An Experimental Investigation of Endwall Heat Transfer and Aerodynamics in a Linear Vane Cascade

York, R. E.; Hylton, L. D.; Mihelc, M. S.

doi:10.1115/1.3239529

Cited by 36 publications

(12 citation statements)

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“…It is thought that this is caused by the horseshoe vortex sweeping off the upstream endwall boundary layer and the subsequent start of a new boundary formed by the mainstream, high energy, flow. Results by York et al (1983) on a linear vane cascade have also indicated similar results. Finally, Figure 12 shows a perspective view of the hub endwall intersection with the suction surface of the NGV.…”

Section: Endwallssupporting

confidence: 61%

Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Kingcombe¹,

Harasgama²,

Leversuch³

et al. 1989

Volume 1: Turbomachinery

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A high rim speed turbine, incorporating some 3-D features has been designed and tested at RAE Pyestock. There has been cold flow turbine testing, with overall performance measurements, rotor exit traversing as well as surface static pressure measurements on the vane and rotor. The vane has also been tested in annular cascade on the Isentropic Light Piston Cascade giving surface heat transfer measurements on the vanes and endwalls as well as aerodynamic information. The data have been used to compare with design predictions and the reasons for the differences observed, particularly on the rotor blade, are explored.

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Section: Endwallssupporting

confidence: 61%

Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Kingcombe¹,

Harasgama²,

Leversuch³

et al. 1989

Volume 1: Turbomachinery

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“…Blair(1974), and Boyle and Russell(1990) presented endwall heat transfer distributions obtained in linear cascades for large scale vanes, at relatively low Mach numbers. York et al(1984) obtained similar data, but at transonic Mach numbers. Arts and Heider(1994) presented vane and endwall heat transfer measurements obtained at transonic Mach numbers in an annular cascade with constant radii.…”

Section: Introductionsupporting

confidence: 57%

Heat Transfer Predictions for Two Turbine Nozzle Geometries at High Reynolds and Mach Numbers

Boyle

Jackson²

1995

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

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Predictions of turbine vane and endwall heat transfer and pressure distributions are compared with experimental measurements for two vane geometries. The differences in geometries were due to differences in the hub profile, and both geometries were derived from the design of a high rim speed turbine (HRST). The experiments were conducted in the Isentropic Light Piston Facility (ILPF) at Pyestock at a Reynolds No. of 5.3 × 106, a Mach No. of 1.2, and a wall-to-gas temperature ratio of 0.66. Predictions are given for two different steady state three-dimensional Navier-Stokes computational analyses. C-type meshes were used, and algebraic models were employed to calculate the turbulent eddy viscosity. The effects of different turbulence modeling assumptions on the predicted results are examined. Comparisons are also given between predicted and measured total pressure distributions behind the vane. The combination of realistic engine geometries and flow conditions proved to be quite demanding in terms of the convergence of the CFD solutions. An appropriate method of grid generation, which resulted in consistently converged CFD solutions, was identified.

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“…Under joint NASA-U.S. Air Farce spansorship, measurements were made of enowall Stanton numbers over a range of conditions that included typical engine operating conditions. The results of that work have b,,en summarized 1,y York et al (10).…”

Section: Intruuuctiunmentioning

confidence: 93%

Comparison of Visualized Turbine Endwall Secondary Flows and Measured Heat Transfer Patterns

Gaugler

Russell

1984

Journal of Engineering for Gas Turbines and Power

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Various flow visualization techniques were used to define the secondary flows near the endwall in a large scale turbine vane cascade. The cascade was scaled up from one used to generate endwall heat transfer data under a joint NASA-USAF contract. A comparison of the visualized flow patterns and the measured Stanton number distributions was made for cases where the inlet Reynolds number and exit Mach number were matched. Flows were visualized by using neutrally buoyant helium-filled soap bubbles, by using smoke from oil soaked cigars, and by a new technique using permanent marker pen ink dots and synthetic wintergreen oil. For the first time, details of the horseshoe vortex and secondary flows can be directly compared with heat transfer distributions. Near the cascade entrance, there is an obvious correlation between the two sets of data, but well into the passage the effect of secondary flow is not as obvious.

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An Experimental Investigation of Endwall Heat Transfer and Aerodynamics in a Linear Vane Cascade

Cited by 36 publications

References 0 publications

Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-Speed Transonic Turbine

Heat Transfer Predictions for Two Turbine Nozzle Geometries at High Reynolds and Mach Numbers

Comparison of Visualized Turbine Endwall Secondary Flows and Measured Heat Transfer Patterns

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