59269 - Uncertainty Analysis of Film Cooling of Fan-Shaped Holes on a Stator Vane Under Realistic Inlet Conditions 

The uncertainty caused by the operating condition of gas turbine impacts directly on film cooling performance, and even the life of hot-section components. This paper presents an investigation on the influences of the inlet parameters of a realistic engine vane on film cooling effectiveness of fan-shaped holes using uncertainty quantification technique. The input parameters include mainstream pressure and temperature, coolant pressure and temperature, and they are assumed to be normal distributions. Surrogate model for the film cooling is established by radial basis function neural network, and the statistical characteristics of outputs are determined by Monte Carlo simulation. The quantitative analysis shows that, on the pressure surface of the vane, a maximum value of 61.6% uncertainty degree of laterally averaged adiabatic cooling effectiveness (η_ad,lat) locates at about 4.0 diameters of the downstream of the film hole exit; however, the maximum uncertainty degree of η_ad,lat is only 4.5% on the suction surface of the vane. Furthermore, the probability density function of the area-averaged effectiveness is of highly left-skewed distribution on the pressure surface. The sensitivity analysis indicates that, the variation in the mainstream pressure has the most pronounced effect on the cooling effectiveness, while the effect of the mainstream temperature is unobvious.