Research Papers

Inlet Condition Effects on the Tip Clearance Flow With Zonal Detached Eddy Simulation

[+] Author and Article Information
William Riéra

e-mail: william.riera@onera.fr

Lionel Castillon

e-mail: lionel.castillon@onera.fr

Julien Marty

e-mail: julien.marty@onera.fr
Onera – The French Aerospace Lab,
Meudon F-92190, France

Francis Leboeuf

Ecole Centrale De Lyon,
Laboratory of Fluid Mechanics and
Acoustics, Ecully 69034, France
e-mail: francis.leboeuf@ec-lyon.fr

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 3, 2013; final manuscript received July 8, 2013; published online October 25, 2013. Editor: Ronald Bunker.

J. Turbomach 136(4), 041018 (Oct 25, 2013) (10 pages) Paper No: TURBO-13-1130; doi: 10.1115/1.4025216 History: Received July 03, 2013; Revised July 08, 2013

In the present study, the influence of the inlet condition on the tip clearance flow of an axial compressor is investigated. Two different zonal detached eddy simulations (ZDES) computations are carried out and compared to Reynolds-averaged Navier–Stokes (RANS) and unsteady RANS (URANS) computations as well as to experimental data. A rotating distortion map of the flow cartography is set as inlet condition for the first ZDES computation. An azimuthally averaged inlet condition is used for the second one and uncouples the rotor tip-leakage vortex flutter phenomenon, which stems from the arrival of the inlet guide vane wake from the behavior inherent to the rotor tip-leakage vortex. In the studied configuration, the inlet guide vane tip vortex reveals to lower the effects from double leakage on the rotor. The topology of the rotor tip-leakage vortex is described, and its development is analyzed.

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Fig. 3

Mesh configuration for the ZDES modes on rotor 1 of CREATE. Blade-to-blade view. Upstream domain: mode = 0. Downstream domain: mode = 1. Blade vicinity and tip gap region: mode = 2.

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Fig. 2

Computational domain for the calculations on the first rotor of CREATE

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Fig. 1

CREATE compressor meridian view

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Fig. 4

Classification of typical flow problems. (a) Separation fixed by the geometry, (b) separation induced by a pressure gradient on a curved surface, (c) separation strongly influenced by the dynamics of the incoming boundary layer (extracted from Ref. [12]).

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Fig. 8

Entropy planes for four different axial positions at time = 3T/4. (Left: URANS, middle: ZDES, right: ZDES-averaged map.)

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Fig. 5

Total pressure at section 25A

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Fig. 6

Total pressure at section 26A for the different computation and experimental data (with uncertainties for the unsteady probes)

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Fig. 7

Snapshots of Q criterion isosurface colored by the normalized helicity and section 31% X/C filled with the entropy. (Left: URANS, middle: ZDES, right: ZDES-averaged map.)

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Fig. 9

Averaged normalized axial velocity at 91% X/C and 90% relative height

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Fig. 10

Averaged normalized circumferential velocity at 91% X/C and 90% relative height

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Fig. 11

Probes position. Instantaneous Schlieren at 98% relative height and T = 3T/4, ZDES with rotating distortion.

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Fig. 12

Power spectral density (PSD) (a and b) and normalized power spectral density (c and d) of static pressure for probes along the tip-leakage vortex




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