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Research Papers

Aerothermal Performance of a Winglet at Engine Representative Mach and Reynolds Numbers

[+] Author and Article Information
D. O. O’Dowd, Q. Zhang, L. He, M. L. G. Oldfield, P. M. Ligrani

Department of Engineering Science, University of Oxford, Parks Road, Oxford, OX1 3PJ, United Kingdom

B. C. Y. Cheong

 Rolls-Royce PLC, Turbine Systems (FH-3), Bristol, BS34 7QE, United Kingdom

I. Tibbott

 Rolls-Royce PLC, Turbine Systems, P.O Box 31, Derby, DE24 8BJ, United Kingdom

J. Turbomach 133(4), 041026 (Apr 26, 2011) (8 pages) doi:10.1115/1.4003055 History: Received June 29, 2010; Revised July 28, 2010; Published April 26, 2011; Online April 26, 2011

This paper presents an experimental and numerical investigation of the aerothermal performance of an uncooled winglet tip, under transonic conditions. Spatially resolved heat transfer data, including winglet tip surface and near-tip side-walls, are obtained using the transient infrared thermography technique within the Oxford high speed linear cascade test facility. Computational fluid dynamics (CFD) predictions are also conducted using the Rolls-Royce HYDRA suite. Most of the spatial heat transfer variations on the tip surface are well-captured by the CFD solver. The transonic flow pattern and its influence on heat transfer are analyzed, which shows that the turbine blade tip heat transfer is greatly influenced by the shock wave structure inside the tip gap. The effect of the casing relative motion is also numerically investigated. The CFD results indicate that the local heat transfer distribution on the tip is affected by the relative casing motion but the tip flow choking and shock wave structure within the tip gap still exist in the aft region of the blade.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

The schematic of the Oxford high speed linear cascade research facility

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Figure 2

Schematic diagrams of the test section and instrumentation

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Figure 3

Schematic of cascade and side-wall heat transfer measurement setup, showing camera positions and the ZnSe window

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Figure 4

The schematic of the test section and winglet tip tested in HSLC (slightly modified from Refs. 8-9)

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Figure 5

An example of heat flux versus temperature history at one location on the tip surface

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Figure 6

Computational domain and grid for winglet

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Figure 7

Experimental Nusselt number

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Figure 8

HYDRA-predicted Nusselt number

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Figure 9

HYDRA-predicted local tip Mach number distributions indicating supersonic flow over the trailing edge

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Figure 10

(a) Experimental adiabatic wall temperature (°C), and (b) isentropic tip Mach number distribution based on experimentally determined recovery (adiabatic) temperature

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Figure 11

HYDRA-predicted tip surface heat flux contours (on the blade surface) and density gradient contours (normal to the blade surface) on an axial cut plane

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Figure 12

Experimental Nusselt number results on suction side near-tip region for (a) winglet tip and (b) flat tip (the dashed line indicates the location of the winglet lip)

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Figure 13

Experimental span-wise-averaged Nusselt number comparison between winglet tip and flat tip for suction side surface

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Figure 14

HYDRA-predicted local total pressure to inlet total pressure ratio, showing over tip leakage vortex for flat tip (left) and winglet tip (right)

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Figure 15

HYDRA-predicted Nusselt number computational results for (a) stationary casing wall and (b) moving casing wall

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Figure 16

HYDRA-predicted local tip Mach number distributions for (a) stationary casing wall and (b) moving casing wall

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Figure 17

Static pressure distributions for the winglet blade with and without moving casing

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