Small exit duct for a reverse flow combustor with integrated cooling elements
US10527288B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 17, 2016 |
| Grant date | Jan 7, 2020 |
| Priority date | — |
| Expiry date | Sep 25, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.