Prediction of the Aerodynamic Environment and Heat Transfer for Rotor-Stator Configurations

Griffin, Lisa W.; Mcconnaughey, H. V.

doi:10.1115/89-gt-89

Cited by 4 publications

(2 citation statements)

References 5 publications

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“…An option of specifying the surface (airfoil, hub, and casing) temperatures was added to RAI3DC. This boundary condition is imposed implicitly [as described by Griffin and McConnaughey (1989)] when the surface points are updated and explicitly during post-update corrections.…”

Section: Fig 2 a Rai3dc Stator Gridmentioning

confidence: 99%

Prediction of the Aerodynamic and Thermal Environment in Turbines

Griffin

Belford

1990

Volume 1: Turbomachinery

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A numerical study of the steady, viscous flow prediction capabilities of the three-dimensional turbine stage code R0T0R3 is presented. Computations were performed with RAI3DC, a cascade version of R0T0R3 capable of being run in a planar or annular mode. Computed results are compared with experimental data obtained for Hodson’s cascade, Kopper’s cascade, and United Technologies Research Center’s Large Scale Rotating Rig (LSRR) first-stage stator. The code’s predictive capability is assessed in terms of the accuracy of predicted airfoil loadings, performance (including secondary flows in the LSRR case), boundary layers, and heat transfer. A grid refinement study was conducted in the LSRR case in an effort to more accurately model the boundary layers on the airfoil and endwall surfaces. The effects of the inlet total pressure profile in secondary flow prediction were also assessed.

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Section: Fig 2 a Rai3dc Stator Gridmentioning

confidence: 99%

Prediction of the Aerodynamic and Thermal Environment in Turbines

Griffin

Belford

1990

Volume 1: Turbomachinery

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“…Representative examples of unsteady heat transfer experiments have been published by Dunn and his coworkers (Dunn et al 1984a(Dunn et al ,19846, 1989(Dunn et al , 1990(Dunn et al , 1992, Ashworth et al (1985), Blair (1992) Liu and Rodi (1992), Magari and LaGraff (1992), and others. Representative unsteady hot-streak-flow and unsteady-heat-transfer computations have been performed by Krouthen and Giles (1988), Griffin and McConnaughey (1989), Tran and Taulbee (1992), and Abhari et al (1992).…”

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confidence: 99%

Unsteady-Flow/Quasi-Steady Heat Transfer Computations on a Turbine Rotor and Comparison With Experiments

Korakianitis

Papagiannidis

Vlachopoulos

1993

Volume 2: Combustion and Fuels; Oil and Gas Applications; Cycle Innovations; Heat Transfer; Electric Power; Industrial and Coge

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The unsteady flow in stator-rotor interactions affects the structural integrity, aerodynamic performance of the cascades, and blade-surface heat transfer. Numerous viscous and inviscid computer programs are currently becoming available for the prediction of unsteady flows in two-dimensional and three-dimensional stator-rotor interactions. The relative effects of the various components of flow unsteadiness on heat transfer are currently under investigation. In this paper it is shown that for subsonic cases the reduced frequency parameter for boundary-layer calculations is about two orders of magnitude smaller than the reduced frequency parameter for the core flow. This means that for typical stator-rotor interactions the unsteady flow terms are needed to resolve the location of disturbances in the core flow, but in many cases the instantaneous disturbances can be input in steady-flow boundary-layer computations to evaluate boundary-layer effects in a quasi-steady approximation. This hypothesis is tested by comparing computations with experimental data on a turbine rotor for which there is extensive experimental heat-transfer data available in the open literature. An unsteady compressible inviscid two-dimensional computer program is used to predict the propagation of the upstream stator disturbances into the downstream rotor passages. The viscous wake (velocity defect) and potential flow (pressure fluctuation) perturbations from the upstream stator are modeled at the computational rotor-inlet boundary. The effects of these interactions on the unsteady rotor flow result in computed instantaneous velocity and pressure fields. The period of the rotor unsteadiness is one stator pitch. The instantaneous velocity fields on the rotor surfaces are input in a steady-flow differential boundary-layer program, which is used to compute the instantaneous heat-transfer rate on the rotor blades. The results of these quasi-steady heat-transfer computations are compared with the results of unsteady heat-transfer experiments and with the results of previous unsteady heat-transfer computations. The unsteady flow fields explain the unsteady amplitudes and phases of the increases and decreases in instantaneous heat-transfer rate. It is concluded that the present method is accurate for quantitative predictions of unsteady heat transfer in subsonic turbine flows.

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Unsteady Flow/Quasi-Steady Heat Transfer Computations on a Turbine Rotor and Comparison With Experiments

Korakianitis

Papagiannidis²,

Vlachopoulos³

2001

Journal of Turbomachinery

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The unsteady flow in stator–rotor interactions affects the structural integrity, aerodynamic performance of the stages, and blade-surface heat transfer. Numerous viscous and inviscid computer programs are used for the prediction of unsteady flows in two-dimensional and three-dimensional stator–rotor interactions. The relative effects of the various components of flow unsteadiness on heat transfer are under investigation. In this paper it is shown that for subsonic cases, the reduced frequency parameter for boundary-layer calculations is about two orders of magnitude smaller than the reduced frequency parameter for the core flow. This means that for typical stator–rotor interactions, the unsteady flow terms are needed to resolve the location of disturbances in the core flow, but in many cases the instantaneous disturbances can be input in steady-flow boundary-layer computations to evaluate boundary-layer effects in a quasi-steady approximation. This hypothesis is tested by comparing computations with experimental data on a turbine rotor for which there are extensive experimental heat transfer data available in the open literature. An unsteady compressible inviscid two-dimensional computer program is used to predict the propagation of the upstream stator disturbances into the downstream rotor passages. The viscous wake (velocity defect) and potential flow (pressure fluctuation) perturbations from the upstream stator are modeled at the computational rotor–inlet boundary. The effects of these interactions on the unsteady rotor flow result in computed instantaneous velocity and pressure fields. The period of the rotor unsteadiness is one stator pitch. The instantaneous velocity fields on the rotor surfaces are input in a steady-flow differential boundary-layer program, which is used to compute the instantaneous heat transfer rate on the rotor blades. The results of these quasi-steady heat-transfer computations are compared with the results of unsteady heat transfer experiments and with the results of previous unsteady heat transfer computations. The unsteady flow fields explain the unsteady amplitudes and phases of the increases and decreases in instantaneous heat transfer rate. It is concluded that the present method is accurate for quantitative predictions of unsteady heat transfer in subsonic turbine flows.

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Prediction of the Aerodynamic Environment and Heat Transfer for Rotor-Stator Configurations

Cited by 4 publications

References 5 publications

Prediction of the Aerodynamic and Thermal Environment in Turbines

Prediction of the Aerodynamic and Thermal Environment in Turbines

Unsteady-Flow/Quasi-Steady Heat Transfer Computations on a Turbine Rotor and Comparison With Experiments

Unsteady Flow/Quasi-Steady Heat Transfer Computations on a Turbine Rotor and Comparison With Experiments

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