Segmented effusion cooled gas turbine engine combustor
US7546737B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 24, 2006 |
| Grant date | Jun 16, 2009 |
| Priority date | — |
| Expiry date | Jun 15, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor includes two or more sets of effusion cooling holes that extend through the inner and outer liners. Each set of effusion cooling holes includes one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed downstream of the one or more initial rows, and a plurality of interposed rows of effusion cooling holes disposed between the initial and final rows. Each effusion cooling hole is disposed at a tangential angle relative to an axial line. The tangential angle of the effusion cooling holes in each set of effusion cooling holes gradually transitions from a substantially transverse tangential angle in each initial row to a substantially axial tangential angle in each final row.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.