Effects of free stream turbulence, Reynolds number, and incidence angle on axial turbine cascade performance

Vijayaraghavan, S. B.

doi:10.31274/rtd-180813-10602

Cited by 4 publications

(4 citation statements)

References 3 publications

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“…The aim of validation is to show that the present code used for the analysis is reliable and could be used with confidence for the flow analysis. Experimental results for comparison were taken from Vijayaraghavan [8]. Fig.…”

Section: Validationmentioning

confidence: 99%

Computational Investigation of Effect of Tip Clearance in an Annular Turbine Rotor Impulse Cascade

Goutham Kumar,

Sitaram

2023

joast

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This paper describes three dimensional computational investigations of the effect of the tip clearance on the secondary and tip clearance flows in an annular turbine rotor cascade with non uniform inlet flow. In the actual turbine, the flow at inlet of the rotor is non uniform due to radial pressure gradient acting from the hub to casing. To provide non uniformity at the rotor cascade inlet, an annular nozzle cascade is provided at the upstream. The studies are carried out with the help of a commercially available CFD package. The studies have been carried out for four values of clearance, i.e. 0%, 1%, 3% and 5% of chord. Detailed comparison of the leakage flow direction, pressure gradient, and leakage vortex size, losses, location and interaction with other flow features is carried out. The results are presented in terms of static pressure coefficient distribution on the blade surfaces and total pressure loss coefficient contours in the passage. Spanwise distributions of the circumferentially averaged loss coefficient and flow angle are presented. The extent of losses in the circumferential direction is increased with the increase in the height of the tip clearance but reduced in the spanwise direction. The mass averaged loss coefficient increases rapidly from 0.24 at zero clearance to 0.42 at 1% tip clearance. As the tip clearance is further increased, the losses increase slowly (0.54 at 3% tip clearance to 0.58 at 5% tip clearance). The mass averaged flow angle decreases from 66.3° at zero clearance to 63.7° at 1% clearance to 60.1° at 3% clearance and to 57.3° at 5% clearance.

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Section: Validationmentioning

confidence: 99%

Computational Investigation of Effect of Tip Clearance in an Annular Turbine Rotor Impulse Cascade

Goutham Kumar,

Sitaram

2023

joast

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“…At these flow conditions, axial velocity ratios of 0.93 to 0.97 were maintained across the cascade. More details on the cascade test facility and the cascade pack can be found in Vijayaraghavan (1987).…”

Section: Test Cascade and Instrumentationmentioning

confidence: 99%

“…Also discussed are the test cascade, instrumentation, and testing procedures. Overall cascade performance based on five-hole pressure probe traverses made in an exit plane of the cascade and comparisons with predicted results are presented in a separate paper (Vijayaraghavan and Kavanagh, 1988).…”

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confidence: 99%

Investigation of Boundary Layer Transition and Separation in an Axial Turbine Cascade Using Glue-On Hot-Film Gages

Vijayaraghavan

Kavanagh

1988

Volume 1: Turbomachinery

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“…Of recent investigations devoted to numerical predictions and code validation, Vijayaraghavan and Kavanagh [1] predict the effects of free-stream turbulence level, Reynolds number, and airfoil incidence on axial turbine cascade performance from boundary-layer calculations based on finite-difference analysis. Their calculations are compared with experimental results from oil-flow visualizations and five-hole probe surveys.…”

Section: Introductionmentioning

confidence: 99%

Numerical Predictions of Stanton Numbers, Skin Friction Coefficients, Aerodynamic Losses, and Reynolds Analogy Behavior for a Transsonic Turbine Vane

Zhang

Ligrani

2006

Numerical Heat Transfer, Part A: Applications

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Stanton numbers, skin friction coefficients, aerodynamic losses, and Reynolds analogy behavior are numerically predicted for a turbine vane using the FLUENT commercial code with a k-e RNG model to show the effects of Mach number, mainstream turbulence level, and surface roughness. Test vane geometry, configuration, and flow conditions match ones from a practical application. Comparisons with experimental data on wake aerodynamic losses are made. Numerical and experimental results show that the magnitudes of integrated aerodynamics losses increase dramatically as the exit Mach number increases from 0.35 to 0.71. Downstream wakes are also widened as the mainstream turbulence intensity level, exit Mach number, or level of surface roughness increases. Deviations of numerically predicted 2 St=C f magnitudes from 2 St=C f ffi 1 on the vane suction and pressure sides are also presented for a variety of flow conditions.

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Effects of free stream turbulence, Reynolds number, and incidence angle on axial turbine cascade performance

Cited by 4 publications

References 3 publications

Computational Investigation of Effect of Tip Clearance in an Annular Turbine Rotor Impulse Cascade

Computational Investigation of Effect of Tip Clearance in an Annular Turbine Rotor Impulse Cascade

Investigation of Boundary Layer Transition and Separation in an Axial Turbine Cascade Using Glue-On Hot-Film Gages

Numerical Predictions of Stanton Numbers, Skin Friction Coefficients, Aerodynamic Losses, and Reynolds Analogy Behavior for a Transsonic Turbine Vane

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