Gas turbine combustor with heat exchanger between rich combustion zone and secondary combustion zone
US11041623B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 14, 2018 |
| Grant date | Jun 22, 2021 |
| Priority date | — |
| Expiry date | Oct 17, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.