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Research Papers

Effects of Deposits on Film Cooling of a Vane Endwall Along the Pressure Side

[+] Author and Article Information
N. Sundaram

Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061nasundar@vt.edu

M. D. Barringer, K. A. Thole

Mechanical and Nuclear Engineering Department, The Pennsylvania University, University Park, PA 16802

J. Turbomach 130(4), 041006 (Jul 31, 2008) (8 pages) doi:10.1115/1.2812332 History: Received June 05, 2007; Revised June 25, 2007; Published July 31, 2008

Film cooling is influenced by surface roughness and depositions that occur from contaminants present in the hot gas path, whether that film cooling occurs on the vane itself or on the endwalls associated with the vanes. Secondary flows in the endwall region also affect the film-cooling performance along the endwall. An experimental investigation was conducted to study the effect of surface deposition on film cooling along the pressure side of a first-stage turbine vane endwall. A large-scale wind tunnel with a turbine vane cascade was used to perform the experiments. The vane endwall was cooled by an array of film-cooling holes along the pressure side of the airfoil. Deposits having a semielliptical shape were placed along the pressure side to simulate individual row and multiple row depositions. Results indicated that the deposits lowered the average adiabatic effectiveness levels downstream of the film-cooling rows by deflecting the coolant jets toward the vane endwall junction on the pressure side. Results also indicated that there was a steady decrease in adiabatic effectiveness levels with a sequential increase in the number of rows with the deposits.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Illustration of the wind tunnel facility

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Figure 2

Illustration of the deposit shape and geometry tested along the pressure side of the vane endwall

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Figure 3

Illustration of the single row deposition on the pressure side along four film cooling rows

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Figure 4

Illustration of the multiple row deposition on the endwall along the pressure side

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Figure 5

Contours of adiabatic effectiveness showing the effect of increasing the film cooling mass flow rate on the pressure side for the base line study

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Figure 6

Laterally averaged effectiveness for the base line study with 0.5% cooling flow rate, and enhancements in laterally averaged effectiveness for the 0.75% and 0.9% mass flow rates

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Figure 7

Contours of adiabatic effectiveness comparing the effect of deposition at a film cooling flow rate of 0.5%

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Figure 8

Reduction in laterally averaged adiabatic effectiveness as a result of deposition located upstream, downstream, and on both sides of the cooling rows

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Figure 9

Area averaged effectiveness comparing the base line study to the deposition located upstream, downstream, and both upstream and downstream

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Figure 10

Reduction in laterally averaged effectiveness as a result of single row deposits located along the pressure side at a coolant flow rate of 0.5%

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Figure 15

Comparison of two superposition methods in predicting the results for the four row deposition study (film cooling at 0.5%)

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Figure 14

Comparison of η¯ between the base line and cases 1R1 and 4R (film cooling at 0.5%)

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Figure 13

Area averaged effectiveness comparing the effect of multiple row deposition with the base line for a low and a high film cooling flow rate

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Figure 12

Reduction in laterally averaged effectiveness as a result of sequentially added multiple row deposits on the pressure side at a coolant flow rate of 0.5%

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Figure 11

Area averaged effectiveness comparing the effect of single row deposition with the base line for a low and a high film cooling flow rate

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