The Impact of Modeling Assumptions on the Hot Spots Convection Within a Cooled High-Pressure Turbine Stage
| Title | The Impact of Modeling Assumptions on the Hot Spots Convection Within a Cooled High-Pressure Turbine Stage |
| Publication Type | Conference Paper |
| Year of Publication | Submitted |
| Authors | Pinelli L, Giannini G, Pacciani R, Arnone A, Bertini F, Spano E, Marconcini M |
| Conference Name | ASME Turbo Expo 2025 Turbomachinery Technical Conference and Exposition |
| Publisher | ASME |
| Conference Location | Memphis, Tennessee, USA, June 16–20, 2025 |
| Abstract | In order to reduce pollutant emissions, modern aeroengine features combustors that work with lean premixed flames. These combustors generate strong distortions of the flow field and due to their compactness, the combustor-turbine interaction becomes a crucial aspect. From an industrial perspective, it is critical to meet design targets while minimizing the time to market, and, it is therefore necessary to have reliable, effective and efficient design tools. The study presented in this paper employes a state-of-the-art CFD (Computational Fluid Dynamics) in-house code, extensively validated in previous works in the context of combustor-turbine interaction, to investigate the aerodynamics of engine-representative HPT (High-Pressure Turbine) stage mounted in the DLR NG-turb facility and tested during the European project FACTOR. The test case consists in one and-a-half cooled transonic rotating stage, where the distorted flow-field coming from a combustor simulator is applied as inlet boundary condition. In detail, steady/unsteady RANS (Reynolds-Averaged Navier-Stokes) analyses are carried out to investigate a leading edge aligned position between the swirling hot spot and the nozzle guide vanes (leading edge clocking). Predictions obtained with different turbulence models are presented and discussed. The considered closures include a helicity-based correction to baseline models. The numerical results are compared with experimental data, showing overall good agreement. This work demonstrates howperforming URANS simulations featuring modern turbulence closures can correctly estimate the complex aerodynamics of realistic HPT stages and hot-spots migration phenomena, while ensuring computational requirements that are in line with industrial design practices. |
| Notes | GT2025-153665 |
| Refereed Designation | Refereed |