Cooling structure of a combustor tail tube
US6553766B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 12, 2001 |
| Grant date | Apr 29, 2003 |
| Priority date | — |
| Expiry date | Apr 12, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2322
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets (5) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets (5) is varied depending on the metal temperature of parts of the tail tube (4). For example, the passage sectional area of the cooling jackets (5) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets (5) formed at the casing side wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.