Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine
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United States of America Patent
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May 16, 2017
Grant Date -
N/A
app pub date -
Jan 21, 2016
filing date -
Jan 21, 2016
priority date (Note) -
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Abstract
A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straight path segment (26) for receiving a gas flow from a respective combustor. A straight ceramic liner (40) may be inwardly disposed onto a metal outer shell (38) along the straight path segment of the exit piece. Structural arrangements are provided to securely attach the ceramic liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.
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