Gas turbine combustor swirl vane arrangement
US5394688A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Oct 27, 1993 |
| Grant date | Mar 7, 1995 |
| Priority date | — |
| Expiry date | Oct 27, 2013 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/26
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages, each of which has a circumferential array of individually rotatable swirl vanes. The swirl vanes are mounted on axially oriented primary fuel pegs that extend through the air inlet passages. The middle and outer liners form an outer annular passage in which radially oriented secondary fuel pegs are disposed. The middle and inner liners form an inner annular passage that is supplied with cooling air. A perforated circumferentially extending baffle is locating in the inner annular passage and directs the cooling air to flow over the inner liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.