Conjugate Heat Transfer Analysis of High Pressure Turbine with Secondary Flow Path and Thermal Barrier Coating Kang, Young-Seok; Rhee, Dong Ho; Cha, Bong Jun;
Conjugate heat analysis on a high pressure turbine stage including secondary flow paths has been carried out. The secondary flow paths were designed to be located in front of the nozzle and between the nozzle and rotor domains. Thermal boundary conditions such as empirical based temperature or heat transfer coefficient were specified at nozzle and rotor solid domains. To create heat transfer interface between the nozzle solid domain and the rotor fluid domain, frozen rotor with automatic pitch control was used assuming that there is little temperature variation along the circumferential direction at the nozzle solid and rotor fluid domain interface. The simulation results showed that secondary flow injected from the secondary flow path not only prevents main flow from penetrating into the secondary flow path, but also effectively cools down the nozzle and rotor surfaces. Also thermal barrier coating with different thickness was numerically implemented on the nozzle surface. The thermal barrier coating further reduces temperature gradient over the entire nozzle surface as well as the overall temperature level.
Kang, Y. S., Rhee, D. H., Kim, C. T. and Cha, B. J., 2013, "Aerodynamic optimization of axial turbine tip cavity with approximation model", ASME Paper No. TBTS2013-2079.
Kim, J. U., Bak, J. G., Kang, Y. S., and Cho, J. S., 2015, "Conjugate heat transfer analysis for high pressure cooled turbine vane in aircraft gas turbine", Journal of Fluid Machinery, Vol 18, No. 2, pp. 60-66.
Kathiravan, S., De Prosperis, R., and Ciani, A., 2013, "Numerical investigation of flow and heat transfer in gas turbine sepertine passage cooling and comparison with experimental data," ASME GT2013-94666.
Ron-Ho Ni, William Humber, George Fan, John P. Clark, Richard J. Anthony, Capt. Jamie J. Johnson, "Comparison of predictions from conjugate heat transfer analysis of a film-cooled turbine vane to experimental data," ASME GT2013-94716.
Robert D. Thulin, David C. Howe and Irwin D. Singer, 1982, "Energy efficient engine high-pressure turbine detailed design report," NASA CR-165608.
Cardwell, N. D., Sundaram, N. and Thole, K. A., 2007, "The effects of varying the combustor-turbine gap", Journal of Turbomachinery, Vol. 129, No. 4, pp. 756-764.
Lynch, S. P. and Thole, K. A., 2008, "The effects of varying the combustor-turbine gap," ASME Journal of Turbomachinery, Vol. 130, pp. 041019-1-041019-10.
Xiwen, S., Min, X., Fen, Z., Guixiao, J., Xihong, H., & Shengli, A. (2011). High-temperature thermal properties of yttria fully stabilized zirconia ceramics. Journal of Rare Earths, 29(2), 155-159.