Thermal behavior of aircraft gas turbine blades under different internal cooling conditions
ISSN: 0148-7191, e-ISSN: 2688-3627
Published January 13, 2020 by SAE International in United States
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Gas turbines are high value-added equipment due to their compact construction, lower weight and high power compared to traditional internal combustion engines. This equipment is subject to high mechanical demands, high temperatures, corrosive and erosive environments, which certainly have a direct influence on its performance. Thus, with the increasing demands of the aerospace industry, it became necessary to use devices to improve their efficiency, such as internal cooling systems and insulation layers. However, a detailed knowledge of the operational variables is necessary in order to define the appropriate internal cooling conditions of the equipment. Thus, the present work aims to analyze, through computational simulations using the finite difference method in its two-dimensional form, the temperature distribution and the heat transfer rate of gas turbine blades under different thermal conditions. The temperature of the hot gas flowing through the blades, as well as the flow and temperature of the cooling air that passes through their internal channels, were varied in order to obtain the influence of each of these factors on the thermal behavior of the blades. It has been observed that a 15% increase in the temperature of the flue gas from 1350K can generate an increase of about 80% in the heat transfer rate for the blade. However, by using an internal cooling air 30% cooler from 1000K, a heat rate dissipation in the blade of about 2.5 times greater can be observed. In addition, an increase in the cooling air flow rate by only 22% can lower the average blade temperature by about 100K. Thus, this demonstrates the importance of using the internal cooling techniques in gas turbines. These techniques associated to the knowledge of the operational variables can greatly influence the heat demand of the blades and, consequently, serve as a basis for future improvements aimed at increasing the overall performance of the equipment.
- L. P. Borlini - Federal Institute of Espírito Santo - IFES
- T. V. Caniçali - Federal Institute of Espírito Santo - IFES
- L. N. Santos - Federal Institute of Espírito Santo - IFES
- J. A. Coelho - Federal Institute of Espírito Santo - IFES
- I. M. Minchio - Federal Institute of Espírito Santo - IFES
- F. A. F. Monhol - Federal Institute of Espírito Santo - IFES
CitationBorlini, L., Caniçali, T., Santos, L., Coelho, J. et al., "Thermal behavior of aircraft gas turbine blades under different internal cooling conditions," SAE Technical Paper 2019-36-0212, 2020.
Data Sets - Support Documents
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