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Research Papers

Numerical Study of Deterministic Fluxes in Compressor Passages

[+] Author and Article Information
Feng Wang

Department of Engineering Science,
Oxford Thermofluids Institute,
University of Oxford,
Oxford OX2 0ES, UK
e-mail: feng.wang@eng.ox.ac.uk

Mauro Carnevale

Department of Mechanical Engineering,
University of Bath,
Bath BA2 7AY, UK
e-mail: m.carnevale@bath.ac.uk

Luca di Mare

Department of Engineering Science,
Oxford Thermofluids Institute,
University of Oxford,
Oxford OX2 0ES, UK
e-mail: luca.dimare@eng.ox.ac.uk

1Corresponding author.

2The deterministic stress appears in the momentum equation, and for compressible flows, there are also terms which appear in the energy equation. Together, they will be called deterministic fluxes in the following text.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 12, 2018; final manuscript received September 5, 2018; published online September 28, 2018. Editor: Kenneth Hall.

J. Turbomach 140(10), 101005 (Sep 28, 2018) (11 pages) Paper No: TURBO-18-1158; doi: 10.1115/1.4041450 History: Received July 12, 2018; Revised September 05, 2018

Computational fluid dynamics (CFD) has been widely adopted in the compressor design process, but it remains a challenge to predict the flow details, performance, and stage matching for multistage, high-speed machines accurately. The Reynolds Averaged Navier-Stokes (RANS) simulation with mixing plane for bladerow coupling is still the workhorse in the industry and the unsteady bladerow interaction is discarded. This paper examines these discarded unsteady effects via deterministic fluxes using semi-analytical and unsteady RANS (URANS) calculations. The study starts from a planar duct under periodic perturbations. The study shows that under large perturbations, the mixing plane produces dubious values of flow quantities (e.g., whirl angle). The performance of the mixing plane can be considerably improved by including deterministic fluxes into the mixing plane formulation. This demonstrates the effect of deterministic fluxes at the bladerow interface. Furthermore, the front stages of a 19-blade row compressor are investigated and URANS solutions are compared with RANS mixing plane solutions. The magnitudes of divergence of Reynolds stresses (RS) and deterministic stresses (DS) are compared. The effect of deterministic fluxes is demonstrated on whirl angle and radial profiles of total pressure and so on. The enhanced spanwise mixing due to deterministic fluxes is also observed. The effect of deterministic fluxes is confirmed via the nonlinear harmonic (NLH) method which includes the deterministic fluxes in the mean flow, and the study of multistage compressor shows that unsteady effects, which are quantified by deterministic fluxes, are indispensable to have credible predictions of the flow details and performance of compressor even at its design stage.

Copyright © 2018 by ASME
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Figures

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Fig. 1

Triple decomposition of a velocity signal

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Fig. 2

Schematic of bladerow coupling for the implemented NLH

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Fig. 3

Schematic of the 2D duct case

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Fig. 4

Comparison of mixed-out and time-averaged variables under different Mach numbers, wake orientations, and velocity deficits

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Fig. 5

Geometry and mesh details of the front stages

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Fig. 6

Predicted whirl angle downstream of IGV

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Fig. 7

Axial velocity signal at S1 inlet around middle span using different time steps. The data of two revolutions are shown.

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Fig. 8

Entropy around the middle span section for the front stages

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Fig. 9

Entropy at the IGV exit

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Fig. 10

Left: whirl angle on both sides of the mixing plane. Right: pressure ratio along the span of R1.

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Fig. 11

DS divergence at three axial planes in R1

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Fig. 12

Schematic of the planes to extract deterministic and Reynolds stress divergence

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Fig. 13

Projections of DS and RS divergence on ur around 20% span

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Fig. 14

Projections of DS and RS divergence on ut around 20% span

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Fig. 15

Total pressure profiles in front of S1 and S2 leading edges. The values are normalized by their corresponding values at the middle span.

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