System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Sep 29, 2020
Grant Date -
Jul 14, 2016
app pub date -
Jan 11, 2016
filing date -
Jan 12, 2015
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.
First Claim
Other Claims data not available
Family
International Classification(s)
- 2016 Application Filing Year
- F23R Class
- 473 Applications Filed
- 309 Patents Issued To-Date
- 65.33 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 0 Citation Count
- F23R Class
- 0 % this patent is cited more than
- 5 Age
Maintenance Fees
| Fee | Large entity fee | small entity fee | micro entity fee | due date |
|---|---|---|---|---|
| 7.5 Year Payment | $3600.00 | $1800.00 | $900.00 | Mar 29, 2028 |
| 11.5 Year Payment | $7400.00 | $3700.00 | $1850.00 | Mar 29, 2032 |
