Computational Campaign on the MTU T161 Cascade

Rasquin, Michel; Hillewaert, Koen; Colombo, Alessandro; Bassi, Francesco; Massa, Francesco Carlo; Puri, Kunal; Iyer, Arvind S.; Y, Abe; Witherden, Freddie D.; Vermeire, Brian C.; Vincent, Peter

doi:10.1007/978-3-030-62048-6_18

Cited by 2 publications

(2 citation statements)

References 20 publications

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“…In contrast to the extensively investigated T106 cascade, it features diverging end walls as found in real engines, such that the flow cannot be studied using a simple spanwise periodic setup. Its geometry and boundary conditions are in the public domain and it has been the subject of both experimental (Martinstetter et al 2010) and numerical (Müller-Schindewolffs et al 2017;Rasquin et al 2021;Iyer et al 2021) investigations. The numerical studies have focused on operating points with a Mach number of 0.6 and Reynolds numbers of 90 000 and 200 000 based on isentropic exit conditions.…”

Section: Introductionmentioning

confidence: 99%

“…Recently, results including the end wall boundary layers and obtained with a second order Finite Volume (FV) code were presented, but the analysis was focused on the flow physics in the mid-section (Afshar et al 2022). Various computations of the full 3D configuration were conducted using high-order codes during the EU project TILDA (Rasquin et al 2021;Iyer et al 2021). However, due to the specification of laminar end wall boundary layers and no freestream turbulence at the inflow, no satisfactory agreement with the experiment could be obtained.…”

Section: Introductionmentioning

confidence: 99%

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Large Eddy Simulation of a Low Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

Morsbach,

Bergmann,

Tosun

et al. 2023

ERCOFTAC Series

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We present results of implicit large eddy simulation (LES) and different Reynolds-averaged Navier-Stokes (RANS) models of the MTU 161 low pressure turbine at an exit Reynolds number of 90 000 and exit Mach number of 0.6. The LES results are based on a high-order discontinuous Galerkin method and the RANS is computed using a classical finite-volume approach. The paper discusses the steps taken to create realistic inflow boundary conditions in terms of end wall boundary layer thickness and freestream turbulence intensity. This is achieved by tailoring the input distribution of total pressure and temperature, Reynolds stresses and turbulence length scale to a Fourier series based synthetic turbulence generator. With this procedure, excellent agreement with the experiment can be achieved in terms of blade loading at midspan and wake total pressure losses at midspan and over the channel height. Based on the validated setup, we focus on the discussion of secondary flow structures emerging due to the interaction of the incoming boundary layer and the turbine blade and compare the LES to two commonly used RANS models. Since we are able to create consistent setups for both LES and RANS, all discrepancies can be directly attributed to physical modelling problems. We show that both a linear eddy viscosity model and a differential Reynolds stress model coupled with a state-of-the-art correlation-based transition model fail, in this case, to predict the separation induced transition process around midspan. Moreover, their prediction of secondary flow losses leaves room for improvement as shown by a detailed discussion of turbulence kinetic energy and anisotropy fields.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of a Low Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

Morsbach,

Bergmann,

Tosun

et al. 2023

ERCOFTAC Series

View full text Add to dashboard Cite

show abstract

Large Eddy Simulation of a Low-Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

Morsbach,

Bergmann,

Tosun

et al. 2023

Flow Turbulence Combust

View full text Add to dashboard Cite

We present results of implicit large eddy simulation (LES) and different Reynolds-averaged Navier–Stokes (RANS) models of the MTU 161 low pressure turbine at an exit Reynolds number of $$90\,000$$ 90 000 and exit Mach number of 0.6. The LES results are based on a high-order discontinuous Galerkin method and the RANS is computed using a classical finite-volume approach. The paper discusses the steps taken to create realistic inflow boundary conditions in terms of end wall boundary layer thickness and freestream turbulence intensity. This is achieved by tailoring the input distribution of total pressure and temperature, Reynolds stresses and turbulence length scale to a Fourier series based synthetic turbulence generator. With this procedure, excellent agreement with the experiment can be achieved in terms of blade loading at midspan and wake total pressure losses at midspan and over the channel height. Based on the validated setup, we focus on the discussion of secondary flow structures emerging due to the interaction of the incoming boundary layer and the turbine blade and compare the LES to two commonly used RANS models. Since we are able to create consistent setups for both LES and RANS, all discrepancies can be directly attributed to physical modelling problems. We show that both a linear eddy viscosity model and a differential Reynolds stress model coupled with a state-of-the-art correlation-based transition model fail, in this case, to predict the separation induced transition process around midspan. Moreover, their prediction of secondary flow losses leaves room for improvement as shown by a detailed discussion of turbulence kinetic energy and anisotropy fields.

show abstract

Computational Campaign on the MTU T161 Cascade

Cited by 2 publications

References 20 publications

Large Eddy Simulation of a Low Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

Large Eddy Simulation of a Low Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

Large Eddy Simulation of a Low-Pressure Turbine Cascade with Turbulent End Wall Boundary Layers

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