Gas turbine combustor
US6282886A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 10, 1999 |
| Grant date | Sep 4, 2001 |
| Priority date | — |
| Expiry date | Nov 10, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23L2900/07002
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.