This first paper describes the conjugate heat transfer (CHT) method and its application to the performance and lifetime prediction of a high pressure turbine blade operating at a very high inlet temperature. It is the analysis tool for the aerothermal optimization described in a second paper. The CHT method uses three separate solvers: a Navier–Stokes solver to predict the nonadiabatic external flow and heat flux, a finite element analysis (FEA) to compute the heat conduction and stress within the solid, and a 1D aerothermal model based on friction and heat transfer correlations for smooth and rib-roughened cooling channels. Special attention is given to the boundary conditions linking these solvers and to the stability of the complete CHT calculation procedure. The Larson–Miller parameter model is used to determine the creep-to-rupture failure lifetime of the blade. This model requires both the temperature and thermal stress inside the blade, calculated by the CHT and FEA. The CHT method is validated on two test cases: a gas turbine rotor blade without cooling and one with five cooling channels evenly distributed along the camber line. The metal temperature and thermal stress distribution in both blades are presented and the impact of the cooling channel geometry on lifetime is discussed.
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e-mail: sergio.amaral@ge.com
e-mail: tom.verstraete@vki.ac.be
e-mail: vdb@vki.ac.be
e-mail: arts@vki.ac.be
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April 2010
Research Papers
Design and Optimization of the Internal Cooling Channels of a High Pressure Turbine Blade—Part I: Methodology
Sergio Amaral,
Sergio Amaral
Department of Aerospace Engineering,
e-mail: sergio.amaral@ge.com
Pennsylvania State University
, 229 Hammond Building, University Park, PA 16802
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Tom Verstraete,
Tom Verstraete
Department of Turbomachinery and Propulsion,
e-mail: tom.verstraete@vki.ac.be
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgium
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René Van den Braembussche,
René Van den Braembussche
Department of Turbomachinery and Propulsion,
e-mail: vdb@vki.ac.be
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgium
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Tony Arts
Tony Arts
Department of Turbomachinery and Propulsion,
e-mail: arts@vki.ac.be
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgium
Search for other works by this author on:
Sergio Amaral
Department of Aerospace Engineering,
Pennsylvania State University
, 229 Hammond Building, University Park, PA 16802e-mail: sergio.amaral@ge.com
Tom Verstraete
Department of Turbomachinery and Propulsion,
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgiume-mail: tom.verstraete@vki.ac.be
René Van den Braembussche
Department of Turbomachinery and Propulsion,
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgiume-mail: vdb@vki.ac.be
Tony Arts
Department of Turbomachinery and Propulsion,
von Kármán Institute for Fluid Dynamics
, Waterloosesteenweg 72, 640 Sint-Genesius-Rode, Belgiume-mail: arts@vki.ac.be
J. Turbomach. Apr 2010, 132(2): 021013 (7 pages)
Published Online: January 13, 2010
Article history
Received:
September 30, 2008
Revised:
November 19, 2008
Online:
January 13, 2010
Published:
January 13, 2010
Citation
Amaral, S., Verstraete, T., Van den Braembussche, R., and Arts, T. (January 13, 2010). "Design and Optimization of the Internal Cooling Channels of a High Pressure Turbine Blade—Part I: Methodology." ASME. J. Turbomach. April 2010; 132(2): 021013. https://doi.org/10.1115/1.3104614
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