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Research Papers

Effects of an Axisymmetric Contoured Endwall on a Nozzle Guide Vane: Convective Heat Transfer Measurements

[+] Author and Article Information
A. A. Thrift

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, State College, PA 16803aat142@psu.edu

K. A. Thole

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, State College, PA 16803kthole@psu.edu

S. Hada

Takasago Machinery Works, Mitsubishi Heavy Industries Ltd., Hyogo 676-8686, Japansatoshi_hada@mhi.co.jp

J. Turbomach 133(4), 041008 (Apr 20, 2011) (10 pages) doi:10.1115/1.4002966 History: Received June 30, 2010; Revised July 01, 2010; Published April 20, 2011; Online April 20, 2011

Heat transfer is a critical factor in the durability of gas turbine components, particularly in the first vane. An axisymmetric contour is sometimes used to contract the cross sectional area from the combustor to the first stage vane in the turbine. Such contouring can lead to significant changes in the endwall flows, thereby altering the heat transfer. This paper investigates the effect of axisymmetric contouring on the endwall heat transfer of a nozzle guide vane. Heat transfer measurements are performed on the endwalls of a planar and contoured passage whereby one endwall is modified with a linear slope in the case of the contoured passage. Included in this study is upstream leakage flow issuing from a slot normal to the inlet axis. Each of the endwalls within the contoured passage presents a unique flow field. For the contoured passage, the flat endwall is subject to an increased acceleration through the area contraction, while the contoured endwall includes both increased acceleration and a turning of streamlines due to the slope. Results indicate heat transfer is reduced on both endwalls of the contoured passage relative to the planar passage. In the case of all endwalls, increasing leakage mass flow rate leads to an increase in heat transfer near the suction side of the vane leading edge.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Depiction of the low speed, closed loop wind tunnel

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Figure 2

Schematic of the (a) planar passage, (b) contoured passage with contour on ceiling, and (c) contoured passage with contour on floor

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Figure 3

(a) Overhead view of the planar vane passage with the initial transformed streamwise velocity in the x-y plane and (b) side view of the planar vane passage with the final transformed velocities at the stagnation plane where secondary flow vectors are plotted

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Figure 4

Comparison of Nusselt number contours between the three endwalls with no leakage flow

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Figure 5

Secondary flow vectors with no leakage flow at the vane stagnation plane for the (a) flat endwall of the planar passage, (b) flat endwall of the contoured passage, and (c) contoured endwall of the contoured passage

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Figure 6

Comparison of Nusselt numbers between the three endwalls with no leakage flow and 1.0% leakage flow, sampled along inviscid streamlines released from (a) 50% pitch and (b) 75% pitch

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Figure 7

Comparison of Nusselt number augmentations with no leakage flow and 1.0% leakage flow, sampled along inviscid streamlines released from (a) 50% pitch and (b) 75% pitch

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Figure 8

Comparison of Nusselt numbers between the three endwalls along the pitch of the vane passage at 0.35Cax with no leakage flow and 1.0% leakage flow

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Figure 9

Comparison of Nusselt number augmentations along the pitch of the vane passage at 0.35Cax with no leakage flow and 1.0% leakage flow

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Figure 10

Comparison of Nusselt number contours between the three endwalls with 0.25% leakage flow

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Figure 11

Comparison of Nusselt number contours between the three endwalls with 0.5% leakage flow

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Figure 12

Comparison of Nusselt number contours between the three endwalls with 0.75% leakage flow

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Figure 13

Comparison of Nusselt number contours between the three endwalls with 1.0% leakage flow

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Figure 14

Secondary flow vectors with 1.0% leakage flow at the vane stagnation plane for the (a) flat endwall of the planar passage, (b) flat endwall of the contoured passage, and (c) contoured endwall of the contoured passage

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Figure 15

Comparison of Nusselt numbers along the pitch of the vane passage at 0.35Cax over a range of leakage flow rates for the (a) flat endwall of the planar passage, (b) flat endwall of the contoured passage, and (c) contoured endwall of the contoured passage

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Figure 16

Comparison of Nusselt number augmentations along the pitch of the vane passage at 0.35Cax over a range of leakage flow rates for the (a) flat endwall of the contoured passage and (b) contoured endwall of the contoured passage

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