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Research Papers: Flows in Complex Systems

Simulation of the Transitional Flow in a Low Pressure Gas Turbine Cascade With a High-Order Discontinuous Galerkin Method

[+] Author and Article Information
A. Ghidoni

Dipartimento di Ingegneria Meccanica e Industriale,
Università degli Studi di Brescia,
Brescia 25123, Italy
e-mail: antonio.ghidoni@ing.unibs.it

A. Colombo, F. Bassi

Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo,
Dalmine (BG) 24044, Italy

S. Rebay

Dipartimento di Ingegneria Meccanica e Industriale,
Università degli Studi di Brescia,
Brescia 25123, Italy

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received July 13, 2011; final manuscript received July 30, 2012; published online April 17, 2013. Assoc. Editor: Chunill Hah.

J. Fluids Eng 135(7), 071101 (Apr 17, 2013) (8 pages) Paper No: FE-11-1291; doi: 10.1115/1.4024107 History: Received July 13, 2011; Revised July 30, 2012

In the last decade, discontinuous Galerkin (DG) methods have been the subject of extensive research efforts because of their excellent performance in the high-order accurate discretization of advection-diffusion problems on general unstructured grids, and are nowadays finding use in several different applications. In this paper, the potential offered by a high-order accurate DG space discretization method with implicit time integration for the solution of the Reynolds-averaged Navier–Stokes equations coupled with the k-ω turbulence model is investigated in the numerical simulation of the turbulent flow through the well-known T106A turbine cascade. The numerical results demonstrate that, by exploiting high order accurate DG schemes, it is possible to compute accurate simulations of this flow on very coarse grids, with both the high-Reynolds and low-Reynolds number versions of the k-ω turbulence model.

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Figures

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Fig. 1

Coarse grid, 710 quadrilateral elements

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Fig. 2

Detail of the coarse (top) and fine (bottom) grid in the trailing edge region

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Fig. 3

Mach contours, high-Reynolds turbulence model, inlet flow angle α1 = 37.7 deg, P4 approximation, coarse grid

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Fig. 4

Cp distribution along the blade, high-Reynolds turbulence model, α1 = 37.7 deg, coarse grid: numerical and experimental results

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Fig. 5

Cp distribution along the blade, high-Reynolds turbulence model, α1 = 37.7 deg, coarse grid: detail on the suction surface

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Fig. 6

Cp distribution along the blade, high-Reynolds turbulence model, α1 = 37.7 deg, fine mesh: numerical and experimental results

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Fig. 7

Mach contours, low-Reynolds turbulence model, α1 = 37.7 deg, ℙ2 (top) and ℙ4 (bottom) approximation, coarse mesh

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Fig. 8

Cp distribution along the blade, low-Reynolds turbulence model, α1 = 37.7 deg, coarse mesh: numerical and experimental results

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Fig. 9

Cp distribution along the blade, low-Reynolds turbulence model, α1 = 37.7 deg, fine mesh: detail on the suction surface

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Fig. 10

Tu contour lines, low-Re model, ℙ2 (top) and ℙ4 (bottom) approximation, coarse mesh

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Fig. 11

Cf distribution, low-Reynolds turbulence model, coarse mesh

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Fig. 12

Cf distribution detail, low-Reynolds turbulence model, fine mesh

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