Effects of the swirling coolant jet from the upstream slot on the vane endwall cooling and the vane suction side phantom cooling

In order to obtain a higher thermal efficiency, the inlet temperature of gas turbines is gradually increased. However, this increases the thermal load on the first stage vane endwall surface. Therefore, an advanced cooling technique must be implemented for the endwall cooling to ensure that the gas turbine operates safely. In the current study, effects of swirling coolant flow from the upstream slot on the endwall cooling and vane suction side surface phantom cooling were numerically investigated on basis of a validated numerical method. Three-dimensional (3D) Reynolds-averaged Navier-Stokes (RANS) equations combined with the shear stress transport (SST) k-ω turbulence model were solved in the numerical simulations. The results indicate that the endwall cooling and the phantom cooling are significantly influenced by introducing a swirling coolant jet from the upstream slot relative to the baseline. Compared with the baseline case and the negative swirling coolant jet angle, the positive swirling coolant jet angle contributes to increase the overall uniformity of the endwall cooling effectiveness and reduce the hot region along the pressure side, especially for the case with α = 20°. However, it obtains a relatively low level of the phantom cooling effectiveness on the vane suction side. In contrast, the negative swirling coolant jet angle attains a higher level of phantom cooling effectiveness on the vane suction side relative to the positive swirling coolant jet angle. The case with α = −20° obtains the largest phantom cooling effectiveness on the vane suction side. In addition, the aerodynamic loss is increased within a small range. The largest total pressure loss coefficient is 5% for the case with α = −30° among all investigated cases.