This paper is concerned with improving the prediction reliability of CFD modeling of gas turbine combustors. CFD modeling of gas turbine combustors has recently become an important tool in the combustor design process, which till now routinely used the old “cut and try” design practice. Improving the prediction capabilities and reliability of CFD methods will reduce the cycle time between idea and a working product. The paper presents a 3D numerical simulation of the BSE Ltd. YT-175 engine combustor, a small, annular, reversal flow type combustor. The entire flow field is modeled, from the compressor diffuser to turbine inlet. The model includes the fuel nozzle, the vaporizer solid walls, and liner solid walls with the dilution holes and cooling louvers. A periodic 36 deg sector of the combustor is modeled using a hybrid structured/unstructured multiblock grid. The time averaged Navier-Stokes (N-S) equations are solved, using the k-ε turbulence model and the combined time scale (COMTIME)/PPDF models for modeling the turbulent kinetic energy reaction rate. The vaporizer and liner walls’ temperature is predicted by the “conjugate heat transfer” methodology, based on simultaneous solution of the heat transfer equations for the vaporizer and liner walls, coupled with the N-S equations for the fluids. The calculated results for the mass flux passing through the vaporizer and various holes and slots of the liner walls, as well as the jet angle emerging from the liner dilution holes, are in very good agreement with experimental measurements. The predicted location of the liner wall hot spots agrees well with the position of deformations and cracks that occurred in the liner walls during test runs of the combustor. The CFD was used to modify the YT-175 combustion chamber to eliminate structural problems, caused by the liner walls overheating, that were observed during its development.
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e-mail: rgordon@tx.technion.ac.il
e-mail: leoyy@alrodyne.technion.ac.il
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October 2005
Technical Papers
Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation
R. Gordon,
e-mail: rgordon@tx.technion.ac.il
R. Gordon
Faculty of Aerospace Engineering, Technion—Israel Institute of Technology, Haifa 32000, Israel
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Y. Levy
e-mail: leoyy@alrodyne.technion.ac.il
Y. Levy
Faculty of Aerospace Engineering, Technion—Israel Institute of Technology, Haifa 32000, Israel
Search for other works by this author on:
R. Gordon
Faculty of Aerospace Engineering, Technion—Israel Institute of Technology, Haifa 32000, Israel
e-mail: rgordon@tx.technion.ac.il
Y. Levy
Faculty of Aerospace Engineering, Technion—Israel Institute of Technology, Haifa 32000, Israel
e-mail: leoyy@alrodyne.technion.ac.il
Contributed by the Combustion and Fuels Division of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received by the C&F Division April 28, 2003; final revision received May 5, 2004. Associate Editor: P. C. Malte.
J. Eng. Gas Turbines Power. Oct 2005, 127(4): 704-723 (20 pages)
Published Online: September 20, 2005
Article history
Received:
April 28, 2003
Revised:
May 5, 2004
Online:
September 20, 2005
Citation
Gordon, R., and Levy, Y. (September 20, 2005). "Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation ." ASME. J. Eng. Gas Turbines Power. October 2005; 127(4): 704–723. https://doi.org/10.1115/1.1808432
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