Three-dimensional unsteady investigation of HP turbine stages

Adami, Paolo; Martelli, Francesco

doi:10.1243/095765005x69189

Cited by 3 publications

(2 citation statements)

References 24 publications

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“…The stator-rotor rows are matched through a sliding plane approach, properly developed for general unstructured grids [10] and widely assessed for the aero-thermal investigation of HP transonic turbines [11]. A reduced count-ratio approach is applied gathering an exact periodicity among the rows.…”

Section: Numerical Approachmentioning

confidence: 99%

Analysis of the shroud leakage flow and mainflow interactions in high-pressure turbines using an unsteady computational fluid dynamics approach

Adami

Martelli

Cecchi

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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Endwall leakage flows interaction in shrouded high-pressure steam turbines is investigated to provide insights about loss and performances. The prediction of flow through the seal and the understanding of the leakage jet interaction with the main flow is performed using computational fluid dynamics (CFD). A modern research solver is used coupling the labyrinth and the main vane flows including most of the relevant geometric and aerodynamic features. Two similar shroud configurations are here analysed for two high-pressure turbine configurations. Each configuration refers to a different blade technology commonly used by Ansaldo Energia. The computational algorithm is based on a numerical solver developed and applied to solve the compressible Navier-Stokes equations in a multi-rows unsteady environment. The problem has been approached modelling the unsteady 1.5-stage interaction. The CFD results are commented addressing the potential source of losses.

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Section: Numerical Approachmentioning

confidence: 99%

Analysis of the shroud leakage flow and mainflow interactions in high-pressure turbines using an unsteady computational fluid dynamics approach

Adami

Martelli

Cecchi

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The conventional turbulence models offer a good balance between grid resolution requirement and flow field complexity; on the other hand, the large eddy simulation is still prohibitive and probably too detailed to be used for engineering design purposes [20]. Zhou et al [21] used several turbulence models such as Spalart-Allmaras, standard k-ε, kω-SST, and transition kω-SST in studying the effect of the trailing edge of ultrahigh lift lp turbine blades and showed that the two last models provided a good prediction of aerodynamic performance compared with experiments.…”

Section: Turbulence Modelmentioning

confidence: 99%

Characterization of Flow Interactions in a One-Stage Shrouded Axial Turbine

Ghenaiet

2018

International Journal of Aerospace Engineering

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The aim of this paper is to characterize the steady and unsteady flow interactions through a one-stage high-pressure (hp) shrouded axial turbine with a tip cavity. The vane and blade passages were reduced based on the scaling technique, and the domains of compromise were identified and used in the flow computations. The flow structures are mainly in the form of vanes’ wakes and vortices inducing circumferential distortions and interacting with the rotor blades. Fast Fourier transform (FFT) of the static pressure fluctuations recorded at the selected points and lines through the turbine stage revealed high unsteadiness characterized by a space-time periodic behavior, and described by the double Fourier decomposition. The vane-rotor interactions (VRI) appeared in the form of a potential flow field about the blades extending both upstream and downstream and correlated with the rotational speed. The other sources of unsteadiness are induced in the rotor blades by the vanes’ wakes and referred to as the wake interaction, in addition to the secondary flows and vortices in endwall regions.

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Transonic Turbine Stage Heat Transfer Investigation in Presence of Strong Shocks

Loma

Paniagua

Verrastro

et al. 2008

Journal of Turbomachinery

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This paper reports the external convective heat transfer distribution of a modern single-stage transonic turbine together with the physical interpretation of the different shock interaction mechanisms. The measurements have been performed in the compression tube test rig of the von Karman Institute using single- and double-layered thin film gauges. The three pressure ratios tested are representative of those encountered in actual aeroengines, with M2,is ranging from 1.07 to 1.25 and a Reynolds number of about 106. Three different rotor blade heights (15%, 50%, and 85%) and the stator blade at midspan have been investigated. The measurements highlight the destabilizing effect of the vane left-running shock on the rotor boundary layer. The stator unsteady heat transfer is dominated by the fluctuating right-running vane trailing edge shock at the blade passing frequency.

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Three-dimensional unsteady investigation of HP turbine stages

Cited by 3 publications

References 24 publications

Analysis of the shroud leakage flow and mainflow interactions in high-pressure turbines using an unsteady computational fluid dynamics approach

Analysis of the shroud leakage flow and mainflow interactions in high-pressure turbines using an unsteady computational fluid dynamics approach

Characterization of Flow Interactions in a One-Stage Shrouded Axial Turbine

Transonic Turbine Stage Heat Transfer Investigation in Presence of Strong Shocks

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