Gas turbine combustion liner with triangular heat transfer element
US10184662B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 3, 2014 |
| Grant date | Jan 22, 2019 |
| Priority date | — |
| Expiry date | Apr 29, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03045
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.