System and method for thermal control in a gas turbine engine
US9003764B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 16, 2011 |
| Grant date | Apr 14, 2015 |
| Priority date | — |
| Expiry date | Oct 22, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E20/16
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system includes a gas turbine engine that includes a compressor section configured to generate compressed air and a combustor coupled to the compressor section. The combustor is configured to combust a first mixture comprising the compressed air and a first fuel to generate a first combustion gas. The gas turbine engine also includes a turbine section coupled to the combustor. The turbine section is configured to expand the first combustion gas to generate an exhaust gas. The gas turbine engine also includes a boiler coupled to the turbine section. The boiler is configured to combust a second mixture comprising a portion of the first combustion gas and a second fuel to generate a second combustion gas that is routed to the turbine section. In addition, the boiler generates a first steam from heat exchange with the second combustion gas.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.