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Research Papers

Heat Transfer Enhancement Using Angled Grooves as Turbulence Promoters

[+] Author and Article Information
Krishnendu Saha

Turbine Innovation and Energy Research (TIER)
Center,
Mechanical Engineering Department,
Louisiana State University,
Baton Rouge, LA 70803

Sumanta Acharya

Turbine Innovation and Energy Research (TIER)
Center,
Mechanical Engineering Department,
Louisiana State University,
Baton Rouge, LA 70803
e-mail: acharya@tigers.lsu.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 4, 2013; final manuscript received September 1, 2013; published online January 31, 2014. Editor: Ronald Bunker.

J. Turbomach 136(8), 081004 (Jan 31, 2014) (10 pages) Paper No: TURBO-13-1179; doi: 10.1115/1.4025733 History: Received August 04, 2013; Revised September 01, 2013

An experimental study is conducted on a simulated internal cooling channel of a turbine airfoil using angled grooves and combination of grooves-ribs to enhance the heat transfer from the wall. The grooves are angled at 45 deg to the mainstream flow direction and combinations of four different geometries are studied that include (1) angled grooves with a pitch, p/δ = 10, (2) angled groove with a larger pitch, p/δ = 15, (3) combination of angled groove and 45 deg angled rib, and (4) combination of angled groove with transverse rib. Transient liquid crystal experiments are conducted for a Reynolds number range of 13,000–55,000, and local and averaged heat transfer coefficient values are presented for all the geometries. Pressure drops are measured between the inlet and the exit of the grooved channel and friction factors are calculated. The combination of the angled groove and 45 deg angled rib provided the highest performance factor of the four cases considered, and these values were higher or comparable to among the best-performing rib geometries (45 deg broken ribs) commonly used in gas turbine airfoils.

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Figures

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Fig. 1

Schematic of the experimental setup

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Fig. 2

Schematic of the geometries studied

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Fig. 3

Experimental Nu/Nu0 contour map for the angled groove-small pitch case, Re = 40,000 (peak values reach about 3.5). The edge of the angled groove is shown by white dashed lines.

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Fig. 4

Comparison between experimental and numerical data at Re = 25,000

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Fig. 5

Streamlines and turbulence intensity (2k/3/V) in groove (top) and above test surface (numerical data)

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Fig. 6

Streamline profile and turbulence intensity across groove planes 1, 2, 3 (numerical data); note the cross section planes extend from one wall to the other

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Fig. 7

Experimental spanwise Nu/Nu0 distribution at different streamwise locations for angled groove-small pitch case (Re = 25,000)

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Fig. 8

Experimental Nu/Nu0 contour map for the angled groove-large pitch case Re = 40,000 (peak values reach about 3.5)

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Fig. 9

Experimental Nu/Nu0 contour map for the angled groove-angled rib case Re = 40,000 (note: color scale is capped at 4 to show comparison with other contours; peak values reach about 8)

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Fig. 10

Experimental Nu/Nu0 contour map for the angled groove-straight rib case Re = 40,000

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Fig. 11

Zonal averaged Nu/Nu0 for the configurations tested (Re = 25,000)

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Fig. 12

Total averaged Nu/Nu0 for configurations tested

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Fig. 13

Friction factor ratio comparison

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Fig. 14

TPF of the geometries studied

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Fig. 15

TPF comparison with some standard and innovative rib designs

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