Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
US10317080B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 3, 2014 |
| Grant date | Jun 11, 2019 |
| Priority date | — |
| Expiry date | Dec 29, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.