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TECHNICAL PAPERS

Film Effectiveness Performance of an Arrowhead-Shaped Film-Cooling Hole Geometry

[+] Author and Article Information
Yoji Okita, Masakazu Nishiura

Aero-Engine and Space Operations,  Ishikawajima-Harima Heavy Industries (IHI), Tokyo, Japan

J. Turbomach 129(2), 331-339 (Jun 21, 2006) (9 pages) doi:10.1115/1.2437781 History: Received June 05, 2006; Revised June 21, 2006

This paper presents the first experimental and numerical work of film effectiveness performance for a novel film-cooling method with an arrowhead-shaped hole geometry. Experimental results demonstrate that the proposed hole geometry improves the film effectiveness on both suction and pressure surface of a generic turbine airfoil. Film effectiveness data for a row of the holes are compared to that of fan-shaped holes at the same inclination angle of 35 deg to the surface on a large-scale airfoil model at engine representative Reynolds number and Mach number in a high-speed tunnel with moderately elevated temperature mainstream flow. The film effectiveness data are collected using pressure-sensitive paint. Numerical results show that the coolant film with the proposed hole geometry remains well attached to the surface and diffuses in the lateral direction in comparison with the conventional laidback fan-shaped holes for coolant to mainstream blowing ratios of 0.6–3.5.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of the laidback fan-shaped hole and the arrowhead-shaped hole

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Figure 2

Experimental apparatus

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Figure 3

Details of film-cooling instrumented vane

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Figure 4

Computational domain and mesh in the centerline section

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Figure 5

Comparison of measured film effectiveness contours on the suction surface (SS) between the FSH and ASH, lower BR cases

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Figure 6

Comparison of laterally averaged film effectiveness on the suction surface (SS) between the FSH and ASH, lower BR cases

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Figure 7

Comparison of measured film effectiveness contours on the suction surface (SS) between the FSH and ASH, higher BR cases

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Figure 8

Comparison of laterally averaged film effectiveness on the suction surface (SS) between the FSH and ASH, higher BR cases

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Figure 9

Effect of blowing ratio on overall-averaged film effectiveness with FSH and ASH for the suction surface (SS)

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Figure 10

Comparison of measured film effectiveness contours on the pressure side (PS) between the FSH and ASH, lower BR cases

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Figure 11

Comparison of laterally averaged film effectiveness on the pressure side (PS) between the FSH and ASH, lower BR cases

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Figure 12

Comparison of measured film effectiveness contours on the pressure side (PS) between the FSH and ASH, higher BR cases

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Figure 13

Comparison of laterally averaged film effectiveness on the pressure side (PS) between the FSH and ASH, higher BR cases

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Figure 14

Effect of blowing ratio on overall-averaged film effectiveness with FSH and ASH for the pressure surface (PS)

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Figure 15

Comparison of laterally averaged film effectiveness between experiment and computation, BR=2.3

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Figure 16

Calculated secondary velocity vectors and nitrogen mole fraction contours near the hole exit (X=0.31) on the suction surface, BR=2.3

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