Carbureted fuel injection system for a gas turbine engine
US10436117B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 18, 2013 |
| Grant date | Oct 8, 2019 |
| Priority date | — |
| Expiry date | Jun 29, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/494
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.