GRX-810 is an oxide dispersion strengthened (ODS) NiCoCr medium entropy alloy developed for extreme environments such as rocket engine-, gas-, and land-based turbine engines and other extreme temperature applications. GRX-810 offers a 200% increase in oxidation resistance 200% increase in ultimate tensile strength and a 1000x increase in creep life at 2000 \(^\circ\) F (1093 \(^\circ\) C) over traditional wrought polycrystalline nickel-based alloys. The substantial increase in creep life offers tremendous advantages to hot gas turbine components. Currently, there is a deficit of data on the application of laser beam powder bed fusion (PBF-LB) manufacturing methods for turbomachinery using the GRX-810 alloy. Turbomachinery for rocket engine applications poses unique challenges for additive manufacturing. The requirements for hot gas turbines often include tight dimensional tolerances, no defects large enough to initiate a crack, and well-controlled surface texture. The performance of turbomachinery is dependent on surface quality and difficult to predict. These challenges require attention in manufacturing planning. The present paper explores the effects of a multitude of surface finishing post processing methods on GRX-810 turbomachinery surface texture, surface defects, aerodynamic performance, and heat transfer while discussing considerations such as dimensional accuracy. Findings indicate varying surface texture from surface finishing post processing of GRX-810 significantly influences the thermal and aerodynamic performance with extremely textured surfaces having lower profile losses overall and generally higher local spatially-resolved heat transfer coefficients.
