Gaz Türbini Yanma Odası Astarında Efüzyon Soğutmanın Sayısal Olarak İncelenmesi

Abstract

In this study, a numerical analysis was performed to find the aerothermal characteristics of the effusion cooled gas turbine combustor liner. The analyzed geometric model is a scale model of an actual combustor liner. The study aims to investigate the effect of different blowing ratios by validating an experimental test setup. In experimental studies on effusion cooling, the sidewall effect is a serious problem that can distort the results. Numerical analyses provide advantages in visualizing temperature and velocity contours in different sections of physical model. The counter rotating vortex pairs, the horseshoe vortex and the recirculation zone are the main flow features of the jet mixture. At a blowing ratio of 3.35, numerical analyzes gave the highest value of cooling effectiveness. Although the blowing ratio slightly changes the cooling effectiveness in experimental data, it has been found that the effect of blowing ratio is more pronounced on the numerical results, especially at high blowing ratios.

Keywords

• Efüzyon soğutma
• gaz türbini yanma odası astarı
• üfleme oranı
• ısı transferi
• hesaplamalı akışkanlar dinamiği.
• Efüzyon soğutma, gaz türbini yanma odası astarı, üfleme oranı, ısı transferi, hesaplamalı akışkanlar dinamiği.

Numerical Investigation of Effusion Cooling in Gas Turbine Combustor Liner

Abstract

In this study, a numerical analysis was performed to find the aerothermal characteristics of the effusion cooled gas turbine combustor liner. The analyzed geometric model is a scale model of an actual combustor liner. The study aims to investigate the effect of different blowing ratios by validating an experimental test setup. In experimental studies on effusion cooling, the sidewall effect is a serious problem that can distort the results. Numerical analyses provide advantages in visualizing temperature and velocity contours in different sections of physical model. The counter rotating vortex pairs, the horseshoe vortex and the recirculation zone are the main flow features of the jet mixture. At a blowing ratio of 3.35, numerical analyzes gave the highest value of cooling effectiveness. Although the blowing ratio slightly changes the cooling effectiveness in experimental data, it has been found that the effect of blowing ratio is more pronounced on the numerical results, especially at high blowing ratios.

Keywords

• Effusion cooling
• gas turbine combustor liner
• blowing ratio
• heat transfer
• computational fluid dynamics.
• Effusion cooling, gas turbine combustor liner, blowing ratio, heat transfer, computational fluid dynamics.

References

1. Durmus, S. (2017). Investigation of film cooling flow characteristics in gas turbines by PIV method. Doctoral Dissertations. Anadolu University.
2. McGhee, S. K. (2000). Evaluation of an Uncooled Focal Plane Array Thermal Imaging Camera for Effusion Cooling Research. National Library of Canada
3. Gustafsson, K. B. (2001). Experimental studies of effusion cooling. Chalmers University of Technology.
4. Grierson, M. (2004.) Non-adiabatic Effusion Cooling Performance of Laser Drilled Test Plates Using Infrared Thermography. Scrittore, J. J., Thole, K. A., & Burd, S. W. (2007). Investigation of velocity profiles for effusion cooling of a combustor liner. Journal of Turbomachinery,129(3), 518-526.
5. Zhong, F., & Brown, G. L. (2007). A 3-dimensional, coupled, DNS, heat transfer model and solution for multi-hole cooling. International journal of heat and mass transfer, 50(7-8), 1328-1343.
6. Arcangeli, L., Facchini, B., Surace, M., & Tarchi, L. (2008). Correlative analysis of effusion cooling systems. Journal of Turbomachinery, 130(1), 011016.
7. Cho, H. H., Rhee, D. H., & Goldstein, R. J. (2008). Effects of hole arrangements on local heat/mass transfer for impingement/effusion cooling with small hole spacing. Journal of Turbomachinery, 130(4), 041003.
8. Facchini, B., Tarchi, L., Toni, L., Cinque, G., & Colantuoni, S., (2009) Investigation of Circular and Shaped Effusion Cooling Arrays for Combustor Liner Application—Part 1: Experimental Analysis. In ASME Turbo Expo 2009: Power for Land, Sea, and Air (pp. 1409-1418). American Society of Mechanical Engineers.

