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G. sand or cones) employed in previous studies. Surface Roughness Measurement and Fabrication In preparation for the current study, nearly 100 land-based turbine components were assembled from four manufacturers: General Electric, Solar Turbines, SiemensWestinghouse, and Honeywell (formerly Allied-Signal) Corporation. The articles were selected by each manufacturer to be representative of surface conditions generally found in the land-based gas turbine inventory. Chord dimensions on the assembled blades and vanes ranged from 2 to 20cm and included samples with thermal barrier coatings (TBC).

For all cases, the blade Reynolds number, Re c, was approximated at 2x106 . This is in the range of values cons idered typical for high pressure turbine vanes/blades as reported by other researchers [4,13]. 097δ from a power- law boundary layer profile]. Admittedly, this estimate is an oversimplification. Turbine blade boundary layers are not turbulent from the leading edge and they are subject to pressure gradients, transonic Mach numbers, freestream turbulence, and (of course) roughness. 5 to 3) are comparable to those obtained by more sophisticated means [20,21] (see Table 1).

9 St Measurement : For the heat transfer measurements, a FLIR Thermacam SC 3000 infrared camera system is mounted with the lens fit into a hole in the plexiglass ceiling of the tunnel. 03°C (at 30°C) and allows framing rates of approximately one Hz. At the focal distance of 37 cm, the camera field of view is roughly 70 x 90 mm. 20m from the leading edge of the tunnel floor. 18m). The 320 x 240 pixels of the FLIR camera allowed excellent resolution of the roughness features during the transient experiments.

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