Gas turbine engine serpentine cooling passage with chevrons
US9476308B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 27, 2012 |
| Grant date | Oct 25, 2016 |
| Priority date | — |
| Expiry date | Jul 4, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.