Flameless combustion systems for gas turbine engines
US8667800B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 13, 2009 |
| Grant date | Mar 11, 2014 |
| Priority date | — |
| Expiry date | Jan 9, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A flameless burner for a gas turbine engine includes a burner body having a longitudinal axis, an upstream section and a downstream section. The upstream section of the burner body defines a primary swirl generating chamber having air swirlers associated therewith. The primary swirl generating chamber is adapted and configured to receive compressor discharge air through the air swirlers. The strong swirl of the compressor discharge air forms a recirculation zone that entrains combustion product gases toward the burner body. Fuel injectors are operatively connected to the downstream section of the burner body for issuing fuel into the recirculated combustion product gases.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.