Numerical study on unsteady film cooling performance of turbine rotor considering influences of inlet non-uniformities and upstream coolant

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

“…With the very remarkable advances in the present subject made through the investigations mentioned above and many others available in the literature, all investigated hot-streak shapes in rotating HPT stages were ideal, either circular [25][26][27][28][29] or elliptical [30] . To date, there is only the very recent study by Adams et al [31] that investigated the impact of representative aero-engine combustor exit conditions on a rotating HPT.…”

“…Many studies are now available in the literature [18][19][20][21][22][23][24] . However, works on combined residual swirl and hot-streak effects on rotating HPTs are rare in the literature [25][26][27][28][29][30] . The majority of these works are numerical and they adopt an idealized circular or elliptical hot-streak shapes, which are not representing realistic distorted shapes generated by aero-engine combustors.…”

“…They also concluded that the rotor inlet total temperature profile and rotor blade heat transfer rate were significantly altered under the effects of the swirl. Wang et al [30] conducted a sophisticated CFD analysis of the effects of combined residual swirl and hot-streak on both film-cooled vanes and rotor blades of the GE-E3 turbine. They revealed that under uniform inlet conditions (no swirl and no hot-streak) the film cooling effectiveness fluctuations at the rotor LE are the most important with an amplitude of ±100%.…”

“…Note that Adams et al [31] used a realistic quasi-uniform total pressure distribution that has almost a negligible variation of around ±0.47%. In addition, a constant turbulence intensity I = 10% is imposed at the inlet, which may not be representative to real aero-engine conditions, but this assumption is adopted in many available studies [28][29][30][31] . The inlet length scale is auto-computed by the solver based on the specified turbulence intensity, as follows [38] :…”

Analysis of Rotor–Stator Interaction on the Aerothermal and TBC Insulation Performance of a Turbine Stage under Hot Streak Inlet Condition

“…Although there are many studies on the influencing factors and their influencing mechanisms on the cooling performance of the uncoated vane or blade, there are few studies that have considered the coated vane or blade. Wang et al [7] conducted unsteady numerical simulations on the film-cooled first-stage vane and blade of the GE-E 3 engine HPT. The results showed that unsteady film cooling effectiveness fluctuations at the leading edge (LE) region are the most significant, with the mean-to-peak fluctuation amplitude reaching over ±100%.…”