Turbine vanes are generally manufactured as single- or double-airfoil sections that are assembled into a full turbine disk. The gaps between the individual sections, as well as a gap between the turbine disk and the combustor upstream, provide leakage paths for relatively higher-pressure coolant flows. This leakage is intended to prevent ingestion of the hot combustion flow in the primary gas path. At the vane endwall, this leakage flow can interfere with the complex vortical flow present there and thus affect the heat transfer to that surface. To determine the effect of leakage flow through the gaps, heat transfer coefficients were measured along a first-stage vane endwall and inside the midpassage gap for a large-scale cascade with a simulated combustor-turbine interface slot and a midpassage gap. For increasing combustor-turbine leakage flows, endwall surface heat transfer coefficients showed a slight increase in heat transfer. The presence of the midpassage gap, however, resulted in high heat transfer near the passage throat where flow is ejected from that gap. Computational simulations indicated that a small vortex created at the gap flow ejection location contributed to the high heat transfer. The measured differences in heat transfer for the various midpassage gap flowrates tested did not appear to have a significant effect.
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October 2011
Research Papers
The Effect of the Combustor-Turbine Slot and Midpassage Gap on Vane Endwall Heat Transfer
Stephen P. Lynch,
Stephen P. Lynch
Department of Mechanical and Nuclear Engineering,
The Pennsylvania State University
, University Park, PA 16802
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Karen A. Thole
Karen A. Thole
Department of Mechanical and Nuclear Engineering,
The Pennsylvania State University
, University Park, PA 16802
Search for other works by this author on:
Stephen P. Lynch
Department of Mechanical and Nuclear Engineering,
The Pennsylvania State University
, University Park, PA 16802
Karen A. Thole
Department of Mechanical and Nuclear Engineering,
The Pennsylvania State University
, University Park, PA 16802J. Turbomach. Oct 2011, 133(4): 041002 (9 pages)
Published Online: April 19, 2011
Article history
Received:
May 19, 2010
Revised:
June 4, 2010
Online:
April 19, 2011
Published:
April 19, 2011
Citation
Lynch, S. P., and Thole, K. A. (April 19, 2011). "The Effect of the Combustor-Turbine Slot and Midpassage Gap on Vane Endwall Heat Transfer." ASME. J. Turbomach. October 2011; 133(4): 041002. https://doi.org/10.1115/1.4002950
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