Effective reduction of temperature unevenness in turbine shell blades
https://doi.org/10.18384/2949-5067-2025-1-6-16
Abstract
Aim. Reduction of temperature unevenness in a shell-type turbine blade under conditions of heat supply and removal.
Methodology. The mathematical formulation of the problem of reducing the temperature unevenness of the shell using a system of curved heat sink channels is carried out. The mathematical model was constructed using the condition of continuity of the cooling flow in the channel, data on the source of thermal stress, boundary conditions at the entrance and exit to the cooling channel, restrictions on the height of the channels using interpolation polynomials.
Results. The variable height and trajectories of the heat sink channels are calculated for a given uneven temperature field, allowing to intensify cooling in the most thermally loaded area of the shell.
Research implications. The theoretical and practical significance lies in the possibility of using the proposed model to develop a deflector shape with curved channels for blades of a gas turbine engine with an internal cooling system.
About the Authors
I. K. Andrianov
Komsomolsk-na-Amure State University
Russian Federation
Russian Federation
Ivan K. Andrianov – Cand. Sci. (Engineering), Assoc. Prof., Department of Aircraft Engineering
Komsomolsk-on-Amur
E. K. Chepurnova
Komsomolsk-na-Amure State University
Russian Federation
Russian Federation
Elena K. Chepurnova – Research Assistant, Department of organization and support of scientific and innovative activities
Komsomolsk-on-Amur
References
1. Wang, T., Xuan, Y. & Han, X. (2023). Investigation on hybrid thermal features of aeroengines from combustor to turbine. In: International Journal of Heat and Mass Transfer, 200, 123559. DOI: 10.1016/j.ijheatmasstransfer.2022.123559.
2. Anoosha, K., Akhil Kumar, Ch., Kesava, L., Bharath, V. & Akhil, N. (2024). Thermal analysis of a gas turbine rotar blade. In: Interantional Journal of Scientific Research in Engineering and Management, 8 (4), 1–8. DOI: 10.55041/IJSREM31271.
3. Lepeshkin, A. R. (2013). Thermal conductivity of metal materials in conditions of action of centrifugal accelerations and forces. In: Modern Science: Researches, Ideas, Results, Technologies, 1 (12), 336–339 (in Russ.).
4. Tugazakov, R. Ya. (2024). Numerical and analytical study of turbulence of supersonic viscous gas flow. In: Bulletin of Federal State University of Education. Series: Physics and Mathematics, 1, 68–82. DOI: 10.18384/10.18384/2949-5067-2024-1-68-82 (in Russ.).
5. Gulakova, S. V. & Popov, V. N. (2014). On the boundaries of applicability of the hydrodynamic approach to the solution of the poiseuille flow problem. In: Bulletin of Federal State University of Education. Series: Physics and Mathematics, 2, 52–62 (in Russ.).
6. Germider, O. V., Popov, V. N. & Yushkanov, A. A. (2015), Computation of heat flow in a long, rectangular channel of constant cross section in the framework of the kinetic approach. In: Bulletin of Federal State University of Education. Series: Physics and Mathematics, 2, 96–106 (in Russ.).
7. Sadkov, A. A. & Popov, V. N. (2021). Search for the heat flow profile and gas mass velocity in a cylindrical channel. In: International Journal of Open Information Technologies, 9 (2), 54–58 (in Russ.).
8. Poletaev, V. A. & Tsvetkov, E. V. (2018). Improvements in Turbine-Blade Manufacture. In: Russian Engineering Research, 38 (12), 1053–1055. DOI: 10.3103/S1068798X18120298.
9. Vikulin, A. V. & Zemlyanaya, V. A. (2023). Study of the thermal state of models of gas turbine blades with transpiration cooling made of sintered steel fibers. In: STIN, 3, 21–25 (in Russ.).
10. Andrianov, I. K. & Chepurnova, E. K. (2023). Optimizing Crack Detection in Gas Turbine Blades Using Implanted Capsules of Ionizing Gas in Nonsteady Operation at Nonuniform Temperature. In: Russian Engineering Research, 43 (11), 1361–1366. DOI: 10.3103/s1068798x23110035.
11. Gulevskiy, V. A., Tsurikhin, S. N., Gulevskiy, V. V. & Miroshkin, N. Y. (2021). Research of modification influence on cracking resistance of cast iron in moulds. In: CIS Iron and Steel Review, 22, 9–14. DOI: 10.17580/cisisr.2021.02.02.
12. Veerabhadra, S. & Madhu, B. (2023). CFD Analysis of Gas Turbine Blade Cooling with Staggered Holes. In: Journal of Mines, Metals and Fuels, 71 (12), 2593–2609. DOI: 10.18311/jmmf/2023/40595.
13. Gaikwad, S. S. & Sonawane, C. R. (2014). Review of heat transfer augmentation for cooling of turbine blade tip by geometrical modifications to the surfaces of blade. In: International Journal of Research in Engineering and Technology, 3 (7), 15–22.
14. Zuo, M., He, Z., Sun, S., Mao, J. & Dong, C. (2024). Simulation of flow and heat transfer characteristics of laminated turbine blades with kerosene cooling channels. In: Thermal Science, 28 (1A), 13–24. DOI: 10.2298/TSCI230115082Z.
15. Nguyen, V., Duy, V., Dinh, C. & Park, S. (2024). Numerical investigation of the flows and heat transfer characteristics of internal cooling channels with separated ribs in gas turbine blades. In: Physics of Fluids, 36 (3), 035112. DOI: 10.1063/5.0183192.
16. Wu, L. (2007). Thermal effects on liquid film dynamics in spin coating. In: Sensors and Actuators A: Physical, 134 (1), 140–145. DOI: 10.1016/j.sna.2006.05.008.
17. Isakov, G. N., Kuzin, A. Ya., Savel'ev, V. N. & Ermolaev, V. F. (2003). Determination of characteristics of thin-layer thermoprotective coatings by solving inverse heat- and masstransfer problems. In: Combustion, Explosion, and Shock Waves, 39 (5), 86–97 (in Russ.).
18. Mazilin, I. V., Zaitsev, N. G., Akhmetgareeva, A. M., Baldaev, L. Kh. & Drobot, D. V. (2018). Domestic materials for new generation heat-protective coatings. In: Gas turbo technology, 3 (154), 20–25 (in Russ.).
19. You, H. (2023). Effect of thermal barrier coating on the thermal characteristic of turbine blade and its geometric optimization. In: Theoretical and Natural Science, 14, 62–77. DOI: 10.54254/2753-8818/14/20240880.
20. Guo, X. & Ding, M. (2010). Simulation of thermal NDT of thickness and its unevenness of thermal barrier coatings. In: Hangkong Xuebao (Acta Aeronautica et Astronautica Sinica), 31 (1), 198–203.
Supplementary files
Review
Views:
12
Email this article 