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Research Papers

Effects of Effusion Cooling Pattern Near the Dilution Hole for a Double-Walled Combustor Liner—Part II: Flowfield Measurements

[+] Author and Article Information
Adam C. Shrager

Mem. ASME
Department of Mechanical and Nuclear
Engineering,
The Pennsylvania State University,
127 Reber Building,
University Park, PA 16802
e-mail: adam.shrager@gmail.com

Karen A. Thole

Mem. ASME
Department of Mechanical and Nuclear
Engineering,
The Pennsylvania State University,
136 Reber Building,
University Park, PA 16802
e-mail: kthole@psu.edu

Dominic Mongillo

Pratt & Whitney,
400 Main Street,
East Hartford, CT 06118
e-mail: dominic.mongillo@pw.utc.com

1Corresponding author.

Manuscript received July 8, 2018; final manuscript received July 23, 2018; published online October 15, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(1), 011023 (Oct 15, 2018) (10 pages) Paper No: GTP-18-1464; doi: 10.1115/1.4041153 History: Received July 08, 2018; Revised July 23, 2018

The complex flowfield inside a gas turbine combustor creates a difficult challenge in cooling the combustor walls. Many modern combustors are designed with a double-wall that contain both impingement cooling on the backside of the wall and effusion cooling on the external side of the wall. Complicating matters is the fact that these double-walls also contain large dilution holes whereby the cooling film from the effusion holes is interrupted by the high-momentum dilution jets. Given the importance of cooling the entire panel, including the metal surrounding the dilution holes, the focus of this paper is understanding the flow in the region near the dilution holes. Near-wall flowfield measurements are presented for three different effusion cooling hole patterns near the dilution hole. The effusion cooling hole patterns were varied in the region near the dilution hole and include: no effusion holes; effusion holes pointed radially outward from the dilution hole; and effusion holes pointed radially inward toward the dilution hole. Particle image velocimetry (PIV) was used to capture the time-averaged flowfield at approaching freestream turbulence intensities of 0.5% and 13%. Results showed evidence of downward motion at the leading edge of the dilution hole for all three effusion hole patterns. In comparing the three geometries, the outward effusion holes showed significantly higher velocities toward the leading edge of the dilution jet relative to the other two geometries. Although the flowfield generated by the dilution jet dominated the flow downstream, each cooling hole pattern interacted with the flowfield uniquely. Approaching freestream turbulence did not have a significant effect on the flowfield.

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References

Shrager, A. C. , Thole, K. A. , and Mongillo, D. , 2018, “ Effects of Effusion Cooling Pattern Near the Dilution Hole for a Double-Walled Combustor Liner—Part 1: Overall Effectiveness Measurements,” ASME Paper No. GT2018-77288.
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Figures

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Fig. 1

Illustration of the combustor simulator test

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Fig. 2

Illustration of the center portion (33% of the span) of the combustor panel including the effusion and impingement plates with a pitchwise spacing of the dilution holes at 2.1D. The flowfield measurement plane is defined by the line along the central dilution hole and contains effusion holes in rows 5 and 15.

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Fig. 3

Illustration of the effusion and impingement holes detailing the geometry and parameters as well as defining u and w velocity directions. Note for the top down view, solid lines indicate effusion holes and dashed lines indicate impingement holes.

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Fig. 4

Cross-sectional view of the cooling patterns near the dilution hole for the (a) closed, (b) outward, and (c) inward cases

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Fig. 5

Local effusion momentum flux ratio, Ieff, normalized by inlet effusion momentum flux ratio, Ieff,in, for each of the flow conditions

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Fig. 6

Contours of the turbulence levels and time-averaged streamlines in the centerline plane for the (a) closed, (b) outward, and (c) inward geometries at ID = 30 and Tu = 13%

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Fig. 7

Contours of the turbulence level and time-averaged velocity vectors in the centerline plane, upstream of the dilution jet for the (a) closed, (b) outward, and (c) inward geometries at ID = 30, Tu = 13%

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Fig. 8

Contours of the turbulence level and time-averaged velocity vectors in the centerline plane, downstream of the dilution jet for the (a) closed, (b) outward, and (c) inward geometries at ID = 30, Tu = 13%. Note that the field of view is from x/D = 0.4–1.2.

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Fig. 9

Contours of turbulence level with time-averaged streamlines at Tu = 13% for (a) closed, ID = 30, (b) closed, ID = 20, (c) closed, ID = 11, (d) outward, ID = 30, (e) outward, ID = 20, (f) outward, ID = 11, (g) inward, ID = 30, (h) inward, ID = 20, and (i) inward, ID = 11

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Fig. 10

Centerline overall effectiveness for each effusion hole geometry near the dilution hole for ID = 30 and 11 at Tu = 13%. Note the contours shown are from the ID = 30 case.

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Fig. 11

Contours of turbulence level with time-averaged streamlines for (a) closed, Tu = 0.5%, (b) outward, Tu = 0.5%, (c) inward, Tu = 0.5%, (d) closed, Tu = 13%, (e) outward, Tu = 13%, and (f) inward, Tu = 13% at ID = 30 upstream of the dilution jet. Note the scale of the turbulence level contours is from 0 to 0.8.

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