[en] The current energy challenges in the field of aircraft propulsion demands a better understanding of turbine flows. The complexity of the flows and the geometrical configurations at play limit the feasibility of experimental investigations in this field. Building predictive numerical methods to capture accurately the flow physics is thus important, even if it still constitutes a challenge. This paper focuses on numerical simulations of high-speed low-pressure turbine blades (HS-LPT), a major component in the framework of high-efficiency geared turbofan engine designs. In this framework,Wall Resolved Large-Eddy Simulations (WRLES) of flows in HS-LPT transonic cascades are performed, using a high order Finite Volume Method (FVM). The Explicit Compressible Solver (ECS) of the massively parallel code "YALES2"is used here. The study focuses on two different cases of low-pressure turbine cascades. First, the well-known T106-C cascade benchmark is studied in order to assess the YALES2 solver for compressible turbomachinery flows. The predictions matches fairly well with those of other numerical codes in the literature and experiments. The second test case investigated is the "SPLEEN"cascade, a next-generation high-speed low-pressure turbine cascade developed by Safran aircraft engines and the von Karman institute for fluid dynamics as a part of a large scale collaborative project. The aim here is to assess the solver for transonic flows, in terms of prediction of the SS separation bubble, the separation-induced laminar-turbulent transition and the wake deficit, using a very detailed experimental database. The results are thus compared with high-fidelity experimental data. This paper shows that the method presented here is able to provide predictive results that can be further used to help in the design LPT blades.
Disciplines :
Engineering, computing & technology: Multidisciplinary, general & others
Author, co-author :
Tene hedje, Patrick ✱; Université de Mons - UMONS > Faculté Polytechniqu > Service de Thermique et Combustion ; Université de Mons - UMONS > Faculté Polytechnique > Service des Fluides-Machines ; VKI - Von Karman Institute for Fluid Dynamics [BE] > Turbomachinery and Propulsion
Ansys Cadence et al. GE International Gas Turbine Institute Rolls Royce
Funding text :
This research benefited from computational resources made available on the Tier-1 supercomputer of the Fédération Wallonie-Bruxelles, infrastructure funded by the Walloon Region under the grantagreement.1117545. IthasbeeninitiatedduringtheEx-treme CFD Workshop (https://ecfd.coria-cfd.fr) partly financedThis research benefited from computational resources made available on the Tier-1 supercomputer of the FédérationWallonie- Bruxelles, infrastructure funded by the Walloon Region under the grant agreement No. 1117545. It has been initiated during the Extreme CFD Workshop (https://ecfd.coria-cfd.fr) partly financed by GENCI. Vincent Moureau, Ghislain Lartigue and Pierre Bénard from CORIA lab are also acknowledged for providing the YALES2 code.The SPLEEN blade is a new HS-LPT blade configuration that has been designed at the von Karman institute for fluid dynamics, in collaboration with Safran aircraft engines, and extensively investigated in the period 2018-2022 within the "Secondary and Leakage Flow Effects in High-Speed Low-Pressure Turbines" project, funded by the Clean Sky 2 Joint Undertaking under the European Union’s Horizon 2020 research and innovation program. It is a blade with a chord = 52.28 , an axial chord = 47.61 and a pitch = 32.95 . The first detailed measurement campaign, collected on a linear cascade, has recently been made available in [36] for isentropic exit Reynolds numbers 2, ranging from 65000 to 120000 and transonic condition (2, = 0.7 − 0.95). For this first numerical campaign, the SPLEEN cascade is investigated for the following isentropic exit flow conditions : 2, = 70000 and 2, = 0.7. This case is listed as ”_1__000_70_070” in the database [36] . The corresponding boundary conditions are 1, = 10779.149 , 1, = 300 and 2, = 7770.989 . The imposed inflow angle is 1 = 36.2◦. This first investigation is carried out on a simplified configuration, i.e. with zero turbulence at the inlet ( = 0%) and without end-walls effects. The computational domain and the mesh use the same methodology as in the case of the T106C cascade. The properties of the mesh are given in Table 2.
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