The influence of blade row temperature on the aerodynamic characteristics of an axial compressor impeller

Volodymyr Otroshchenko, Maryna Pikul, Yuriy Tereshchenko

Abstract


The subject of this study was the characteristics of the compressor impeller regarding the heating of the blade row. The object of this study was the blade row of an axial compressor impeller. The purpose of this study was to evaluate the effect of the blade row temperature on the characteristics of the axial compressor impeller. The following tasks were set and solved in the study: modeling the flow in the compressor impeller considering even heating of the blade row to a temperature in the range of Tb/Ta = 1...2 with a step of 0.25 at different values of the axial flow velocity at the inlet from 100 to 140 m/s with a step of 10 m/s; calculating the degree of pressure increase and efficiency of the compressor impeller in the range of blade rim heating Tb/Ta = 1...2 with a step of 0.25; the effect of heating the compressor impeller blade row on the flow pattern in the interblade channel of the impeller was evaluated. The study was carried out by the method of numerical experimentation in the Ansys Workbench Student software environment. Results: The influence of the temperature of the impeller blade row on the compressor impeller characteristics was evaluated. The dependences of the efficiency η and the degree of pressure increase π of the compressor impeller on the speed coefficient Ca were obtained at different values of the blade rim temperature in the range Tb/Ta = 1...2. The results show that the temperature of the blade row does not significantly affect the impeller characteristics. Thus, with an increase in the ratio of the blade row temperature to the ambient temperature, the efficiency η increases by 0.06...0.173%. At the same time, the degree of pressure increase π hardly changes. With an increase in the Ca velocity coefficient, the degree of pressure increase π initially decreases by 0.001...0.003, but then at Tb/Ta = 1.25...2 gradually increased by 0.005 compared with the results obtained when calculating the characteristics of the compressor impeller at Tb/Ta = 1. The scientific novelty and practical significance of the conducted research is that new data on the influence of the impeller blade row temperature on the characteristics of the compressor impeller were obtained. The obtained results can be used to optimize the turbofan attachment of gas turbine engines and to create promising three-circuit gas turbine engines.

Keywords


gas turbine engine; temperature; efficiency; pressure ratio; three-circuit engine; turbofan attachment; impeller; blade row; impeller characteristic; numerical experiment

References


Meng, F., Gong, C., Li, K., Xiong, J., Li, J., & Guo, P. Aerodynamic Optimization and Mechanism Investigation on Performance Improvements in a Transonic Compressor Cascade. Machines, 2023, vol. 11, iss. 2, article no. 244, pp. 1-18. DOI: 10.3390/machines11020244.

Tian, Z., Wang, C., & Zheng, Q. Investigation of the effects of different working fluids on compressor cascade performance. Applied Sciences, 2021, vol. 11, iss. 5, article no. 1989, pp. 1-14. DOI: 10.3390/app11051989.

Bednarz, A., Kuźniar, M., & Boltynjuk, E. Temperature distribution as a method of measuring crack length in fatigue tests of compressor blade. Mechanika, 2016, vol. 33, iss. 293(1/16), pp. 5-16. DOI: 10.7862/rm.2016.1.

Liu, F., Chen, Y., He, C., Li, L., Wang, C., Li, H., Zhang, H., Wang, Q., & Liu, Y. Tensile and very high cycle fatigue behaviors of a compressor blade titanium alloy at room and high temperatures. Materials Science and Engineering: A, 2021, vol. 811, article no. 141049. DOI: 10.1016/j.msea.2021.141049.

Maiboroda, R. Vply`v temperaturnogo pe-repadu na stupin` pidvy`shhennya ty`sku u venty`lyato-rnomu konturi turboventy`lyatornoyi pry`stavky` GTD [Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment]. Aviacijno-kosmichna texnika i texnologiya – Aerospace Technic and Technology, 2023, no. 4sup2 (190), pp. 70-75. DOI: 10.32620/aktt.2023.4sup2.09.

Allali, A., Belbachir, S., Alami, A., Boucham, B., & Lousdad, A. The effect of the outlet angle β 2 on the thermomechanical behavior of a centrifugal compressor blade. Journal of the Mechanical Behavior of Materials, 2020, vol. 29, iss. 1, pp. 1-8. DOI: 10.1515/jmbm-2020-0001.

Tereshhenko, Yu. M., Kuly`k, M. S., Lastivka, I. O., Volyans`ka, L. G., & Tereshhenko, Yu. Yu. Teoriya aviatsiynykh tr'okhkonturnykh turboreaktyv-nykh dvyhuniv [Theory of aircraft three-circuit turbojet engines]. Kyiv, NAU Publ., 2010. 116 p.

Tereshchenko, Yu. M., & Markivs'ka, L. H. Modelyuvannya temperaturnoho stanu dvokh"yarusnoyi lopatky robochoho kolesa turboventylyatornoyi prysta-vky hazoturbinnoho dvyhuna [Modelling of the temperature state of a two-tiered blade of a gas turbine engine turbofan attachment]. Zbirnyk naukovykh prats' Derzhavnoho naukovo-doslidnoho instytutu aviatsiyi [Proc. of the State Research Institute of Aviation], 2020, Vol. 16, iss. 23, pp. 184-188.

Tereshhenko, Yu. M., Kuly`k, M. S., Vo-lyans`ka, L. G., Dmy`triyev, S. O., Panin, V. V., Mitra-xovy`ch, M. M., Grekov, P. I., Kirchu, F. I., Kinashhuk, I. F., & Raty`ns`ky`j, V. V. Teoriya teplovy`x dvy`guniv. Termogazo-dy`namichny`j rozraxunok gazoturbinny`x dvy`guniv : navch. posib [Theory of thermal engines. Thermo-gas-dynamic calculation of gas turbine engines: a manual]. Kyiv, NAU Publ., 2009. 327 p.




DOI: https://doi.org/10.32620/aktt.2024.4sup2.03