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Research Papers

Deposition Near Film Cooling Holes on a High Pressure Turbine Vane

[+] Author and Article Information
Weiguo Ai, Nathan Murray, Thomas H. Fletcher

Department of Chemical Engineering, Brigham Young University, Provo, UT 84602

Spencer Harding

Department of Mechanical Engineering, Brigham Young University, Provo, UT 84602

Scott Lewis

Department of Mechanical Engineering, Ohio State University, Columbus, OH 43210

Jeffrey P. Bons

Department of Aerospace Engineering, Ohio State University, Columbus, OH 43210

J. Turbomach 134(4), 041013 (Jul 21, 2011) (11 pages) doi:10.1115/1.4003672 History: Received October 12, 2010; Revised November 30, 2010; Published July 21, 2011; Online July 21, 2011

Deposition on film-cooled turbine components was studied in an accelerated test facility. The accelerated deposition facility seeds a natural-gas burning combustor with finely ground coal ash particulate at 1180°C and 180 m/s (M=0.25). Both cylindrical and shaped holes, with and without thermal barrier coating, were studied over a range of blowing ratios from 0.5 to 4.0. Coolant density ratios were maintained at values from 2.1 to 2.4. Deposition patterns generated with the cylindrical film cooling holes indicated regions of low deposition in the path of the coolant with heightened deposition between film holes. This distinctive pattern was more accentuated at higher blowing ratios. Optical temperature measurements of the turbine component surface during deposition showed elevated temperatures between coolant paths. This temperature nonuniformity became more accentuated as deposition increased, highlighting a mechanism for deposition growth that has been documented on in-service turbines as well. The shaped-hole components exhibited little or no deposition in the region just downstream of the holes due to the distributed coolant film. Close cylindrical hole spacing of 2.25d displayed similar behavior to the shaped-hole configuration.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Example of power turbine fouling due to excessive deposition (looking downstream through nozzle guide vane passage)

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Figure 2

Schematic of the BYU turbine accelerated deposition facility

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Figure 3

TADF test coupon holder design with film cooling

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Figure 5

Measured relative spectral response of the SVS285CSCL RGB camera

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Figure 6

Post-test images of deposits on C-M1 coupon at various blowing ratios

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Figure 7

Effect of blowing ratio on net capture efficiency of cylindrical hole metal coupon (C-M1)

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Figure 8

Surface maps of deposit height for C-M1 coupons obtained at three different blowing ratios (hole locations are approximate)

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Figure 9

Coupon front-side temperature map at the blowing ratio of 2.0

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Figure 10

(a) Spanwise distribution of temperature for cylindrical holes at y/d=0.5 and 2 M=1.5. Gray circles represent hole positions. (b) The temperature map for this condition.

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Figure 11

(a) Photo of deposits at high loading in the TADF. (b) Roughness plot of the surface of a deposit on a serviced turbine blade. Note visible “ridges” of deposit between film cooling holes.

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Figure 12

Post-test images of deposits on the shaped-hole coupon at two blowing ratios. Both tests ran for 4 h.

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Figure 13

Temperature map of shaped-hole coupon during deposition testing at M=2.0

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Figure 14

Variation of deposit patterns on the C-TBC surface with blowing ratio from M=0 to M=4 with a deposit thickness map for M=4.0

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Figure 15

Spanwise distribution of temperature for the C-TBC tests at y/d=2.5 and M=0.5, 2.0, and 4.0, respectively. Gray circles are the approximate hole locations.

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Figure 16

Effect of blowing ratio on net capture efficiency of C-TBC coupons with holes 2 and 4 plugged

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Figure 17

Comparison of surface temperature maps from bare metal coupons ((a) and (b)) and TBC coupons ((c) and (d)) with holes 2 and 4 plugged at two blowing ratios

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Figure 18

Deposit development with the elapsing time at the value of M=2.0 (C-TBC test series)

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Figure 19

Influence of blowing ratio (M) on deposit surface coverage at a set particulate loading rate

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Figure 20

Deposition pattern and temperature map of a TBC coupon with five holes with a spacing of 2.25 diameters after 4 h of deposition at M=2.0

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