Numerical Characterization of a HP Compressor Stage Equipped With a Closed Shrouded Stator Cavity

Babin, Cedric; Dumas, Michel; Ottavy, Xavier; Fontaneto, Fabrizio

doi:10.1115/1.0003077v

Cited by 1 publication

(4 citation statements)

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“…Both RANS simulations exhibit total pressure peaks at around 20% and 80% span. As shown in Babin et al (2020), these simulations present strong streamline radial migration on the blade pressure and suction side. Local wake thickening and momentum loss is then visible at mid span.…”

Section: Mean Radial Profilesmentioning

confidence: 71%

“…As seen in Figure 3, the cavities C1 and C2 below the rotor are not computed with this RANS approach. It has been shown in (Babin et al , 2020) that these cavities, while operating in closed conditions, have very little impact on the flow in the rotor-stator stage.…”

Section: H25 Compressormentioning

confidence: 99%

“…Figures 6 and 7 present these performances measured in the test rig and predicted by RANS and LBM simulations. Even if RANS simulations data do not include the cavities within the computational domain, it is seen in the study of Babin et al (2020) that this effect is almost negligible on global performances and on radial profiles. The iso-speed line predicted by LBM M1 presents a correct shape with respect to measurements; however, a shift is noticeable in terms of mass flow and pressure ratio.…”

Section: Global Aerodynamics Performancesmentioning

confidence: 99%

“…These existing detailed measurements are used to perform comparisons with LBM simulations results. Moreover, these comparisons are complemented with existing RANS data, obtained on the same configuration (Babin et al , 2020).…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic simulation of a high-pressure compressor stage using the lattice Boltzmann method

Laborderie

Babin

Fontaneto

2021

HFF

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Purpose The present paper aims at evaluating the lattice Boltzmann method (LBM) on a high-subsonic high-pressure compressor stage at nominal regime. Design/methodology/approach The studied configuration corresponds to the H25 compressor operated in a closed-loop test rig at the von Karman Institute. Several operating points are simulated with LBM for two grids of successive refinements. A detailed analysis is performed on the time-averaged flow predicted by LBM, using a comparison with experimental and existing RANS data. Findings The finest grid is found to correctly predict the mean flow across the machine, as well as the influence of the rotor tip gap size. Going beyond time-averaged data, some flow analysis is performed to show the relevance of such a high-fidelity method applied to a compressor configuration. In particular, vortical structures and their evolution with the operating points are clearly highlighted. Spectral analyses finally hint at a proper prediction of tonal and broadband contents by LBM. Originality/value The application of LBM to high-speed turbomachinery flows is very recent. This paper validates one of the first LBM simulations of a high-subsonic high-pressure compressor stage.

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Section: Mean Radial Profilesmentioning

confidence: 71%

Section: H25 Compressormentioning

confidence: 99%

Section: Global Aerodynamics Performancesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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