Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine
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.
- Research Organization:
- SIEMENS ENERGY, INC. Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FE0023955
- Assignee:
- SIEMENS ENERGY, INC.
- Patent Number(s):
- 9,650,904
- Application Number:
- 15/002,429
- OSTI ID:
- 1357523
- Resource Relation:
- Patent File Date: 2016 Jan 21
- Country of Publication:
- United States
- Language:
- English
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