Gas turbine engine wave geometry combustor liner panel
US10508808B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 12, 2014 |
| Grant date | Dec 17, 2019 |
| Priority date | — |
| Expiry date | Dec 24, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/611
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.