Transition duct with late injection in turbine system
Abstract
A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.
- Inventors:
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1215539
- Patent Number(s):
- 9,133,722
- Application Number:
- 13/459,516
- Assignee:
- General Electric Company (Schenectady, NY)
- DOE Contract Number:
- FC26-05NT42643
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2012 Apr 30
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
LeBegue, Jeffrey Scott, Pentecost, Ronnie Ray, Flanagan, James Scott, Kim, Won -Wook, and McMahan, Kevin Weston. Transition duct with late injection in turbine system. United States: N. p., 2015.
Web.
LeBegue, Jeffrey Scott, Pentecost, Ronnie Ray, Flanagan, James Scott, Kim, Won -Wook, & McMahan, Kevin Weston. Transition duct with late injection in turbine system. United States.
LeBegue, Jeffrey Scott, Pentecost, Ronnie Ray, Flanagan, James Scott, Kim, Won -Wook, and McMahan, Kevin Weston. Tue .
"Transition duct with late injection in turbine system". United States. https://www.osti.gov/servlets/purl/1215539.
@article{osti_1215539,
title = {Transition duct with late injection in turbine system},
author = {LeBegue, Jeffrey Scott and Pentecost, Ronnie Ray and Flanagan, James Scott and Kim, Won -Wook and McMahan, Kevin Weston},
abstractNote = {A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {9}
}
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Works referenced in this record:
Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010
- Bancalari, Eduardo; Wilson, Jody; Little, David A.
- US Patent Document 7,721,547