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Research Papers

A Novel Antivortex Turbine Film-Cooling Hole Concept

[+] Author and Article Information
James D. Heidmann

 NASA Glenn Research Center, Cleveland, OH 44135

Srinath Ekkad

 Louisiana State University, Baton Rouge, LA 70803

J. Turbomach 130(3), 031020 (May 06, 2008) (9 pages) doi:10.1115/1.2777194 History: Received June 07, 2007; Revised June 18, 2007; Published May 06, 2008

A novel turbine film-cooling hole shape has been conceived and designed at NASA Glenn Research Center. This “antivortex” design is unique in that it requires only easily machinable round holes, unlike shaped film-cooling holes and other advanced concepts. The hole design is intended to counteract the detrimental vorticity associated with standard circular cross-section film-cooling holes. This vorticity typically entrains hot freestream gas and is associated with jet separation from the turbine blade surface. The antivortex film-cooling hole concept has been modeled computationally for a single row of 30 deg angled holes on a flat surface using the 3D Navier–Stokes solver GLENN-HT . A blowing ratio of 1.0 and density ratios of 1.05 and 2.0 are studied. Both film effectiveness and heat transfer coefficient values are computed and compared to standard round hole cases for the same blowing rates. A net heat flux reduction is also determined using both the film effectiveness and heat transfer coefficient values to ascertain the overall effectiveness of the concept. An improvement in film effectiveness of about 0.2 and in net heat flux reduction of about 0.2 is demonstrated for the antivortex concept compared to the standard round hole for both blowing ratios. Detailed flow visualization shows that as expected, the design counteracts the detrimental vorticity of the round hole flow, allowing it to remain attached to the surface.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Counter-rotating vortex pair and jet lift-off (from Haven (11))

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Figure 2

Initial antivortex design (top view)

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Figure 3

Initial antivortex design (side view)

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Figure 4

Initial antivortex design (front view)

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Figure 5

Modified antivortex design (top view)

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Figure 6

Modified antivortex design (side view)

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Figure 7

Modified antivortex design (front view)

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Figure 8

Computational grid for baseline round hole case

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Figure 9

Hole intersection grid close-up

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Figure 10

Stagnation temperature (T∕Tin), x∕d=7 (Case 1)

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Figure 11

Stagnation temperature (T∕Tin), xd=7 (Case 3)

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Figure 12

Stagnation temperature (T∕Tin), x∕d=7 (Case 4)

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Figure 13

Stagnation temperature (T∕Tin), x∕d=7 (Case 6)

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Figure 14

Secondary flow vectors colored by temperature (T∕Tin), x∕d=7 (Case 1)

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Figure 15

Secondary flow vectors colored by temperature (T∕Tin), x∕d=7 (Case 3)

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Figure 16

Area-averaged streamwise vorticity

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Figure 17

Film effectiveness η (Cases 1–6)

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Figure 18

Heat transfer coefficient h∕ho (Cases 1–6)

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Figure 19

Span-averaged film effectiveness

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Figure 20

Span-averaged heat transfer coefficient

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