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Research Papers

Development of a Novel Mixing Plane Interface Using a Fully Implicit Averaging for Stage Analysis

[+] Author and Article Information
Lucian Hanimann

Lucerne University of Applied Sciences and Arts,
Engineering and Architecture,
Technikumstrasse 21,
Horw 6048, Switzerland
e-mail: lucian.hanimann@hslu.ch

Luca Mangani, Ernesto Casartelli

Lucerne University of Applied Sciences and Arts,
Engineering and Architecture,
Technikumstrasse 21,
Horw 6048, Switzerland

Thomas Mokulys, Sebastiano Mauri

MAN Diesel and Turbo Schweiz AG,
Hardstrasse 319,
Postfach 2602
Zurich 8021, Switzerland

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 27, 2013; final manuscript received December 14, 2013; published online January 31, 2014. Editor: Ronald Bunker.

J. Turbomach 136(8), 081010 (Jan 31, 2014) (14 pages) Paper No: TURBO-13-1264; doi: 10.1115/1.4026323 History: Received November 27, 2013; Revised December 14, 2013

This paper describes the development and validation steps of a characteristics-based explicit along with a novel fully implicit mixing plane implementation for turbomachinery applications. The framework is an unstructured 3D RANS in-house modified solver, based on open-source libraries. Particular attention was paid to mass-conservation, accurate variables interpolation, and algorithm stability in order to improve robustness and convergence. By introducing a specific interface, allowing the use of algebraic multigrid solvers together with multiprocessor computation, a speed up of the numerical solution procedure was achieved. The validation of both mixing plane algorithms is carried out on an industrial radial compressor and a cold air 1.5 stages axial turbine.

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Figures

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Fig. 1

Concept of mixing plane averaging

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Fig. 2

Labeling convention

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Fig. 3

Data path for agglomerated levels

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Fig. 4

Agglomeration of the faces

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Fig. 5

Multiprocessor distribution

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Fig. 6

Axial fan with backflow

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Fig. 7

Computational domains with cutting planes

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Fig. 8

Entropy rise in streamwise direction

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Fig. 9

Total pressure rise in streamwise direction

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Fig. 10

Comparison of the speed lines against the measurement

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Fig. 11

Pressure rise in the rotor and stator

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Fig. 12

Velocity profiles at CP1: (a) CC1; (b) implicit mixing plane

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Fig. 13

Contours of entropy at CP1: (a) CC1 frozen rotor; (b) CC1 mixing plane; (c) implicit mixing plane; (d) explicit mixing plane

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Fig. 14

Contours of enthalpy at CP1: (a) CC1 frozen rotor; (b) CC1 mixing plane; (c) implicit mixing plane; (d) explicit mixing plane

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Fig. 15

Contours of total pressure at CP1: (a) CC1 frozen rotor; (b) CC1 mixing plane; (c) implicit mixing plane; (d) explicit mixing plane

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Fig. 16

Computational domain with cutting planes

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Fig. 17

Absolute flow angle at CP1

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Fig. 18

Absolute flow angle at CP2

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Fig. 19

Absolute flow angle at CP3

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Fig. 20

Contours of total pressure at CP4 for the first interface: (a) mixing plane 1, CC1; (b) mixing plane 1, implicit

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Fig. 21

Contours of total pressure at CP4 for the second interface: (a) mixing plane 2, CC1; (b) mixing plane 2, implicit

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Fig. 23

Explicit separation

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Fig. 24

Implicit separation

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Fig. 25

Unstructured mixing plane boundary

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Fig. 26

Detail of transformed interface

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