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- W4308734290 abstract "In this paper, through the heat transfer experiment of a certain type of aero-engine turbine guide vane, the numerical simulation of gas-heat coupling is carried out using CFX. At the same time, the improvement of the aerodynamic heat transfer calculation of the high-pressure turbine guide vane provides a numerical calculation for the numerical simulation of the heat transfer of the blade air-cooled structure. The thermal stress distribution of the vanes shows that the place where the load is relatively large is also the place where the vanes are prone to be damaged, and the thermal stress of the trailing edge is longer than that of the leading edge. Compared with the temperature and stress field, the maximum stress of the vane is present at the end, but it is not easy to produce structural damage, but the temperature and stress are relatively high, so it is more likely to cause heat damage. The predicted results are the same as those where the actual turbine vanes are prone to being damaged." @default.
- W4308734290 created "2022-11-15" @default.
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- W4308734290 date "2022-10-01" @default.
- W4308734290 modified "2023-09-27" @default.
- W4308734290 title "Research of Thermal Stress on a High Pressure Turbine Guide Vane During the Start-Up Period" @default.
- W4308734290 cites W2050767346 @default.
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- W4308734290 doi "https://doi.org/10.1109/icmeas57305.2022.00061" @default.
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