Abstract
Using conjugate heat transfer, thermal analysis of a turbine vane coated with thermal barrier coating (TBC) at a high temperature is presented. Numerical results are carried out at two turbine inlet temperatures (T ∞) i.e. 783 K (low) and 1566 K (high) under two turbulence intensities (Tus) i.e. 8.3% and 16.6%. The main findings of this research are that for both Tus, the metal surface temperature reduction at the high temperature is higher than that at the low temperature because of the lower heat-flux ratio at the higher temperature. Based on the metal temperature reduction, the increasing inlet temperature has a greater influence than the increasing turbulence intensity. The results also indicate that at T ∞ = 783 K, on the pressure side (PS) the metal surface temperature reduction at Tu = 8.3% is lower than that at Tu = 16.6%, while on the suction side (SS) no significant difference happens when Tu increases. Interestingly, an inverse phenomenon happens for both PS and SS, that is the metal surface temperature reduction at Tu = 8.3% increases above that at Tu = 16.6% when T ∞ increases. This discrepancy may suggest the instability of the surface heat-flux ratio due to complex heat convection at the different inlet temperatures.
Highlights
It is a well-known fact that to obtain high power output and thermal efficiency, a gas-turbine engine needs to run under high-temperature operating conditions with high thermal load and high turbulence
Based on the metal temperature reduction, the increasing inlet temperature has a greater influence than the increasing turbulence intensity
The results indicate that at T = 783 K, on the pressure side (PS) the metal surface temperature reduction at turbulence intensities (Tus) = 8.3% is lower than that at Tu = 16.6%, while on the suction side (SS) no significant difference happens when Tu increases
Summary
It is a well-known fact that to obtain high power output and thermal efficiency, a gas-turbine engine needs to run under high-temperature operating conditions with high thermal load and high turbulence. Boyle et al [2] Numerical investigated the role of ceramic matrix composites for a high-pressure turbine vane coated with a low conductivity layer thickness of 0.25 mm at 2141 K and 50 atm. Their conclusion was drawn by comparing the stress distribution of the vane with trailing edge ejection to that without trailing edge ejection. The object of this research is to conduct a numerical study and predict thermal analysis of a convectively internal cooling turbine vane coated with a TBC layer at a high temperature. This paper fulfills a real operating condition of using gas turbines in practice
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