Method for reducing fuel nozzle coking in a gas turbine engine
US11199325B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 22, 2019 |
| Grant date | Dec 14, 2021 |
| Priority date | — |
| Expiry date | Feb 11, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combustor. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.