Film Cooling Performance Prediction for Air and Supercritical CO2

The current study explores the possibility of cooling the vanes and blades of a direct-fired sCO(2) turbine using film cooling. The operating conditions of a direct-fired sCO(2) cycle and thermophysical properties of the fluid at those conditions can alter the flow field characteristics of the coolant jet and its mixing with the mainstream. Very little information is present in the literature regarding the performance of film cooling geometries employing supercritical CO2. The objective of this study is to estimate the resulting film cooling effectiveness while also capturing the effects of the crossflow-to-mainstream velocity ratio on the coolant jet. A computational fluid dynamic model is used to study the coolant jet exiting a cylindrical hole located on a flat plate, with the coolant fed by an internal channel. Steady-state Reynolds-averaged Navier-Stokes equations were solved along with the (shear-stress transport) SST k-omega model to provide the turbulence closure. The operating conditions for the direct-fired sCO(2) turbine are obtained using an in-house Cooled Turbine Model. Numerical predictions revealed that the crossflow effects and jet lift-off were more pronounced in the case of sCO(2) when compared to air. Spatial distribution of flow field and cooling effectiveness are presented at different operating conditions.

Automated summary

This study investigates the possibility of cooling the vanes and blades of a direct-fired sCO(2) turbine using film cooling. The operating conditions and fluid properties of the direct-fired sCO(2) cycle can affect the flow characteristics and mixing of the coolant jet. Limited information is available on the performance of film cooling using supercritical CO2. The study aims to estimate film cooling effectiveness and the impact of crossflow-to-mainstream velocity ratio on the coolant jet, using computational fluid dynamics and a cooled turbine model.