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Optimization sealing and cooling to control gas intrusion in a floating-wall combustion chamber

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Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
In response to the problems of high-temperature gas intrusion and ablation in the expansion slit between ceramic tiles under complex flow conditions in the floating-wall combustion chamber, as well as the issue of hooks exceeding their service temperature, numerical simulations and analysis were conducted for this paper. The study revealed the mechanisms of gas intrusion and sealing and proposed two evaluation metrics for evaluating the cooling effect: the maximum temperature of the hook and the proportion of high-temperature area on the sidewall of the tile. Furthermore, the CRITIC weighting method was used to analyze the weight of these metrics. Based on this, the spacing, radius, and length effects on sealing and cooling effectiveness were studied, and multi-parameter calculations and optimization were performed. The results showed that the degree of gas intrusion in the transverse slit was significantly higher than that in the longitudinal slit. In addition, the sealing method of the jet impingement could effectively cool the downstream of both the transverse and longitudinal slit. The spacing of the jet impingement holes had the greatest impact on the cooling effect, followed by the radius and length. Finally, when the spacing of the holes is 10 mm, the length is 18.125 mm, and the radius is 1.6 mm, the cooling effect is optimal, with the proportion of high-temperature area on the side wall of the tile being 20.86% and the highest temperature of the hook reaching 836.02 K.
Rocznik
Strony
art. no. e148834
Opis fizyczny
Bibliogr 22 poz., rys., tab.
Twórcy
autor
  • College of Energy & Power Engineering, Jiangsu University of Science and Technology, China
autor
  • College of Energy & Power Engineering, Jiangsu University of Science and Technology, China
autor
  • College of Power and Energy Engineering, Harbin Engineering University, China
autor
  • College of Energy & Power Engineering, Jiangsu University of Science and Technology, China
autor
  • College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, China
  • College of Energy & Power Engineering, Jiangsu University of Science and Technology, China
autor
  • College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, China
Bibliografia
  • [1] A.B. Ali, W. Kriaa, H. Mhiri, and P. Bournot, “Numerical investigations of cooling holes system role in the protection of the walls of a gas turbine combustion chamber,” Heat Mass Transf., vol. 48, no. 5, pp. 779–788, May 2012.
  • [2] K.M. Kim, Y.H. Jeon, N. Yun, D.H. Lee, and H.H. Cho, “Thermo-mechanical life prediction for material lifetime improvement of an internal cooling system in a combustion liner,” Energy, vol. 36, no. 2, pp. 942–949, Feb 2011.
  • [3] P. Tarnawski and W. Ostapski, “Rotating combustion chambers as a key feature of effective timing of turbine engine working according to Humphrey cycle – CFD analysis,” Bull. Pol. Acad. Sci. Tech. Sci., vol. 70, no. 5, p. e143100, Oct 2022.
  • [4] K. Chidambaram and T. Packirisamy, “Smart ceramic materials for homogeneous combustion in internal combustion engines – A review,” Therm. Sci., vol. 13, no. 3, pp. 153–163, 2009.
  • [5] W.W. Choi and S.M. Kim, “Effect of effusion hole arrangement on jet array impingement heat transfer,” Int. J. Heat Mass Transf., vol. 192, p. 122900, Aug 2022.
  • [6] J.M. Owen, “Prediction of Ingestion Through Turbine Rim Seals – Part I: Rotationally Induced Ingress,” J. Turbomach.-Trans. ASME, vol. 133, no. 3, p. 031005, Jul 2011.
  • [7] J.M. Owen, “Prediction of Ingestion Through Turbine Rim Seals-Part II: Externally Induced and Combined Ingress,” J. Turbomach.-Trans. ASME, vol. 133, no. 3, p. 031006, Jul 2011.
  • [8] X.Y. Jia, H.Y. Dong, Y.Z. Ming, Y. Wu, and L.D. He, “Hot gas ingestion in chute rim seal clearance of gas turbine,” Int. J. Turbo. Jet-Engines, vol. 40, no. 3, pp. 329–339, 2023, doi: 10.1515/tjj-2021-0010.
