Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity
US6286317A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 18, 1998 |
| Grant date | Sep 11, 2001 |
| Priority date | — |
| Expiry date | Dec 18, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget further includes a first portion connected to the upstream liner section, a second portion connected to the downstream liner section, and a third portion joining the first and second cooling nugget portions at a first end, the third cooling nugget portion extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.