Bergh, JSnedden, Glen CReddy, D2020-03-192020-03-192019-09Bergh, J., Snedden, G.C. and Reddy, D. 2019. Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, pp1-15.0957-65092041-2967https://journals.sagepub.com/doi/abs/10.1177/0957650919876730https://doi.org/10.1177/0957650919876730http://hdl.handle.net/10204/11354Copyright: 2019 The Author(s). This is the pre-print version of the work. For access to the published item, kindly consult the publisher's website.Secondary flows are a well-known source of loss in turbomachinery flows, contributing up to 30% of the total aerodynamic blade row loss. With the increase in pressure on aero-engine manufacturers to produce lighter, more powerful and increasingly more efficient engines, the mitigation of the losses associated with secondary flow has become significantly more important than in the past. This is because the production of secondary flow is closely related to the amount of loading and hence work output of a blade row, which then allows part counts and overall engine weight to be reduced. Similarly, higher efficiency engines demand larger engine pressure ratios which in turn lead to reduced blade passage heights in which secondary flows then dominate. This article discusses the design and application of an automated turbine non-axisymmetric endwall contour optimization procedure for the rotor of a low speed, 1-stage research turbine, which was used as part of a research program to determine the most effective objective functions for reducing turbine secondary flows. In order to produce as effective as possible designs, the optimization procedure was coupled to a CFD routine with as high a degree of fidelity as possible and an efficient global optimization scheme based on the so-called EGO algorithm. In order to compliment the requirements of the EGO approach, as well as offset some of the computational requirements of the CFD, the DACE metamodel was used as an underlying surrogate model.enDesign and Analysis of Computer ExperimentsDACEEfficient Global OptimizationEGOKrigingNon-axisymmetric endwallsTurbine optimizationArticleBergh, J., Snedden, G. C., & Reddy, D. (2019). Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design. http://hdl.handle.net/10204/11354Bergh, J, Glen C Snedden, and D Reddy "Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design." (2019) http://hdl.handle.net/10204/11354Bergh J, Snedden GC, Reddy D. Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design. 2019; http://hdl.handle.net/10204/11354.TY - Article AU - Bergh, J AU - Snedden, Glen C AU - Reddy, D AB - Secondary flows are a well-known source of loss in turbomachinery flows, contributing up to 30% of the total aerodynamic blade row loss. With the increase in pressure on aero-engine manufacturers to produce lighter, more powerful and increasingly more efficient engines, the mitigation of the losses associated with secondary flow has become significantly more important than in the past. This is because the production of secondary flow is closely related to the amount of loading and hence work output of a blade row, which then allows part counts and overall engine weight to be reduced. Similarly, higher efficiency engines demand larger engine pressure ratios which in turn lead to reduced blade passage heights in which secondary flows then dominate. This article discusses the design and application of an automated turbine non-axisymmetric endwall contour optimization procedure for the rotor of a low speed, 1-stage research turbine, which was used as part of a research program to determine the most effective objective functions for reducing turbine secondary flows. In order to produce as effective as possible designs, the optimization procedure was coupled to a CFD routine with as high a degree of fidelity as possible and an efficient global optimization scheme based on the so-called EGO algorithm. In order to compliment the requirements of the EGO approach, as well as offset some of the computational requirements of the CFD, the DACE metamodel was used as an underlying surrogate model. DA - 2019-09 DB - ResearchSpace DP - CSIR KW - Design and Analysis of Computer Experiments KW - DACE KW - Efficient Global Optimization KW - EGO KW - Kriging KW - Non-axisymmetric endwalls KW - Turbine optimization LK - https://researchspace.csir.co.za PY - 2019 SM - 0957-6509 SM - 2041-2967 T1 - Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design TI - Development of an automated non-axisymmetric endwall contour design system for the rotor of a 1-stage research turbine - Part 1 System Design UR - http://hdl.handle.net/10204/11354 ER -