Dual fuel mixer for gas turbine combustor
US5816049A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jan 2, 1997 |
| Grant date | Oct 6, 1998 |
| Priority date | — |
| Expiry date | Jan 2, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/14021
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine is disclosed as including a linear mixing duct having a circular cross-section defined by a wall. A gas fuel manifold is positioned adjacent the upstream end of the mixing duct and is in flow communication with a gas fuel supply and control means. An outer annular swirler is oriented radially to the mixing duct and positioned adjacent the upstream end of the mixing duct to impart swirl to an air stream entering the outer annular swirler. The outer annular swirler includes hollow vanes with internal cavities which are in flow communication with the gas manifold, the outer swirler vanes also having a plurality of gas fuel passages therethrough in flow communication with the internal cavities to inject gas fuel into the radially-oriented air stream. An inner annular swirler is oriented axially with the mixing duct and positioned adjacent the upstream end of the mixing duct to impart swirl to an air stream entering the inner annular swirler. A holder is provided for connecting the inner and outer annular swirlers in radially spaced relation so that a passage is formed upstream of the mixing duct to dire…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.