Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade

Vane endwall heat transfer distributions are documented for a mock aeroderivative combustion system and for a low turbulence condition in a large-scale low speed linear cascade facility. Inlet turbulence levels range from below 0.7% for the low turbulence condition to 14% for the mock combustor system. Stanton number contours are presented at both turbulence conditions for Reynolds numbers based on true chord length and exit conditions ranging from 500,000 to 2,000,000. Low turbulence endwall heat transfer shows the influence of the complex three-dimensional flow field, while the effects of individual vortex systems are less evident for the high turbulence cases. Turbulent scale has been documented for the high turbulence case. Inlet boundary layers are relatively thin for the low turbulence case, while inlet flow approximates a nonequilibrium or high turbulence channel flow for the mock combustor case. Inlet boundary layer parameters are presented across the inlet passage for the three Reynolds numbers and both the low turbulence and mock combustor inlet cases. Both midspan and 95% span pressure contours are included. This research provides a well-documented database taken across a range of Reynolds numbers and turbulence conditions for assessment of endwall heat transfer predictive capabilities.

[1]  Forrest E. Ames,et al.  The influence of large-scale high-intensity turbulence on vane heat transfer , 1997 .

[2]  R. J. Boyle,et al.  Predicted Turbine Heat Transfer for a Range of Test Conditions , 1996 .

[3]  Gary D. Lock,et al.  Endwall heat transfer measurements in an annular cascade of nozzle guide vanes at engine representative Reynolds and Mach numbers , 1996 .

[4]  P. W. Giel,et al.  Endwall Heat Transfer Measurements in a Transonic Turbine Cascade , 1996 .

[5]  Karen A. Thole,et al.  Computational Design and Experimental Evaluation of Using a Leading Edge Fillet on a Gas Turbine Vane , 2001 .

[6]  R. J. Moffat,et al.  An Algebraic Model for High Intensity Large Scale Turbulence , 1999 .

[7]  Karen A. Thole,et al.  High Free-Steam Turbulence Effects on Endwall Heat Transfer for a Gas Turbine Stator Vane , 2000 .

[8]  Robert J. Moffat,et al.  Describing the Uncertainties in Experimental Results , 1988 .

[9]  Steven A. Hippensteele,et al.  Use of a liquid-crystal and heater-element composite for quantitative, high-resolution heat-transfer coefficients on a turbine airfoil including turbulence and surface-roughness effects , 1987 .

[10]  C. H. Sieverding,et al.  Recent Progress in the Understanding of Basic Aspects of Secondary Flows in Turbine Blade Passages , 1985 .

[11]  L. Langston,et al.  Three-Dimensional Flow Within a Turbine Cascade Passage , 1977 .

[12]  L. M. Russell,et al.  High-resolution liquid-crystal heat-transfer measurements on the endwall of a turbine passage with variations in Reynolds number , 1988 .

[13]  L. M. Russell,et al.  Local heat-transfer measurements on a large scale-model turbine blade airfoil using a composite of a heater element and liquid crystals , 1985 .

[14]  L D Hylton,et al.  An experimental investigation of endwall heat transfer and aerodynamics in a linear vane cascade , 1984 .

[15]  T. Arts,et al.  Aerodynamic and thermal performance of a three dimensional annular transonic nozzle guide vane , 1994 .

[16]  M. Plesniak,et al.  The Influence of Large-Scale, High-Intensity Turbulence on Vane Aerodynamic Losses, Wake Growth, and the Exit Turbulence Parameters , 1997 .

[17]  Terrence W. Simon,et al.  Flow measurements in a nozzle guide vane passage with a low aspect ratio and endwall contouring , 2000 .

[18]  R. Goldstein,et al.  Turbulent Transport on the Endwall in the Region Between Adjacent Turbine Blades , 1987 .