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Numerical Simulation of Effect of Various Rib Configurations on Enhancing Heat Transfer of Matrix Cooling Channel

Authors: Seok Min Choi, Minho Bang, Seuong Yun Kim, Hyungmin Lee, Won-Gu Joo, Hyung Hee Cho

Abstract:

The matrix cooling channel was used for gas turbine blade cooling passage. The matrix cooling structure is useful for the structure stability however the cooling performance of internal cooling channel was not enough for cooling. Therefore, we designed the rib configurations in the matrix cooling channel to enhance the cooling performance. The numerical simulation was conducted to analyze cooling performance of rib configured matrix cooling channel. Three different rib configurations were used which are vertical rib, angled rib and c-type rib. Three configurations were adopted in two positions of matrix cooling channel which is one fourth and three fourth of channel. The result shows that downstream rib has much higher cooling performance than upstream rib. Furthermore, the angled rib in the channel has much higher cooling performance than vertical rib. This is because; the angled rib improves the swirl effect of matrix cooling channel more effectively. The friction factor was increased with the installation of rib. However, the thermal performance was increased with the installation of rib in the matrix cooling channel.

Keywords: Matrix cooling, rib, heat transfer, gas turbine.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1314877

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References:


[1] Bunker, R. S, “Latticework (vortex) cooling effectiveness part 1: stationary channel experiments,” ASME Paper, 2004, No. GT2004-54157.
[2] Acharya, S., Zhou, F., Lagrone, J., Mahmood, G. and Bunker, R. S, “Lattice (vortex) cooling effectiveness: rotating channel experiments,” ASME Paper, 2004, GT2004-53983.
[3] Su, S., Liu, J. J., Fu, J. L., Hu, J. and An, B. T. “Numerical investigation of fluid flow and heat transfer in a turbine blade with serpentine passage and latticework cooling,” ASME Turbo Expo, 2008, GT2008-50392
[4] Saha, K., Guo, S., Acharya, S. and Nakamata, C, “Heat transfer and pressure measurements in a lattice-cooled trailing edge of a turbine airfoil,” ASME Turbo Expo, 2008, GT2008-51324
[5] Oh, I. T., Kim, K. M., Lee, D. H., Park, J. S., and Cho, H. H, “Local heat/mass transfer and friction loss measurement in a rotating matrix cooling channel,” Journal of Heat Transfer, 2012, Vol.134, No.1, 011901.
[6] Hagari, T., and Ishida, K, “Numerical investigation on flow and heat transfer in a lattice (matrix) cooling channel,” ASME Turbo Expo, 2013, GT2013-95412
[7] Carcasci, C., Facchini, B., Pievaroli, M., Tarchi, L., Ceccherini, A., and Innocenti, L, “Heat transfer and pressure loss measurements of matrix cooling geometries for gas turbine airfoils,” Journal of Turbomachinery, 2014, Vol.136, No.12, 121005.
[8] Luan, Y., Bu, S., Sun, H., and Sun, T, “Numerical Investigation on Flow and Heat Transfer in Matrix Cooling Channels for Turbine Blades,” ASME Turbo Expo, 2016, GT2016-56279
[9] Luan, Y., Yang, L., Wan, B., and Sun, T. “Large Eddy Simulation of Flow and Heat Transfer Mechanism in Matrix Cooling Channel,” ASME Turbo Expo, 2017, GT2017-63515
[10] Bu, S., Yang, Z., Zhang, W., Liu, H., and Sun, H, “Research on the thermal performance of matrix cooling channel with response surface methodology,” Applied Thermal Engineering, 2016, Vol.109, pp.75-86.
[11] Gillespie, D. R., Ireland, P. T. and Dailey, G. M, “Detailed flow and heat transfer coefficient measurements in a model of an internal cooling geometry employing orthogonal intersecting channels,” ASME Paper, 2000, 2000-GT-653.
[12] Deng, H., Wang, K., Zhu, J., and Pan, W., “Experimental study on heat transfer and flow resistance in improved latticework cooling channels,” Journal of Thermal Science, 2013, Vol.22, No.3, pp.250-256.