Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
US10731858B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 16, 2014 |
| Grant date | Aug 4, 2020 |
| Priority date | — |
| Expiry date | May 10, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.