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TECHNICAL PAPERS: Gas Turbines: Ceramics

Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications

[+] Author and Article Information
G. S. Corman, A. J. Dean, S. Brabetz, M. K. Brun, K. L. Luthra

GE Global Research Center, P.O. Box 8, Schenectady, NY 12301

L. Tognarelli, M. Pecchioli

GE Oil and Gas/Nuovo Pignone, GE Power Systems, Via Felice Matteucci, 2, 50127 Firenze, Italy

J. Eng. Gas Turbines Power 124(3), 459-464 (Jun 19, 2002) (6 pages) doi:10.1115/1.1455637 History: Received November 01, 1999; Revised February 01, 2000; Online June 19, 2002
Copyright © 2002 by ASME
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References

Figures

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Processing flow charts for fabrication of prepreg and slurry cast MI-CMCs
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Photograph of turbine shroud components following combustion rig testing
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Schematic of Frame 5 combustors mounted in the test rig. Top: metallic LHE liner. Bottom: test rig liner showing the location of the two MI-CMC liner sections.
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Photograph of the liner assembly for the Frame 5 combustor test rig
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Calculated bulk flame temperature (Tflame cal) and temperature readings of downstream liner (Tlnr) at four locations during cyclic testing in Test 3
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Schematic of the turbine section of the GE-2 engine showing the positions of the stage 1 and stage 2 nozzles (S1N and S2N), buckets (S1B and S2B), and shrouds (S1S and S2S)
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MI-CMC second stage shroud design in the GE-2 engine
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Photograph of a finished prepreg MI-CMC GE-2 shroud ring. The dimensions of the ring were 466 mm ID×57.5 mm wide.
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Photograph of the MI-CMC stage 2 shroud in the GE-2 engine showing the blade tip rub region

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