System and method for impingement cooling of turbine system components
US10753611B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 5, 2017 |
| Grant date | Aug 25, 2020 |
| Priority date | — |
| Expiry date | Jul 1, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03342
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor includes a combustor shell, an inner liner disposed inside the combustor shell and having an inner surface defining a cavity configured to receive hot combustion gases from a combustion chamber of the combustor, and an outer surface, the combustor shell and the inner liner defining an annular flow channel therebetween, and a segment carrier operatively connected to the inner liner and operative to receive an upper portion of the inner liner, the segment carrier and the inner liner defining a purging cavity therebetween. The inner liner includes a plurality of impingement jet holes configured to direct a flow of cooling air from the annular flow channel to the purging cavity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.