  • [9] A. Andreini, L. Cocchi, B. Facchini, L. Mazzei, and A. Picchi, “Experimental and numerical investigation on the role of holes arrangement on the heat transfer in impingement/effusion cooling schemes,” Int. J. Heat Mass Transf., vol. 127, pp. 645–659, Dec 2018.
  • [10] T. Jackowski, M. Elfner, and H.J. Bauer, “Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis,” Energies, vol. 14, no. 16, p. 4843, Aug 2021.
  • [11] K.M. Kim, H. Moon, J.S. Park, and H.H. Cho, “Optimal design of impinging jets in an impingement/effusion cooling system,” Energy, vol. 66, pp. 839–848, Mar 2014.
  • [12] S. Ahmed, B.H. Wahls, S.V. Ekkad, H. Lee, and Y.H. Ho, “Effect of Spanwise Hole-to-Hole Spacing on Overall Cooling Effectiveness of Effusion Cooled Combustor Liners for a Swirl-Stabilized Can Combustor,” J. Turbomach.-Trans. ASME, vol. 144, no. 7, p. 071015, Jul 2022.
  • [13] A.B. Ali, W. Kriaa, H. Mhiri, and P. Bournot, “Analysis of the influence of cooling hole arrangement on the protection of a gas turbine combustor liner,” Meccanica, vol. 53, no. 9, pp. 2257–2271, Jul 2018.
  • [14] J. Wang, Z.W. Hu, C. Du, L. Tian, and J. Baleta, “Numerical study of effusion cooling of a gas turbine combustor liner,” Fuel, vol. 29, p. 120578, Jun 2021.
  • [15] R. Da Soghe, C. Bianchini, J. D’Errico, and L. Tarchi, “Effect of Temperature Ratio on Jet Impingement Heat Transfer in Active Clearance Control Systems,” J. Turbomach.-Trans. ASME, vol. 141, no. 8, p. 081009, Aug 2019.
  • [16] K.X. Liu, “Heat transfer characteristics of triple-stage impingement designs and their application for industrial gas turbine combustor liner cooling,” Int. J. Heat Mass Transf., vol. 172, p. 121174, Jun 2021.
  • [17] K. Liu and Q. Zhang, “A Novel Multi-Stage Impingement Cooling Scheme – Part I: Concept Study,” J. Turbomach.-Trans. ASME, vol. 142, no. 12, p. 121008, Dec 2020.
  • [18] K. Liu and Q. Zhang, “A Novel Multi-Stage Impingement Cooling Scheme – Part II: Design Optimization,” J. Turbomach.-Trans. ASME, vol. 142, no. 12, p. 121009, Dec 2020.
  • [19] J.U. Choi, G.M. Kim, H.C. Lee, and J.S. Kwak, “Optimization of the Coanda bump to improve the film cooling effectiveness of an inclined slot,” Int. J. Therm. Sci., vol. 139, pp. 376–386, May 2019.
  • [20] J. Joy, P.C. Wang, and S.C.M. Yu, “Effect of geometric modification on flow behaviour and performance of reverse flow combustor,” Proc. Inst. Mech. Eng. Part G-J. Aerosp. Eng., vol. 233, no. 4, pp. 1457–1471, Mar 2019.
  • [21] N.J. Bai et al., “Experimental investigations into the effusion plate wall temperature of impingement/effusion cooling systems for gas turbine combustors,” Aerosp.. Sci. Technol., vol. 132, p. 108052, Jan 2023.
  • [22] A.R. Krishnan, M.M. Kasim, R. Hamid, and M.F. Ghazali, “A Modified CRITIC Method to Estimate the Objective Weights of Decision Criteria,” Symmetry-Basel, vol. 13, no. 6, p. 973, Jun 2021.
Uwagi
Opracowanie rekordu ze środków MNiSW, umowa nr SONP/SP/546092/2022 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2024).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-ed730bae-bc5f-4323-8d73-fdfb5c83428a
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