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TECHNICAL PAPERS

Flow Field Computations of Combustor-Turbine Interactions Relevant to a Gas Turbine Engine

[+] Author and Article Information
Sarah Stitzel, Karen A. Thole

Mechanical Engineering Department, Virginia Tech, Blacksburg, VA 24061

J. Turbomach 126(1), 122-129 (Mar 26, 2004) (8 pages) doi:10.1115/1.1625691 History: Received December 01, 2002; Revised March 01, 2003; Online March 26, 2004
Copyright © 2004 by ASME
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References

Figures

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(Color online) Illustration showing layout for the film-cooling holes and dilution holes relative to the vane location
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Schematic of computational domain for a full pitch combustor model for Case 2 with the slot
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(Color online) Comparisons of surface adiabatic effectiveness contours for Case 2 with the slot (a) predicted using CFD and (b) experimentally measured (Colban and Thole 16)
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(Color online) Comparisons of laterally averaged adiabatic effectiveness through the vane passage computationally predicted and experimentally measured
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(Color online) Streamlines released from slot feed holes around vane for Case 2 with a slot
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Total pressure contours in plane SP for (a) Case 1, (b) Case 2 with the slot and (c) an approaching turbulent boundary layer along the endwall 7
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Velocity vectors in SP for (a) Case 1, (b) Case 2, and (c) turbulent boundary layer 7
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Secondary flow fields in PS-2 for (a) Case 1, (b) Case 2, and (c) an approaching turbulent boundary layer 7
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Secondary flow fields in SS-1 (a) Case 1, (b) Case 2 with the slot, and (c) an approaching turbulent boundary layer along the endwall 7
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(Color online) Streamlines released for Case 1 (no slot) colored by w/Ucomb,exit from (a) 0–13 percent span and (b) 15–20 percent span. (c). Streamlines released at stagnation from 0 to 13 percent of the span at x/C=−0.05 for Case 2 with the slot colored by w/Ucomb,exit.
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Total pressure contours in plane SP for Case 3 with a slot and compound angle film-cooling holes
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Secondary flow fields for Case 3 with compound angle film-cooling and slot (a) plane PS-2 and (b) plane SS-1.
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(Color online) Streamlines released from 0–13 percent span at x/C=−0.05 for Case 3 colored by w/Ucomb,exit.
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(Color online) Endwall effectiveness contours for (a) Case 1 with no slot, (b) Case 2 with slot, and (c) Case 3 compound angled film-cooling holes and slot

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