Simulation of 3D-Unsteady Stator/Rotor Interaction in Turbomachinery Stages of Arbitrary Pitch Ratio

Jung, Alexander; Mayer, Jürgen F.; Stetter, H.

doi:10.1115/96-gt-069

Cited by 23 publications

(7 citation statements)

References 9 publications

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“…The equations solved are the fully three-dimensional, unsteady, Favre-averaged Navier-Stokes equations. They are written for a cylindrical coordinate system that rotates at constant angular velocity, see Jung et al (1996). The fluid is assumed to behave as an ideal gas with a constant ratio of specific heat capacities.…”

Section: Flow Solver Itsm3dmentioning

confidence: 99%

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Walraevens

Gallus

Jung

et al. 1998

Volume 1: Turbomachinery

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A study of the unsteady flow in an axial flow turbine stage with a second stator blade row is presented. The low aspect ratio blades give way to a highly three-dimensional flow which is dominated by secondary flow structures. Detailed steady and unsteady measurements throughout the machine and unsteady flow simulations which include all blade rows have been carried out. The presented results focus on the second stator flow. Secondary flow structures and their origins are identified and tracked on their way through the passage. The results of the time-dependent secondary velocity vectors as well as flow angles and Mach number distributions as perturbation from the time-mean flow field are shown in cross-flow sections and azimuthal cuts throughout the domain of the second stator. At each location the experimental and numerical results are compared and discussed. A good overall agreement in the time-dependent flow behaviour as well as in the secondary flow structures is stated. ' fluctuation

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Section: Flow Solver Itsm3dmentioning

confidence: 99%

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Walraevens

Gallus

Jung

et al. 1998

Volume 1: Turbomachinery

Self Cite

View full text Add to dashboard Cite

show abstract

“…The equations solved are the fully three-dimensional, unsteady, Favre-averaged Navier-Stokes equations. The set of equations is written for a cylindrical coordinate system that rotates at constant angular velocity, see Jung et al (1996). The fluid is assumed to behave as an ideal gas with a constant ratio of specific heat capacities.…”

Section: Methodsmentioning

confidence: 99%

Prediction of 3D-Unsteady Flow in an Air Turbine and a Transonic Compressor Including Blade Gap Flow and Blade Row Interaction

Jung

Mayer

Stetter

1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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This paper presents the results of three-dimensional unsteady Navier-Stokes simulations of the flow in a transonic compressor stage with inlet guide vanes and an axial flow air turbine stage with two identical stators for which detailed unsteady experimental data are available. Various unsteady flow phenomena are shown. The focus in the computations are stator/rotor interaction effects. Of special interest are their influences on the flow field downstream of the interface regions. The secondary flow effects are visualized via vector plots. The numerical results are compared with the experimental results. Although there is a good agreement in the major flow phenomena local deviations can be observed.

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“…Phase lagged boundary conditions were used at the interface by He and Denton [29], Gerolymos et al [30], Van Zante et al [31], Shyam et al [32]. Another method is the time-inclining technique studied by Giles [33], Jung et al [34], and Zhou et al [35].…”

Section: Computational Featuresmentioning

confidence: 99%

Computational Validation of the Flow Through a Turbine Stage and the Effects of Rim Seal Cavity Leakage on Secondary Flows

Turgut

Camcı

2012

Volume 8: Turbomachinery, Parts A, B, and C

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A computational validation study related to aerodynamic loss generation mechanisms is performed in an axial flow turbine. The 91.66 cm diameter axial flow turbine research facility has a stationary nozzle guide vane assembly and a 29 bladed HP turbine rotor. The NGV inlet and exit Reynolds numbers based on midspan axial chord are around 300000 and 900000, respectively. GRIDPRO is used as the structured grid generator. y+ values are kept below unity. The finite-volume flow solver ANSYS CFX with SST k–ω turbulence model together with the transitional flow model is employed. Experimental flow conditions are imposed at the boundaries. The computational predictions are compared to experimental data at NGV exit plane and rotor inlet plane. NGV exit plane measurements come from a previous experimental study with a five-hole probe and the data at rotor inlet plane is taken by the current authors using a Kiel probe with 3.175mm head diameter. The comparison of rotor-stator interface models shows that the stage model, which calculates the circumferentially averaged fluxes and uses as the boundary condition at the interface plane, agrees well with the experimental total pressure coefficient data at the NGV exit. The difference between the NGV only simulation and the rotor-stator simulation is emphasized. The effect of rim seal flow on the mainstream aerodynamics is investigated. This validation study shows that the effect of future geometrical modifications on the endwalls and the vane will be predicted reasonably accurately.

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Simulation of 3D-Unsteady Stator/Rotor Interaction in Turbomachinery Stages of Arbitrary Pitch Ratio

Cited by 23 publications

References 9 publications

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Prediction of 3D-Unsteady Flow in an Air Turbine and a Transonic Compressor Including Blade Gap Flow and Blade Row Interaction

Computational Validation of the Flow Through a Turbine Stage and the Effects of Rim Seal Cavity Leakage on Secondary Flows

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