Boundary layer investigations on a highly loaded transonic compressor cascade with shock/laminar boundary layer interactions

Hilgenfeld, Lothar; Cardamone, Pasquale; Fottner, Leonhard

doi:10.1243/095765003322315405

Cited by 9 publications

(5 citation statements)

References 19 publications

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“…Conventionally, H=2.59 Blasius boundary layer [29] is typical of laminar flows, while H=1.3 to 1.4 is typical of turbulent flows. At x/C=0.3, strong shock-induced boundary layer separation with reattachment is characterized by the significant rise in shape factor in the interaction zone and the steep decrease further downstream [30]. The reattachment in the high Reynolds case is at x/C=0.5 whereas in low Reynolds it is at x/C=0.6.…”

Section: Comparison Of Cascade and Test Sectionmentioning

confidence: 94%

“…Modern aircraft engines with highly loaded transonic compressors have a great potential to minimize the weight and length of an axial compressor by reducing the number of compressor stages [1]. This leads to an increase in flow velocities relative to the blades with supersonic speeds and shock waves upstream and within the blade passages [2].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

Joseph,

Flaszynski,

Doerffer

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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The performance of a highly loaded compressor stator is limited by increased viscous losses caused by operating at a low Reynolds number (Re). The numerical investigation has been carried out on a linear stator cascade profile with an inlet Mach number of 0.9. A test section has been designed based on the extracted streamlines from cascade simulations to perform an experimental investigation of Shock Wave Boundary Layer Interaction (SBLI). Three-dimensional simulations have been carried out on the test section model using a steady state RANS with EARSM turbulence model including transition effects. The low Re number 2.3 × 10 5 case has been investigated on test section configuration and is compared with the high Re number 7.3×10 5 case while maintaining the same Mach inflow conditions. A detailed comparison of boundary layer and SBLI investigations have been performed to analyze the different Reynolds number effects on a representative test section configuration.

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Section: Comparison Of Cascade and Test Sectionmentioning

confidence: 94%

Section: Introductionmentioning

confidence: 99%

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

Joseph,

Flaszynski,

Doerffer

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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“…The compressor cascade V103-220 shown in Figure 4 is chosen as the verification model. It was designed for the hub section of a stator blade in a highly loaded axial compressor (Bell & Fottner, 1995;Hilgenfeld, Cardamone, & Fottner, 2003). This compressor cascade is constructed by conventional NACA-65 blades with a circular camber line.…”

Section: Validation Of Numerical Methodsmentioning

confidence: 99%

“…In view of these facts, the V103-220 compressor cascade is considered to be an appropriate model for investigating inverse design under high subsonic and transonic flow regimes. More detailed information about the test facility and measuring techniques of this compressor cascade can be found in Bell are Fottner (1995) and Hilgenfeld et al (2003).…”

Section: Validation Of Numerical Methodsmentioning

confidence: 99%

Use of computational fluid dynamics to implement an aerodynamic inverse design method based on exact Riemann solution and moving wall boundary

Duan

Zheng

Jiang

2020

Engineering Applications of Computational Fluid Mechanics

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An aerodynamic inverse design method, which is used in compressors, is introduced in this paper. This inverse design method is based on the exact solution of the local Riemann problem on moving blade surfaces. Furthermore, an improved relaxation factor is added to control the induced velocity for reasonable deformation sizes in different cases. The viscous flow analysis and the inverse design are integrated in the computational fluid dynamics software ANSYS Fluent using the dynamic mesh user-defined function, which reduces the time spent on remeshing the computational domain. A compressor cascade is taken to illustrate the effect of this inverse design method. Using the compressor model, the case of a different loading pattern design under a high subsonic flow regime and the case of a loading smooth design under a transonic flow regime have proved the capability of this inverse design method to realize the prescribed pressure loading distribution.

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“…Ratio of total Reynolds stresses to normal Reynolds stresses linear compressor cascade, widely studied in the literature [52,53,54,55,56] and already used as a test case in our previous works [18,19]. The cascade is representative of the mid-span section of a stator blade in a highly loaded axial compressor [52].…”

Section: Test Case Descriptionmentioning

confidence: 99%

Space-dependent turbulence model aggregation using machine learning

Zordo-Banliat¹,

Dergham²,

Merle³

et al. 2023

Preprint

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Computational models of fluid flows based on the Reynolds-averaged Navier-Stokes (RANS) equations supplemented with a turbulence model are the golden standard in engineering applications. A plethora of turbulence models and related variants exist, none of which is fully reliable outside the range of flow configurations for which they have been calibrated. Thus, the choice of a suitable turbulence closure largely relies on subjective expert judgement and engineering know-how. In this article, we propose a data-driven methodology for combining the solutions of a set of competing turbulence models. The individual model predictions are linearly combined for providing an ensemble solution accompanied by estimates of predictive uncertainty due to the turbulence model choice. First, for a set of training flow configurations we assign to component models high weights in the regions where they best perform, and vice versa, by introducing a measure of distance between high-fidelity data and individual model predictions.The model weights are then mapped into a space of features, representative of local flow physics, and regressed by a Random Forests (RF) algorithm. The RF regressor is finally employed to infer spatial distributions of the model weights for unseen configurations. Predictions of new cases are constructed as a convex linear combination of the underlying models solutions, while the between model variance provides information about regions of high model uncertainty. The method is demonstrated for a class of flows through the compressor cascade NACA65 V103 at R e 3 × 10 5 . The results show that the aggregated solution outperforms the accuracy of individual models for the quantity used to inform the RF regressor, and performs well for other quantities well-correlated to the preceding one.The estimated uncertainty intervals are generally consistent with the target high-fidelity data. The present approach then represents a viable methodology for a more objective selection and combination of alternative turbulence models in configurations of interest for engineering practice.

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Boundary layer investigations on a highly loaded transonic compressor cascade with shock/laminar boundary layer interactions

Cited by 9 publications

References 19 publications

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade

Use of computational fluid dynamics to implement an aerodynamic inverse design method based on exact Riemann solution and moving wall boundary

Space-dependent turbulence model aggregation using machine learning

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