Stabilizing a gas turbine engine via incremental tuning during transients
US9927818B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 14, 2014 |
| Grant date | Mar 27, 2018 |
| Priority date | — |
| Expiry date | Feb 14, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23N2241/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored. A stability bias is applied to the system if either the state is changing or if lean blowout is imminent until the lean blowout is no longer determined to be imminent. The stability bias monitors operating conditions of the gas turbine engine and determines when one of the operating conditions has overcome a threshold value. Once a threshold value is overcome, a fuel flow fraction is adjusted by a predefined increment. The application of the stability bias is gradually terminated once it is determined that the lean blowout is no longer imminent.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.