9. Andreini, A., Facchini, B., Picchi, A., Tarchi, L., & Turrini, F. (2014). Experimental and theoretical investigation of thermal effectiveness in multiperforated plates for combustor liner effusion cooling. Journal of Turbomachinery, 136(9), 091003.
10. Ligrani, P., Goodro, M., Fox, M., & Moon, H. K. (2012). Full-Coverage Film Cooling: Film Effectiveness and Heat Transfer Coefficients for Dense and Sparse Hole Arrays at Different Blowing Ratios. Journal of Turbomachinery,134(6), 061039.
11. Wurm, B., Schulz, A., Bauer, H. J., & Gerendas, M. (2012). Impact of swirl flow on the cooling performance of an effusion cooled combustor liner. Journal of Engineering for Gas Turbines and Power, 134(12), 121503.
12. Andrei, L., Andreini, A., Bianchini, C., Caciolli, G., Facchini, B., Mazzei, L., & Turrini, F. (2014). Effusion cooling plates for combustor liners: Experimental and numerical investigations on the effect of density ratio. Energy Procedia,45, 1402-1411.
13. Andreini, A., Caciolli, G., Facchini, B., Picchi, A., & Turrini, F. (2015). Experimental investigation of the flow field and the heat transfer on a scaled cooled combustor liner with realistic swirling flow generated by a lean-burn injection system. Journal of Turbomachinery, 137(3), 031012.
14. Da Soghe, R., Andreini, A., Facchini, B., & Mazzei, L. (2015). Heat transfer enhancement due to coolant extraction on the cold side of effusion cooling plates. Journal of Engineering for Gas Turbines and Power, 137(12).
15. Oguntade, H. I., Andrews, G. E., Burns, A. D., Ingham, D. B., & Pourkashanian, M. (2015). The Influence the Number of Holes on Effusion Cooling Effectiveness for an X/D of 4.7. In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition (pp. V05AT10A002-V05AT10A002). American Society of Mechanical Engineers.
16. [Hasan, R., & Puthukkudi, A. (2013). Numerical study of effusion cooling on an adiabatic flat plate. Propulsion and Power Research, 2(4), 269-275.
17. Jingzhou, Z., Hao, X., & Chengfeng, Y. (2009). Numerical study of flow and heat transfer characteristics of impingement/effusion cooling. Chinese Journal of Aeronautics, 22(4), 343-348.
18. Walton, M., & Yang, Z. (2014). Numerical study of effusion cooling flow and heat transfer.
19. Murray, A. V., Ireland, P. T., Wong, T. H., Tang, S. W., & Rawlinson, A. J. (2018). High Resolution Experimental and Computational Methods for Modelling Multiple Row Effusion Cooling Performance. International Journal of Turbomachinery, Propulsion and Power, 3(1), 4.
20. Ceccherini, A., Facchini, B., Tarchi, L., Toni, L., & Coutandin, D. (2009). Combined effect of slot injection, effusion array and dilution hole on the cooling performance of a real combustor liner. In ASME Turbo Expo 2009: Power for Land, Sea, and Air (pp. 1431-1440). American Society of Mechanical Engineers.
21. Tarchi, L., Facchini, B., Maiuolo, F., & Coutandin, D. (2012). Experimental investigation on the effects of a large recirculating area on the performance of an effusion cooled combustor liner. Journal of Engineering for Gas Turbines and Power, 134(4), 041505.
22. Inanli, S., Yasa, T., & Ulas, A. (2016). Experimental investigation of effusion and film cooling for gas turbine combustor.
23. Ekiciler, R., Çetinkaya, M. S. A., & Arslan, K. (2020). Effect of shape of nanoparticle on heat transfer and entropy generation of nanofluid-jet impingement cooling. International Journal of Green Energy, 17(10), 555-567.