In order to improve the engine reliability and efficiency, an effective way is to reform the turbine blade tip conformation. The paper aims to discuss this issue.
The present research provides several novel tip-shaping structures, which are considered to control the blade tip loss. Four different tip geometries have been studied: flat tip, squealer tip, flat tip with streamwise ribs and squealer tip with streamwise ribs. The tip heat transfer and leakage flow are both analyzed in detail, for example the tip heat transfer coefficient, tip flow and local pressure distributions.
The results show that the squealer seal and streamwise rib can reduce the tip heat transfer and leakage loss, especially for the squealer tip with streamwise ribs. The tip and near-tip flow patterns at the different locations of axial chord reflect that both the squealer seal and streamwise rib structure can control the tip leakage flow loss. In addition, the analysis of the aerodynamic parameters (the static pressure and turbine efficiency) also indicates that the squealer tip with streamwise ribs obtains the highest adiabatic efficiency with an increase of 2.34 percent, compared with that of the flat tip case.
The analysis of aerothermal and dynamic performance can provide a reference for the blade tip design and treatment.
This work is supported by the National Natural Science Foundation of China (Grant No. 51575444), Aerospace Science and Technology Foundation (Grant No. 2017-HT-XGD) and Aviation Power Foundation (Grant No. 6141B090319).
Tong, F., Gou, W., Li, L., Yue, Z., Gao, W. and Li, H. (2019), "Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance", Multidiscipline Modeling in Materials and Structures, Vol. 15 No. 6, pp. 1121-1135. https://doi.org/10.1108/MMMS-03-2019-0053Download as .RIS
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