of Transition with a Two-Equation Turbulence Model , 1994 .

[10]  T. Arts,et al.  The Effect of Periodic Ribs on the Local Aerodynamic and Heat Transfer Performance of a Straight Cooling Channel , 1996 .

[11]  Meng-Sing Liou,et al.  Multigrid calculation of three-dimensional viscous cascade flows , 1991 .

[12]  John K. Eaton,et al.  Illuminant invariant calibration of thermochromic liquid crystals , 1994 .

[13]  Todd Garrett Wetzel,et al.  Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade - Part 1: Experimental Measurements. Part 1; Experimental Measurements , 2000 .

[14]  J. Wolfersdorf,et al.  Heat Transfer Technology for Internal Passages of Air‐Cooled Blades for Heavy‐Duty Gas Turbines , 2001, Annals of the New York Academy of Sciences.

[15]  D. Rigby,et al.  Heat transfer on a film-cooled blade – effect of hole physics , 1998 .

[16]  Dino J. Farina,et al.  A system for making temperature measurements using thermochromic liquid crystals , 1994 .

[17]  N. Abuaf,et al.  Heat Transfer and Turbulence in a Turbulated Blade Cooling Circuit , 1992 .