Three-Dimensional Analysis of Turbine Rotor Flow Including Tip Clearance

Heider, R.; Duboue, J. M.; Petot, Bertrand; Billonnet, Gilles; Couaillier, Vincent; Liamis, N.

doi:10.1115/93-gt-111

Cited by 11 publications

(7 citation statements)

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“…In the High condition). These large angular fluctuations are caused by the tip clearance vortex which is driven by a jet of hot gas that leaks from the pressure side towards the suction side of the rotor blade, mostly in the trailing edge region (Heider et al, 1993). The underturning associated to the passage vortex is identified at about 25 % of the span.…”

Section: Unsteady Flow Measurementsmentioning

confidence: 99%

Enhanced performance of fast-response 3-hole wedge probes for transonic flows in axial turbomachinery

et al. 2010

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This contribution presents the development, calibration, and application of a directional, three-sensor fast-response wedge probe for aerodynamic measurements in turbomachines. The probe is equipped with flush-mounted commercial fast-response miniaturized pressure transducers. Angular calibrations cover a wide range of Mach numbers (0.3-0.7). The angular range of the probe and linearity of the calibration maps is enhanced with a novel zonal calibration technique.. The effect of the pressure readings uncertainty on the retrieved flow variables is analyzed for different Mach numbers, and the effect of self-induced perturbations is discussed. The effects of the Reynolds and Mach numbers are studied through spectral analysis of the calibration tests together with CFD simulations. The data reduction methodology is explained and demonstrated with measurements performed in a single-stage high pressure turbine mounted in the compression tube facility of the von Karman Institute. The turbine was operated at subsonic and transonic pressure ratios (2.4 and 5.1) for a Reynolds number of 10 6 , representative of modern engine conditions. Time-resolved angular measurements were obtained at high speed conditions downstream of the rotor and allowed studying secondary flows and the rotor trailing edge shocks for different test conditions.

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Section: Unsteady Flow Measurementsmentioning

confidence: 99%

Enhanced performance of fast-response 3-hole wedge probes for transonic flows in axial turbomachinery

et al. 2010

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“…The numerical aspects of the scheme have already been described on different occasions (see e.g. Heider et al, 1993).…”

Section: Solver Characteristicsmentioning

confidence: 99%

Three-Dimensional Navier-Stokes Prediction of Heat Transfer With Film Cooling

Fougères¹,

Helder²

1994

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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Three-dimensional Navier-Stokes calculations have been performed on various geometries in the presence of discrete-hole injection. The quality of the aerodynamic and thermal predictions of the flow is assessed by comparison to experiments. The code used for the calculations is developed at ONERA and has previously been presented by various authors (Billonnet et al., 1992). It solves the unsteady set of three-dimensional Navier-Stokes equations, completed by a mixing-length turbulence model, using a finite volume technique. The multi-domain approach of the code has facilitated the treatment of this type of geometry. The injection holes are discretized on cylindrical subdomains which overlap the mesh of the main flow. Two applications of the code are presented in this paper. First, a calculation was performed on a row of hot jets injected into a flat plate turbulent boundary layer. Secondly, the code was tested on a plane nozzle guide vane grid with multiple injections. Heat transfer rates, temperature and velocity profiles are compared to experimental data.

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“…The quasi-3D Navier-Stokes code "COLJBRF' is able to give accurate aerodynamic (velocity field, losses, angles) and heat transfer predictions for uncooled or cooled turbines operating in steady or unsteady conditions (Vuillez and Veuillot, 1990;Petot and Fourmaux, 1992;Clianez et al, 1993;D'Hoop et al, 1996). The 3D Navier-Stokes code "CANARF' provides precise aerodynamic and heat transfer solutions for uncooled, film cooled, unshrouded or multi-stage turbines running in steady or unsteady conditions (Petot and Fourmaux, 1992;Heider and Arts, 1994;Fougeres and Heider, 1994;Heider et al, 1993;Billonnet et al, 1995).…”

Section: Introductionmentioning

confidence: 99%

Aero-Thermal Performance Measurements and Analysis of a Two-Dimensional High Turning Rotor Blade

Arts

Duboue²,

Rollin³

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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The purpose of this contribution is to report on the aerothermal performance measurements and calculations carried out around a high pressure gas turbine rotor blade profile mounted in a two-dimensional linear cascade arrangement. The measurements were performed in the CT-2 facility of the von Karman Institute, allowing a correct simulation of the operating conditions encountered in modern aero-engines. Independent variations of exit Mach (0.8 … 1.3) and Reynolds numbers (5 105 … 2 106), free stream turbulence (1 … 6 %) and incidence angle (−14 … +11 deg) provided the definition of a detailed data base of test results. The measured quantities were the blade velocity and convective heat transfer coefficient distributions. The first objective of the paper is to open and analyze this data base which is one of those used at SNECMA for validation purposes. The paper shows the degree of maturity and reliability SNECMA-ONERA Navier-Stokes solvers have now reached for daily use in turbine airfoil design and analysis.

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Three-Dimensional Analysis of Turbine Rotor Flow Including Tip Clearance

Cited by 11 publications

References 0 publications

Enhanced performance of fast-response 3-hole wedge probes for transonic flows in axial turbomachinery

Enhanced performance of fast-response 3-hole wedge probes for transonic flows in axial turbomachinery

Three-Dimensional Navier-Stokes Prediction of Heat Transfer With Film Cooling

Aero-Thermal Performance Measurements and Analysis of a Two-Dimensional High Turning Rotor Blade

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