Gas turbine arrangement with controlled bleed air injection into combustor, and method of operation
US11680523B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 4, 2017 |
| Grant date | Jun 20, 2023 |
| Priority date | — |
| Expiry date | Jan 25, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/75
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine arrangement for dual fuel operation has a first manifold that delivers a first fuel or compressor bleed fluid and is connected to a bleed port and a first passage for ejecting fuel or fluid into a combustor space. A second manifold delivers a second fuel and is connected to a second passage for ejecting the second fuel into the combustor space. A control system, when operated with the second fuel, provides the second fuel to the second manifold and continuously opens the bleed valve to provide bleed fluid into the first manifold to replace the first fuel. The control system controls the bleed valve over time by throttling a mass flow of the bleed fluid provided to the first passage or by increasing a mass flow of the bleed fluid provided to the first passage to adapt to fuel properties of the second fuel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.